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
1995051900152	19950519	00152	SW 	1995	5	19	950063210 	1	19950508	G	3211	206030104023	FITTING 			BELL 	206 	206L4 	1182110	SW 										FWD CROSS-TUBE	CRACKED 	B	L	A	ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	173AL	1707 				52066				A FORWARD CROSS-TUBE FITTING WAS FOUND CRACKED DURING THE DAILY INSPECTION. THE CRACK HAD PROPAGATED THROUGH APPROXIMAT	ELY 75 PERCENT OF THE BOSS AREA THAT SECURES THE CROSS-TUBE TO THE FITTING. THE CRACK WAS FORTUNATELY DISCOVERED PRIOR 	TO A COMPLETE FAILURE OF THE FITTING. (X)				1	G	7	1 	3U			NC	H2SW 					 
1996010500256	19960105	00256	NM 	1996	1	5	9519R1624 	1	19951025	G	5330		SKIN 			BOEING	737 	737291 	138448W	NM 										FS 986	CORRODED 	B	P		S5WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	7376F					20364				FUSELAGE SKIN BULGE, STA 986, STR 25L. DISCOVERED DURING ROUTINE C-CHECK INSPECTION CAUSED BY SEALANT FAILURE AT SKIN. 	 SUBMITTER STATED FURTHER CORROSION SHOULD BE DETECTED BY REGULAR SCHEDULED MAINTENANCE INSPECTIONS. (X)					2	L	7	2 	4F				A16WE 					 
1996010500257	19960105	00257	NM 	1996	1	5	9519RI626 	1	19951025	G	5313		STRINGER 			BOEING	737 	737291 	138448W	NM 										FS 500B STR 22L	CRACKED 	B			S5WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	7376F					20364				FUSELAGE STRINGER CRACKED AT STA 500B, STR 22L. DETECTED DURING ROUTINE C-CHECK INSPECTION. SUSPECT CAUSE OF STRESS LO	ADS FROM BAGGAGE LOADING. SUBMITTER SUGGESTS ROUTINE MAINTENANCE INSPECTION SHOULD DETECT ANY FURTHER DAMAGE. (X)					2	L	7	2 	4F				A16WE 					 
1995101300499	19951013	00499	NM 	1995	10	13	95ZZZM535 	1	19950713	G	3221	69B100032	BUSHINGS 			BOEING	747 	747123 	1384873	NM 										NLG	BROKEN 	B			ERKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	905NA	10434				20107				DURING NOSE LANDING GEAR CHANGE, THE LEFT AND RIGHT TRUNNION BEARINGS WERE CLEANED AND REINSTALLED IAW BOEING 747-SCA MM	 CHAPTER 32-21-01. AFTER THE NOSE GEAR WAS INSTALLED, MAINTENANCE PERSONNEL FOUND THE LEFT AND RIGHT TRUNNION BUSHINGS 	BROKEN WITH EVIDENCE OF CRACKING BEFORE GEAR REMOVAL. CRACKING CONDITION NOT FOUND PRIOR TO INSTALLATION WHEN PROCESSED	 PER MM CHAPTER 32-21-01, WHICH DOES NOT REQUIRE ANY SPECIAL INSPECTION OF THE BUSHINGS PRIOR TO INSTALLATION. INSTALLE	D NEW BUSHINGS FABRICATED PER BOEING 747 SRM. REFER TO EVERGREEN AIR CENTER WORKORDER NR 20-0009.		2	L	7	4 	4F				A20WE 					 
1995102700593	19951027	00593	EU 	1995	10	27	95ZZZM565 	1	19950725	G	7712		CONNECTOR 			BAG 	JETSTM	JETSTM3101 	1500215	EU 										RT ENGINE	DIRTY 	A			VNAA	A				UNSCHED LANDING 				N			FALSE WARNING 			CL	CLIMB 	1			GL	07	845JS					769				FLT NR 4145 - AFTER DEPARTURE, RIGHT ENGINE HAD LARGE FLUCTUATIONS IN RPM, EGT AND TORQUE. REDUCED POWER AND ENGINE STA	BILIZED, RETURNED TO FIELD. CLEANED CANNON PLUGS ON RIGHT ENGINE TORQUE SIGNAL CONDITIONER. GROUND RUN AND OPERATIONAL	 CHECK OF ENGINE GOOD. AIRCRAFT RETURNED TO SERVICE. (M)				2	L	7	2 	4T			RT	A21EU 					 
1995102700594	19951027	00594	EU 	1995	10	27	95ZZZM566 	1	19950721	G	7712		TORQUE IND 			BAG 	JETSTM	JETSTM3101 	1500215	EU 										RT ENGINE	FLUCTUATION 	A			VNAA	A				UNSCHED LANDING 				N			FALSE WARNING 			CL	CLIMB 	1			GL	07	845JS					769				FLT NR 4101 - ON CLIMB-OUT RIGHT ENGINE EXPERIENCED AN EGT AND TORQUE FLUCTUATION WITH SRL COMPUTER DEFERRED. RETURNED 	TO PIT, CONDUCTED GROUND RUNS ON ENGINE IAW MM 71-00-00. OPERATIONAL CHECK GOOD. UNABLE TO DUPLICATE DISCREPANCY. AIR	CRAFT RETURNED TO SERVICE. (M)				2	L	7	2 	4T			RT	A21EU 					 
1995121500568	19951215	00568	SW 	1995	12	15	95ZZZM705 	1	19951025	G	5210		SEAL 			SWRNGN	SA227 	SA227AC 	8780603	SW 										CABIN DOOR	WATER CONTAM 	A			PNSA	D				RETURN TO BLOCK 				O			OTHER 			TX	TAXI/GRND HDL 	1			AL	03	650PA					AC775B				CABIN DOOR WOULD NOT SEAL. WATER IN TUBE AT DOOR SEAL, PURGED WATER.						1	L	7	2 	4T				A8SW 					 
1995122200222	19951222	00222	CE 	1995	12	22	95ZZZM730 	1	19951119	G	2911	995800691	RESERVOIR INSTL 			BEECH 	99 	C99 	1154006	CE 										HYD SYSTEM	REQ'D SERVICE 	A			GUUA	O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			SO	19	7209W					U224				FLT NR 417 - EYW-MIA - LANDING GEAR REQUIRED 3 CYCLES TO RETRACT. TROUBLESHOT SYSTEM. FOUND AND BLED AIR FROM HYD POWE	R PACK. SERVICED RESERVOIR. PERFORMED FUNCTIONAL CHECK. BLED AND OPS CHECKED NORMAL.					1	L	7	2 	3T				A14CE 					 
1995031000041	19950310	00041	WP 	1995	3	10	95ZZZX1000 	2	19950210	G	7250		BLADE 			AMD 	FALC50	FALCON50MYST	2730106	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					NR 1 ENG LP TURB	FAILURE 	C				E	B			ENGINE SHUTDOWN 	EMER. DESCENT 			E			VIBRATION/BUFFET 			CR	CRUISE 	1			GL	05	4350M	6300 	2317 			142	P76556			AN IN-FLIGHT SHUT DOWN OF NR 1 ENGINE OCCURRED ON 1-31-95 DURING FLIGHT FROM DAY TO ATW. AT 35,000 FEET, CREW HEARD AND	 FELT NOISE (THUMP) AND VIBRATION. THEY DETERMINED CAUSE TO BE NR 1 ENGINE AND IT WAS SHUT DOWN, VIBRATION CONTINUED UN	TIL ACFT DESCENDED TO 5,000 FEET WHEN WINDMILLNG ENGINE SEIZED. FAILURE IS UNDER INVESTIGATION, FOUND LP3 TURBINE BLADE	 FAILURE.			2	L	7	3 	4F	4	F		A46EU 	E6WE				 
1995031000042	19950310	00042	SO 	1995	3	10	95ZZZX1001 	2	19950120	G	8530	641917	CYLINDER 			UNIVAC	GC1 	GC1B 	9230104	NM 	CONT 	O300 	O300A 	17022	SO 					EXHAUST VALVE	GUIDE FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	2420B	1800 	40 			3720	16110DR			ACFT OWNER'S BOOK ON THE O300A CALLS FOR 80/87 FUEL. HOWEVER, THE LEAD HAS BEEN REMOVED FROM 80/87, SO NO LUBRICATION C	OULD TAKE PLACE. CONTINENTAL USES LEAD IN THE FUEL FOR LUBE. VALVE GUIDES TOTALLY WORE OUT CAUSING LOW COMPRESSION AND	 HIGH OPERATION TEMPERATURES.				1	L	7	1 	3O	3	O		A766 	E253				 
1995031000043	19950310	00043	SO 	1995	3	10	95ZZZX1002 	2	19950120	G	8530		CYLINDER 			UNIVAC	GC1 	GC1B 	9230104	NM 	CONT 	O300 	O300A 	17022	SO 					NR 5 HEAD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	2420B	1800 	40 			3720	16110DR			CYLINDER CRACKED BETWEEN INTAKE AND EXHAUST SEATS.						1	L	7	1 	3O	3	O		A766 	E253				 
1995031000044	19950310	00044		1995	3	10	95ZZZX1003 	1	19950210	G	2434	902014	BEARING 	PRESTOLITE 	ALT9422 															SLIP RING END	FAILED 	B			CYKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07					10K000342					BEARING INNER RACE DOES NOT SEEM TO BE PROPERLY HARDENED. MARKINGS ON BEARING: PEER TRI 13307E JAPAN.																			 
1995031000046	19950310	00046	NE 	1995	3	10	95ZZZX1005 	1	19950104	G	7900		BREATHER 			CONAER	LA4 	LA4200 	5110310	NE 										ENGINE OIL	ICE BLOCKED 	G				A				UNSCHED LANDING 				K			FLUID LOSS 			CL	CLIMB 	1			GL	15	2FOR					568				AIRCRAFT DEPARTED INL ON A MINUS 9 DEGREES FAHRENHEIT DAY. OIL BREATHER PLUGGED WITH ICE, FRONT OIL SEAL BLOW-OUT ALONG	 WITH ALL THE ENGINE OIL. AIRCRAFT WAS SUBSTANTIALLY DAMAGED DURING 'OFF FIELD' LANDING. AD 64-17-05 IS NOT APPLICABLE	 BECAUSE BREATHER HAS A 'NICKLE SLOT' CUT IN IT DURING MANUFACTURE, BUT SLOT WAS FILLED WITH ICE. SUBMITTER RECOMMENDS 	MOVING BREATHER LINE AND AIR/OIL SEPARATOR TO A WARMER PART OF THE ENGINE COWLING. IT IS CURRENTLY MOUNTED IN THE FRONT	 NOSE COWL WHICH PROVIDES NO PROTECTION FROM THE ELEMENTS.		1	H	7	1 	3O				1A13 					 
1995032000352	19950320	00352	CE 	1995	3	20	95ZZZX1006 	1	19950102	G	5520	043200151	ELEVATOR 			CESSNA	150 	152 	2071835	CE 										LT ELEVATOR	NUTPLATE FAILED 	D				O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			SO	16	1931H	4896 				15283831				LEFT ELEVATOR DEPARTED AIRCRAFT IN-FLIGHT WITH NO DAMAGE TO THE PLANE. SUSPECT THE OUTBOARD HINGE BOLT FELL OUT DUE TO 	NUTPLATE MALFUNCTION. EITHER IT BACKED OUT BECAUSE OF LOSS OF LOCKING ACTION OF THE NUTPLATE, OR THE NUTPLATE FAILED AN	D BROKE UP BECAUSE OF CORROSION FORCES ON THE METAL AND THE BOLT CAME OUT. CORRECTION ACTION WOULD BE TO REPLACE ALL TH	E OLD NUTPLATES WITH AN310-3 NUT AND COTTER PIN. NUTPLATE PN NAS682A3.			1	H	7	1 	3O			NT	3A19 					 
1995031000047	19950310	00047	EA 	1995	3	10	95ZZZX1007 	2	19950208	G	8530	LW16343	INTAKE PIPE 			AMTR 	GHAWK 	GOSHAWK 		GL 	LYC 	O540 	IO540P1A5 	41532	EA 					NR 3 CYL FLANGE	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	345RM		304 			001	L800048			DURING ROUTINE MAINTENANCE, MAINTENANCE PERSONNEL NOTED THAT NR 3 CYLINDER INTAKE PIPE WAS LOOSE AT CYLINDER. FOUND INT	AKE PIPE BROKEN ABOUT 45 DEGREES AT THE FLANGE. REPLACED PART WITH A NEW INTAKE PIPE. OLD INTAKE PIPE HAD BEEN CHROMEP	LATED BY UNKNOWN SHOP. SUSPECT HYDROGEN EMBRITTLEMENT. RECOMMEND THAT INTAKE PIPES NOT BE CHROMEPLATED.				1	H	7	1 	3O	3	O		EXPA1H71	1E4				 
1995031000048	19950310	00048	CE 	1995	3	10	95ZZZX1008 	1	19950214	G	3230	12430661	CLEVIS ASSY 			CESSNA	210 	210 	2073402	CE 										NLG UPLOCK	FAILED 	D		A		O				OTHER 				O			OTHER 			AP	APPROACH 	1			SW	11	7481E					57181				NOSE LANDING GEAR FAILED TO EXTEND. NOSE GEAR UPLOCK ACT. CLEVIS ASSY FAILED CAUSING NOSE GEAR ASSY TO STAY IN UP AND L	OCKED POSITION. UPLOCK ASSY IS SPRING LOADED TO THE LOCKED POSITION TO RELIEVE HYDRAULIC SYSTEM PRESS. AND HOLD DOORS U	P. SUBMITTER RECOMMENDS EVERY 100 HOURS CHECK CLEVIS ASSY FOR SECURITY OF COTTER KEY IN CLEVIS ASSY FOR LOCKING EFFECTI	VENESS.			1	H	7	1 	3O			RT	3A21 					 
1995031000049	19950310	00049	SO 	1995	3	10	95ZZZX1009 	2	19950127	G	7322	6462124	PUMP FITTING 			GULSTM	500 	500A 	0141104	SW 	CONT 	O470 	IO470M 	17026	SO 					ENGINE FUEL	FAILED 	B			UPNR	O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			WP	25	57EB				1C109407BR	500A124571				FOUND FUEL PUMP HAS 90 DEGREE MALE TO FEMALE BRASS FITTING DEFECTIVE. FITTINGS ARE OVERTORQUED AND ONE FITTING FAILED I	N-FLIGHT. OTHER PUMP, UPON REMOVAL, HAD FITTING FAIL WITH ABOUT 25 INCH/POUNDS OF TORQUE.					1	H	7	2 	3O	3	O		6A1 	3E1				 
1995031000050	19950310	00050	SO 	1995	3	10	95ZZZX1010 	1	19950213	G	3246	9533348	WHEEL 	LORAL 	9542306 	GULSTM	G1159 	G1159 	3953505	SO 										MAIN GEAR	CRACKED 	B			COZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27					JULY71200					WHEEL WAS REPORTED TO HAVE A SLOW LEAK. PERFORMED LEAK CHECK AND FOUND LEAK COMING FROM BOLT HOLE AREA ON THE OUTBOARD 	WHEEL HALF. DYE-PENETRANT SHOWED NO DEFECT. PERFORMED EDDY CURRENT AND U.T. INSPECTION AND BOTH METHODS SHOWED A DEFEC	T FROM THE BOLT-BOSS INNER RADIUS AREA INTO THE TIRE WELL AREA. THIS IS THE SECOND DEFECT IN THIS AREA ON THIS PART NUM	BER WHEEL SUB-ASSEMBLY FOUND BY THIS REPAIR STATION.			2	L	7	2 	4F			RT	A12EA 					 
1995031000053	19950310	00053	WP 	1995	3	10	95ZZZX1013 	1	19950209	G	5230	37061647	FITTING 			DOUG 	DC8 	DC871F 	302199D	WP 										FWD CARGO DOOR	CRACKED 	B			EE4Y	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	23	825BX	71536				45978				FORWARD CARGO COMPARTMENT 'A' DOOR RT, NR 2 FITTING CRACKED.						2	L	7	4 	4F			RT	4A25 					 
1995031000054	19950310	00054	WP 	1995	3	10	95ZZZX1014 	1	19950209	G	5330		SKIN 			DOUG 	DC8 	DC871F 	302199D	WP 										STA Y620 L34L	CORRODED 	B			EE4Y	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	23	825BX	71536				45978				FORWARD CARGO COMPARTMENT, STA Y620.00, BETWEEN LONGERON 34L AND 34R, FUSELAGE SKIN CORRODED.						2	L	7	4 	4F			RT	4A25 					 
1995031000055	19950310	00055	NE 	1995	3	10	95ZZZX1015 	2	19950209	G	7250	3054289010	MANIFOLD 			DOUG 	DC8 	DC871F 	302199D	WP 	GE 	CFM56 	CFM562C1 	13802	NE 					INLET PORT RT	CRACKED 	B			EE4Y	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	23	825BX		28348			45978	693209			ENGINE NR 1, LOW PRESSURE TURBINE COOLING MANIFOLD DISTRIBUTOR INLET PORT CRACKED AT RIGHT SIDE.						2	L	7	4 	4F	4	F	RT	4A25 	E2GL				 
1995031000056	19950310	00056	NE 	1995	3	10	95ZZZX1016 	2	19950209	G	7250	3054289010	MANIFOLD 			DOUG 	DC8 	DC871F 	302199D	WP 	GE 	CFM56 	CFM562C1 	13802	NE 					NR 3 ENGINE	CRACKED 	B			EE4Y	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	23	825BX		27785			45978	693303			ENGINE NR 3 LOW PRESSURE TURBINE COOLING MANIFOLD DISTRIBUTOR, CRACKED AT 10 O'CLOCK POSITION.						2	L	7	4 	4F	4	F	RT	4A25 	E2GL				 
1995031000063	19950310	00063	CE 	1995	3	10	95ZZZX1023 	1	19950202	G	5610	NP1397211	WINDSHIELD 			CESSNA	650 	650 	2076802	CE 										PILOT	CRACKED 	B			GMCR	K				NONE 				O			OTHER 			TX	TAXI/GRND HDL 	1			GL	23	5113	65 			92043H6023	7013				PILOT'S WINDSHIELD OUTER LAYER CRACKED WHILE TAXIING TO RAMP AFTER LANDING.						2	L	7	2 	4F				A9NM 					 
1995031000064	19950310	00064	CE 	1995	3	10	95ZZZX1024 	1	19950214	G	2730		CONTROL CABLE 			BEECH 	MU300 	400BEECH 	 	CE 										ELEVATOR	OUT OF ADJ 	B			VIB4	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	61SM					RK60				PILOT COMPLAINED THAT IN A HIGH SPEED DESCENT, THE AUTOPILOT WOULD NOT MAINTAIN CONSTANT AIRSPEED. IN INSPECTING THE AI	RCRAFT, THE ELEVATOR CABLES WERE SET 35 POUNDS ABOVE MAXIMUM TENSION SETTING AND WITH THE ELEVATOR'S PIN IN THE NEUTRAL 	POSITION, THE LEFT ELEVATOR WAS IN THE NEUTRAL POSITION, BUT THE RIGHT ELEVATOR WAS ONE INCH ABOVE NEUTRAL. RECENTERED 	TORQUE TUBE AND REPLACED A SHIM. P/N: AN960D516L BETWEEN THE BEARING. RESET ALL CABLE TENSIONS TO SPECS.			2	H	7	2 	4F			RT	A16SW 					 
1995031000065	19950310	00065	CE 	1995	3	10	95ZZZX1025 	1	19950129	G	3340	MS3505822	SWITCH 			CESSNA	500 	S550 	2076607	CE 										LANDING LIGHT	DEFECTIVE 	B			DXTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	112QS	7966 				S5500112				RIGHT LANDING LIGHT INOPERATIVE. FOUND COCKPIT ON/OFF SWITCH BAD. SWITCH HAS SIGNS OF HEAT ON BOTTOM OF IT, AND AT ONE	 LUG CONNECTION. OPERATED UNDER NORMAL CONDITIONS. SUBMITTER SUGGESTS SWITCH COULD NOT HANDLE CURRENT.					1	L	7	2 	4F			RT	A22CE 					 
1995031000066	19950310	00066	CE 	1995	3	10	95ZZZX1026 	1	19950131	G	2810	10092007113	ADAPTER PLATE 			BEECH 	200 	200BEECH 	1152920	CE 										RT NACELLE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	8SV	4700 				BB506				THE RIGHT NACELLE FUEL CELL WAS BEING REINSTALLED AFTER REPAIR. ALL PLATES AND ADAPTERS WERE BEING CLEANED AND INSPECTE	D PRIOR TO BEING REINSTALLED. THE DEFUELING ADAPTER WAS FOUND TO HAVE 4 SPOTS OF CORROSION, ONE OF WHICH HAD REACHED TH	ROUGH THE PLATE. THE NEW PLATE ASSY HAS A PAINTED FINISH ON IT. SUBMITTER RECOMMENDS A SHORTER PERIOD FOR NACELLE INSP	ECTION. CURRENTLY, 30 MONTHS OR 2550 HOURS. RECOMMEND 18 MONTHS OR 600 HOURS. SECOND PLATE ASSY ON KA200'S TO BE REPL	ACED, BOTH 1970'S VINTAGE.		1	L	7	2 	4T				A24CE 					 
1995031000067	19950310	00067	CE 	1995	3	10	95ZZZX1027 	1	19950126	G	5610	45AS310102	WINDOW 	PPG 	NP1382022 	BEECH 	MU300 	400BEECH 		CE 										COPILOT SIDE	CHIPPED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	440DS	1015 			82H0516229	RK8				DURING CLEANING OF THE COPILOT'S SIDE WINDOW, A DEFECT WAS FOUND IN THE UPPER FORWARD CORNER. INVESTIGATION FOUND IT WA	S A CHIP CAUSED BY THE WINDOW FRAME COMING IN CONTACT WITH THE WINDOW AND CAUSING A CHIP. THIS WAS A FACTORY INSTALLED 	WINDOW. CHECK CLEARNESS AROUND THE WINDOW FRAME.				2	H	7	2 	4F			RT	A16SW 					 
1995031000068	19950310	00068	CE 	1995	3	10	95ZZZX1028 	1	19950126	G	8010	6041H190	RELAY 	CUTLERHAM 		BEECH 	200 	200BEECH 	1152920	CE 										LT ENG STARTER	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	222KA					BB49				WHEN BATTERY MASTER WAS SWITCHED TO THE 'ON' POSITION, THE LEFT ENGINE BEGAN TO SPOOL UP. THE CONTACT POINTS WERE WELDE	D SHUT ON START RELAY. REPLACED RELAY, OKAY FOR SERVICE.					1	L	7	2 	4T				A24CE 					 
1995031000072	19950310	00072	CE 	1995	3	10	95ZZZX1032 	1	19950113	G	5320	504300431183	INTERCOSTAL 			BEECH 	200 	200BEECH 	1152920	CE 										CABIN DOOR	CRACKED 	B			KI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	191FL					BB107				INTERCOSTAL FOUND CRACKED AT HANDRAIL SUPPORT RIVET HOLES. (2 PLACES.) CRACKS ARE SEVERE ENOUGH, CABIN DOOR HANDRAIL S	UPPORT COULD COME FREE, CAUSING DOOR TO CONTACT GROUND. SUBMITTER RECOMMENDS PAYING SPECIAL ATTENTION TO THIS AREA DURI	NG 150-HOUR INSPECTIONS.				1	L	7	2 	4T				A24CE 					 
1995031000074	19950310	00074	SO 	1995	3	10	95ZZZX1034 	1	19950210	G	3610	18368031	PRE-COOLER 	AIRESRCH 		GULSTM	G1159 	G1159 	3953505	SO 										CORE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	26WP	8741 			28171	24				DISCOVERED PRE-COOLER LEAKING WHILE DOING OTHER TROUBLESHOOTING DURING ENGINE RUN-UP. THESE PRE-COOLERS HAVE A HISTORY 	OF CRACKING WITH AGE AND USE. INSTALLED NEW PRE-COOLER.					2	L	7	2 	4F			RT	A12EA 					 
1995031000078	19950310	00078	CE 	1995	3	10	95ZZZX1038 	1	19950206	G	3230	63183233	PC BOARD 			CESSNA	525 	525 	2076601	CE 										MLG	DEFECTIVE 	B			ERY2	O				OTHER 				O			OTHER 			AP	APPROACH 	1			SO	11	444RH	1227 				5250001				PILOT REPORTED LANDING GEAR AND FLAP SYSTEM CIRCUIT BREAKER TRIPPED AND WOULD NOT RESET. LANDING GEAR WAS BLOWN DOWN WI	TH EMERGENCY SYSTEM. TROUBLESHOT SYSTEM AND FOUND P.C. BOARD HAD BURNED TRACKS. FOUND CIRCUIT BREAKER FOR LANDING GEAR	 CONTROL DIODE ON LAND VALVES GROUNDING. REPLACED ABOVE NOTED ITEMS WITH NEW UNITS.				1	L	7	2 	4F			RT	A1WI 					 
1995031000079	19950310	00079	CE 	1995	3	10	95ZZZX1039 	1	19950206	G	3230	52899L5	CIRCUIT BREAKER 			CESSNA	525 	525 	2076601	CE 										MLG	SHORTED 	B			ERY2	O				OTHER 				O			OTHER 			AP	APPROACH 	1			SO	11	444RH	1227 				5250001				PILOT REPORTED LANDING GEAR AND FLAP SYSTEM CIRCUIT BREAKER TRIPPED AND WOULD NOT RESET. LANDING GEAR WAS BLOWN DOWN WI	TH EMERGENCY SYSTEM. TROUBLESHOT SYSTEM AND FOUND P.C. BOARD HAD BURNED TRACKS. FOUND CIRCUIT BREAKER FOR LANDING GEAR	 CONTROL DIODE ON LAND VALVES GROUNDING. REPLACED ABOVE NOTED ITEMS WITH NEW UNITS.				1	L	7	2 	4F			RT	A1WI 					 
1995031000081	19950310	00081	EU 	1995	3	10	95ZZZX1041 	1	19950114	G	6730	SC50811A	SERVO 			SNIAS 	350 	AS350BA 	8680817	EU 										LT LATERAL	LEAKING 	D		A		A	H			UNSCHED LANDING 	DEACTIVATE SYST/CIRCUITS			J	K		WARNING INDICATION 	FLUID LOSS 		CR	CRUISE 	1			WP	13	269JM	6773 	269 			1398				DURING 3RD TOUR FLIGHT OF THE DAY, 2.6 HOURS SINCE PRE-FLIGHT, THE WARNING HORN SOUNDED AND THEN THE HYD LIGHT ILLUMINAT	ED ON THE WARNING PANEL. PILOT SLOWED THE AIRCRAFT AND TURNED THE HYDRAULICS OFF & MADE AN EMERGENCY LANDING AT KALAPAP	A AIRPORT. UPON INPSECTION OF THE TRANSMISSION AREA, THE LT TRANSMISSION DECK, LT SERVO, AND LT TRANSMISSION AREAS WERE	 COVERED IN HYD FLUID. CLEANED AND INSPECTED LT SERVO AND LINES AND NO OBVIOUS SOURCE OF THE LEAK WAS DETECTED. ADDED 	1 QUART OF HYD FLUID TO RESERVOIR & RAN ACFT. AFTER SEVERAL MINUTES, HYD FLUID KEPT SEEPING OUT OF SERVO AT MATING AREA	 OF UPPER TAPERED SHAFT & SERVO BODY. REPLACED SERVO, SERVICED RESERVOIR, & RETURNED TO BASE WITH NO FURTHER LEAKAGE.	1	G	7	1 	3U			NC	H9EU 					 
1995031000433	19950310	00433	NE 	1995	3	10	95ZZZX1049 	2	19950209	G	7261		ENGINE 			SNIAS 	350 	AS350D 	8680803	EU 	LYC 	LTS101	LTS101600A3 	41560	NE 					OIL SYSTEM	CHIP WARNING 	D				A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			WP	13	5771N					1344				DURING FLIGHT, ENGINE CHIP LIGHT WARNING MADE PRECAUTIONARY LANDING. MECHANIC INSPECTED ENGINE LUBE SYSTEM, CHIP PLUGS 	AND WIRING, FOUND NO DEFECTS. ACFT RETURNED TO SERVICE.					1	G	7	1 	3U	3	U		H9EU 	E5NE				 
1995031000434	19950310	00434	NE 	1995	3	10	95ZZZX1050 	1	19950116	G	6510	7636105201048	DRIVE SHAFT 			SKRSKY	S76 	S76A 	8143006	NE 										T/R NR 1	SCORED 	B			ZV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	31211	6379 				760225				WHEN COMPLYING WITH ASB 76-53-35, MOD TO CENTER FIREWALL, FOUND NR 1 DRIVE SHAFT SCORED FOR A LENGTH OF 4.50 INCHES. DE	PTH OF SCORE APPROXIMATELY .005 INCH. REPLACED WITH NEW SHAFT. SUSPECT THAT SOMEONE PRESSED DOWN ON TOP OF CENTER FIRE	WALL CAUSING IT TO RUB SHAFT. ASB WILL RELIEVE CAUSE OF PROBLEM.				1	G	7	2 	3U				H1NE 					 
1995031000435	19950310	00435	EU 	1995	3	10	95ZZZX1051 	1	19950222	G	6210		BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										BALANCE WEIGHT	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	214AE	4103 				7206				MAIN ROTOR BLADE BALANCE WEIGHT IS SHIFTING DUE CENTRIFUGAL FORCE WHICH CAUSES LEAD WEIGHT TO BULGE THE BLADE OUTER SKIN	 BEYOND MFG'S LIMITS RENDERING THE BLADE UNSERVICEABLE.					1	G	7	2 	3U				H13EU 					 
1995031000436	19950310	00436	EU 	1995	3	10	95ZZZX1052 	1	19950222	G	6120	117150071	BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										BALANCE WEIGHT	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	215AE	2288 			1277	7216				MAIN ROTOR BLADE BALANCE WEIGHT IS SHIFTING DUE TO CENTRIFUGAL FORCE HWICH CAUSES LEAD WEIGHT TO BULGE THE BLADE OUTER S	KIN BEYOND LIMITS RENDERING THE BLADE UNSERVICEABLE.					1	G	7	2 	3U				H13EU 					 
1995031000440	19950310	00440	SW 	1995	3	10	95ZZZX1056 	1	19950126	G	6300	206010335001	LEVER ASSEMBLY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27545		411 			45234				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, PN 206-010-338-0	01 SPACERS, 4 EACH, PN 206-010-337-001 BEARINGS, 2 EACH, NAS6605D64 BOLTS. NORMAL OPERATION CAUSES PARTS TO WEAR OUT TO	O SOON. SPACERS, BEARINGS, AND BOLTS TT 410.5.				1	G	7	1 	3U				H2SW 					 
1995031000441	19950310	00441	SW 	1995	3	10	95ZZZX1057 	1	19950126	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27545		411 			45234				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, PN 206-010-338-0	01 SPACERS, 4 EACH, PN 206-010-337-001 BEARINGS, 2 EACH, NAS6605D64 BOLTS. NORMAL OPERATION CAUSES PARTS TO WEAR OUT TO	O SOON. SPACERS, BEARINGS, AND BOLTS TT 410.5.				1	G	7	1 	3U				H2SW 					 
1995031000442	19950310	00442	SW 	1995	3	10	95ZZZX1058 	1	19950124	G	5302	206031403001	FITTINGS 		206033004177	BELL 	206 	206L4 	1182110	SW 										T/B ATTACH	LOOSE RIVETS 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	172AL	1377 	450 		52061	52065				DURING PHASE INSPECTION, FOUND WORKING (LOOSE) RIVETS ON ALL FOUR TAILBOOM ATTACH FITTINGS. SUSPECT CAUSE IS USE OF E-R	IVETS AND SOME BAD RIVET BUCK TAILS.					1	G	7	1 	3U			NC	H2SW 					 
1995031000443	19950310	00443	SW 	1995	3	10	95ZZZX1059 	1	19950124	G	5302	206031403005	FITTINGS 		206033004177	BELL 	206 	206L4 	1182110	SW 										T/B ATTACH	LOOSE RIVETS 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	172AL	1377 	450 		52061	52065				DURING PHASE INSPECTION, FOUND WORKING (LOOSE) RIVETS ON ALL FOUR TAILBOOM ATTACH FITTINGS. SUSPECT CAUSE IS USE OF E-R	IVETS AND SOME BAD RIVET BUCK TAILS.					1	G	7	1 	3U			NC	H2SW 					 
1995031000573	19950310	00573	EA 	1995	3	10	95ZZZX1082 	2	19950216	G	7414	10382543	BREAKER CAM 	BENDIX 	D6LN2031 	CESSNA	182 	TR182 	2072735	CE 	LYC 	O540 	O540L3C5 	41532	EA 					ENGINE MAG	LOOSE 	D	L			O				OTHER 				R	W		PARTIAL RPM/PWR LOSS 	INADEQUATE Q C 		CL	CLIMB 	1			NM	09	756QU	1520 			22655K	R18201131	L2151640A			ACFT HAD EXCESS POWER LOSS FROM ENGINE ON CLIMBOUT. INVESTIGATION FOUND MAG BREAKER DRIVE CAM SLIPPING. CAM SCREW WAS 	TIGHT AND TO SPECS. SUBMITTER SUSPECTS TAPER ON ROTOR SHAFT TO BE OUT OF TOLERANCE ALLOWING CAM TO BOTTOM OUT.					1	H	7	1 	3O	3	O		3A13 	E295				 
1995031000574	19950310	00574	CE 	1995	3	10	95ZZZX1083 	1	19950201	G	3233	12810013	ACTUATOR 			CESSNA	172 	172RG 	2072438	CE 										MLG	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17										THE FEBRUARY ISSUE STATED THE BOLTS USED TO SECURE MLG ACTUATOR WERE NOT DRILLED AND WERE LOOSE. SUBMITTER SUGGESTS THE	SE BOLTS SHOULD HAVE DRILLED HEADS AND SHOULD BE SAFETY WIRED. SUBMITTER HAS FOUND NUMEROUS CRACKED ACTUATORS, ALL WITH	 PROPERLY TORQUED BOLTS. HOWEVER, THESE CRACKED ACTUATORS WERE ACCOMPANIED BY THE PISTON ROLLER AND BEARING MOVED OUTWA	RD ABOUT .25 INCH. ALL AIRCRAFT WERE INSPECTED EVERY 100 HOURS. THE CRACK WAS FOUND SOMETIMES ONLY ON ONE SIDE, SOMETI	MES BOTH SIDES. CAUSE UNKNOWN.		1	H	7	1 	3O				3A17 					 
1995031000575	19950310	00575	NE 	1995	3	10	95ZZZX1084 	1	19950131	G	6710	7640000014055	CONTROL TUBE 			SKRSKY	S76 	S76B 	8143007	NE 										BROOM CLOSET	CHAFED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	5AC	1302 				760348				DURING FLIGHT CONTROL INSPECTION, FOUND COLLECTIVE PUSH/PULL TUBE CHAFED ON FORWARD SIDE BOTTOM END. TUBE CHAFED ON KEL	VAR STRUCTURE AND RIVETS. TUBE LOCATED IN BROOM CLOSET AREA AFT OF CREW SEATS.					1	G	7	2 	4U				H1NE 					 
1995031000576	19950310	00576	WP 	1995	3	10	95ZZZX1085 	1	19950213	G	2842	269A4609	SENDER 		269A83469 	HUGHES	269 	269B 	4470502	WP 										MAIN FUEL TANK	STICKING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	9474F					1160278				FUEL GAUGE REPORTED TO BE INOP. INSPECTION REVEALED THAT FUEL SENDER WAS CORRODED AND STICKING IN LOWER POSITION. PART	 TOTAL TIME AND TIME OF INSTALLATION UNKNOWN.					1	G	7	1 	3O				4H12 					 
1995031000577	19950310	00577	EU 	1995	3	10	95ZZZX1086 	1	19950210	G	5531	1090372453	SPAR 			AGUSTA	A109 	A109A2 	0260120	EU 										VERTICAL FIN	CRACKED 	B			KUVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	109RP	384 				7387				DURING COMPLIANCE WITH MANDATORY B.T. 109-96, FOUND AFT VERTICAL FIN SPAR CRACKED AT LOWER END ABOVE HEAVY 'H' BRACKET O	N REAR OF SPAR. THIS IS THE SECOND INSTANCE FOUND ON THIS SERIES ACFT. REPAIRED PER AGUSTA SUPPLIED DRAWINGS.					1	G	7	2 	3U				H7EU 					 
1995031000578	19950310	00578	EU 	1995	3	10	95ZZZX1087 	1	19950113	G	7120	365A51103800	MOUNT 			AEROSP	SA365 	AS365N2 	8680815	EU 										LT ENG REAR	CRACKED 	B			OF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	365AH					6379				MOUNT CRACKED FROM OUTSIDE DIAMETER OF WASHER AT MOUNTING STUD TO OUTBOARD EDGE OF MOUNT. LIGHT RADIUS ON OUTSIDE DIAME	TER OF WASHER MAY ELIMINATE CRACKING. BELIEVE PART T.T. TO BE THE SAME AS AFTT 734.8.					1	G	7	2 	3U			RT	H10EU 					 
1995031000579	19950310	00579	SW 	1995	3	10	95ZZZX1088 	1	19950205	G	2620	209070280101	SWITCH 			BELL 	412 	412 	1182202	SW 										FIRE EXT	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	4UV	3598 				33199				DURING 600-HOUR FIRE EXTINGUISHER VOLT CHECK, FOUND NO POWER TO NR 1 ENGINE RESERVE SYSTEM AND MAIN SYSTEM WAS INTERMITT	ENT. TEE HANDLE CONSISTS OF 8 MICROSWITCHES. WHEN TEE HANDLE WAS PULLED, SLIDER BAR FORCED TAB DOWN TO ENGAGE MICROSWI	TCHES. SLIDER BAR WAS LOOSE AND TAB SLIGHTLY BENT PREVENTING ENGAGEMENT OF TWO OUTBOARD MICROSWITCHES.				1	G	7	2 	4U				H4SW 					 
1995031000581	19950310	00581	EU 	1995	3	10	95ZZZX1090 	1	19950120	G	6210	355A11002004	BLADE 			AEROSP	AS355 	AS355F1 	8680810	EU 										STA 1360MM	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	707WR	1696 			2798	5239				DURING A PRE-FLIGHT INSPECTION, PILOT IDENTIFIED THE SUSPECTED DEFECT AND NOTIFIED MAINTENANCE. UPON INSPECTION, A CRAC	K WAS DETECTED ON THIS MAIN ROTOR BLADE AT STATION 1360MM. CRACK LENGTH WAS 150MM CORDWISE. AS355 MAIN ROTOR BLADES HA	VE A HISTORY OF THIS DEFECT IN THE AREA OF STATION 1000MM TO STATION 1400MM.				1	G	7	2 	3U				H11EU 					 
1995031000582	19950310	00582	CE 	1995	3	10	95ZZZX1091 	1	19950201	G	5312	24130018	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD TORQUE TUBE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	966LA	4133 				172RG1102				FOUND UPPER BULKHEADS CRACKED AT TOP OF RUDDER PEDAL TORQUE TUBE OPENING JUST AFT OF MOUNTING BOLT FOR PN 2460004-1 BELL	CRANK ASSY. LT SIDE CRACKED COMPLETELY THROUGH. RT SIDE ALSO DAMAGED DUE TO BOLT HEAD ON THE BELLCRANK HITTING IT. FO	UND UPPER BULKHEADS, PN 2413001-5 & PN 2413001-8, & LOWER BULKHEADS, PN 2413001-3 & PN 2413001-4, CRACKED AT AFT BOLT HO	LE FOR PN 20670011-1 RUDDER TORQUE TUBE BEARING ASSYS. LT BULKHEADS WERE FOUND IN WORSE CONDITION THAN RT. ACFT HAS HA	D 1 LANDING WHERE NOSE GEAR FOLDED & IS USED FOR FLT TRAINING. RECOMMEND THOROUGH INSP OF AREA EVERY 100 HRS. UPPER BU	LKHEADS NEED TO BE REINFORCED AT TOP EDGE OF OPENING & STRONGER MTNG FOR RUDDER BEARING BLKS NEEDS TO BE DEVELOPED.	1	H	7	1 	3O				3A17 					 
1995031000583	19950310	00583	CE 	1995	3	10	95ZZZX1092 	1	19950201	G	5312	24130015	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD TORQUE TUBE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	966LA	4133 				172RG1102				FOUND UPPER BULKHEADS CRACKED AT TOP OF RUDDER PEDAL TORQUE TUBE OPENING JUST AFT OF MOUNTING BOLT FOR PN 2460004-1 BELL	CRANK ASSY. LT SIDE CRACKED COMPLETELY THROUGH. RT SIDE ALSO DAMAGED DUE TO BOLT HEAD ON THE BELLCRANK HITTING IT. FO	UND UPPER BULKHEADS, PN 2413001-5 & PN 2413001-8, & LOWER BULKHEADS, PN 2413001-3 & PN 2413001-4, CRACKED AT AFT BOLT HO	LE FOR PN 20670011-1 RUDDER TORQUE TUBE BEARING ASSYS. LT BULKHEADS WERE FOUND IN WORSE CONDITION THAN RT. ACFT HAS HA	D 1 LANDING WHERE NOSE GEAR FOLDED & IS USED FOR FLT TRAINING. RECOMMEND THOROUGH INSP OF AREA EVERY 100 HRS. UPPER BU	LKHEADS NEED TO BE REINFORCED AT TOP EDGE OF OPENING & STRONGER MTNG FOR RUDDER BEARING BLKS NEEDS TO BE DEVELOPED.	1	H	7	1 	3O				3A17 					 
1995031000584	19950310	00584	CE 	1995	3	10	95ZZZX1093 	1	19950201	G	5312	24130013	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD TORQUE TUBE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	966LA	4133 				172RG1102				FOUND UPPER BULKHEADS CRACKED AT TOP OF RUDDER PEDAL TORQUE TUBE OPENING JUST AFT OF MOUNTING BOLT FOR PN 2460004-1 BELL	CRANK ASSY. LT SIDE CRACKED COMPLETELY THROUGH. RT SIDE ALSO DAMAGED DUE TO BOLT HEAD ON THE BELLCRANK HITTING IT. FO	UND UPPER BULKHEADS, PN 2413001-5 & PN 2413001-8, & LOWER BULKHEADS, PN 2413001-3 & PN 2413001-4, CRACKED AT AFT BOLT HO	LE FOR PN 20670011-1 RUDDER TORQUE TUBE BEARING ASSYS. LT BULKHEADS WERE FOUND IN WORSE CONDITION THAN RT. ACFT HAS HA	D 1 LANDING WHERE NOSE GEAR FOLDED & IS USED FOR FLT TRAINING. RECOMMEND THOROUGH INSP OF AREA EVERY 100 HRS. UPPER BU	LKHEADS NEED TO BE REINFORCED AT TOP EDGE OF OPENING & STRONGER MTNG FOR RUDDER BEARING BLKS NEEDS TO BE DEVELOPED.	1	H	7	1 	3O				3A17 					 
1995031000585	19950310	00585	CE 	1995	3	10	95ZZZX1094 	1	19950201	G	5312	24130014	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD TORQUE TUBE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	966LA	4133 				172RG1102				FOUND UPPER BULKHEADS CRACKED AT TOP OF RUDDER PEDAL TORQUE TUBE OPENING JUST AFT OF MOUNTING BOLT FOR PN 2460004-1 BELL	CRANK ASSY. LT SIDE CRACKED COMPLETELY THROUGH. RT SIDE ALSO DAMAGED DUE TO BOLT HEAD ON THE BELLCRANK HITTING IT. FO	UND UPPER BULKHEADS, PN 2413001-5 & PN 2413001-8, & LOWER BULKHEADS, PN 2413001-3 & PN 2413001-4, CRACKED AT AFT BOLT HO	LE FOR PN 20670011-1 RUDDER TORQUE TUBE BEARING ASSYS. LT BULKHEADS WERE FOUND IN WORSE CONDITION THAN RT. ACFT HAS HA	D 1 LANDING WHERE NOSE GEAR FOLDED & IS USED FOR FLT TRAINING. RECOMMEND THOROUGH INSP OF AREA EVERY 100 HRS. UPPER BU	LKHEADS NEED TO BE REINFORCED AT TOP EDGE OF OPENING & STRONGER MTNG FOR RUDDER BEARING BLKS NEEDS TO BE DEVELOPED.	1	H	7	1 	3O				3A17 					 
1995031000586	19950310	00586	SO 	1995	3	10	95ZZZX1095 	2	19950201	G	8540		GEAR 			TCRAFT	19 	F19 	9230703	GL 	CONT 	O200 	O200A 	17020	SO 					CRANKSHAFT	FAILED 	D				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			SO	04	20001					F126	255880			ACFT ON LOCAL FLIGHT WHEN ENGINE QUIT AT 1,000 FEET AGL. EMERGENCY LANDING MADE WITH ACFT DAMAGE. INVESTIGATION FOUND 	RT MAG BROKEN AT BASE. BOLTS HOLDING GEAR TO CRANKSHAFT FAILED. STARTER AND CLUTCH FROZEN.					1	H	7	1 	3O	3	O		1A9 	E252				 
1995031000587	19950310	00587	SO 	1995	3	10	95ZZZX1096 	1	19950201	G	3230	025702	FITTING 			PIPER 	PA32 	PA32R301 	7103218	SO 										NLG DRAG LINK	MISMFG 	D	S	A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	13	8473C					32R8213014				WHILE INSTALLING KIT, PN 766-253 TO COMPLY WITH AD 93-05-10 AND SB 955, FOUND THAT WHEN NOSE GEAR WAS FULLY RETRACTED, T	HE INSTALLED FITTING (PN 02570-2) WAS PLACING A STRAIN ON THE SUPPORT ASSY (PN 02867-2) THAT WAS ALSO INSTALLED IN THE K	IT. AFTER CONTACTING PIPER, FOUND THAT SOME OF THE FIRST KITS DELIVERED MAY HAVE HAD A FITTING THAT WAS INCORRECTLY MIL	LED. A NEW FITTING )PN 02570-2) WAS INSTALLED AND THIS CORRECTED THE PROBLEM.			1	L	7	1 	3O				A3SO 					 
1995031000588	19950310	00588	CE 	1995	3	10	95ZZZX1097 	1	19950104	G	2820		LINE 			CESSNA	206 	U206F 	2073333	CE 										TIP TANK FUEL	CORROSION 	C			NZBC	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	05	8295Q	1000 				U20603156				DURING AN ANNUAL INSPECTION OF ACFT, LT WING TIP FUEL TANK (FLINT AERO) FUEL LINE TO TRANSFER PUMP FOUND TO HAVE FUEL ST	AINS IN SEVERAL PLACES & WAS WET TO THE TOUCH. UPON REMOVAL OF FUEL LINE FOR INSP, FOUND SEVERAL PIN HOLES IN AREAS OF 	THE FUEL STAINS & CORROSION WAS PRESENT INSIDE. FLINT AERO NOTIFIED & SAMPLES OF TUBING WHERE THE PIN HOLES WERE FOUND 	WERE SENT TO THEM AT THEIR REQUEST. BOTH LT AND RT WING FUEL LINES FORM THE WING TIP FUEL TANK TO TRANSFER PUMPS WERE R	EPLACED. PART WAS INSTALLED FOR APPROXIMATELY 3 AND ONE-HALF YEARS (AMPH. AIRCRAFT).		1	H	7	1 	3O				A4CE 					 
1995031000589	19950310	00589	CE 	1995	3	10	95ZZZX1098 	1	19950207	G	7160	7110	FILTER 	BRACKETT 		BEECH 	35 	F35 	1151514	CE 										AIR INTAKE	DEFECTIVE 	D				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			EA	09	3896B					D4146				AFTER INSTALLATION OF THE FILTER, NOTICED MANIFOLD PRESSURE ON TAKEOFF WAS 2 INCHES LOWER THAN WITH DONALDSON FILTER SOL	D BY BEECH. ON INSPECTION, DETERMINED THAT THIS DIFFERENTIAL PRESSURE WAS PULLING THE ALTERNATE AIR DOOR INSIDE THE COW	LING OPEN. DOOR BEGAN TO FLUTTER AT FLAT PITCH AND ABOUT 21 INCHES; WAS WIDE OPEN AT 23 INCHES. WITH A NEW SPRING ON T	HE ALTERNATE AIR DOOR, THE RESULT WAS THE SAME.			1	L	7	1 	3O				A777 					 
1995031000590	19950310	00590	SO 	1995	3	10	95ZZZX1099 	2	19950119	G	8530	639272CP	CYLINDER 			BEECH 	55 	D55 	1152730	CE 	CONT 	O520 	IO520CB 	17032	SO 					EXHAUST PORT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	69RP					TE766	243621R			DURING A 200-HOUR INSPECTION ALL CYLINDERS OF LT ENGINE PASSED A DIFFERENTIAL COMPRESSION TEST. CLOSER INSPECTION OF CL	YLINDER ASSYS REVEALED CRACKS BETWEEN COOLING FINS OF SEVERAL CYLINDERS IN THE EXHAUST PORT AREA. NOTE: CRACKS ORIGINA	TING IN THIS AREA ARE NOT CHECKED DURING COMPRESSION TEST AND WILL LEAD TO CYLINDER HEAD SEPARATION IN 100 HOURS OR LESS	. SUSPECT FATIGUE/SHOCK COOLING.			1	L	7	2 	3O	3	O		3A16 	E5CE				 
1995031000591	19950310	00591	CE 	1995	3	10	95ZZZX1100 	1	19950207	G	5312	511201123	BULKHEAD 			CESSNA	402 	402CESSNA 	207590K	CE 										LOWER AFT	CRUSHED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	4046Q	5800 				4020146				DURING A ROUTINE INSPECTION, NOTICED TAIL TIE-DOWN HOOK BROKEN AND SKIN CRUSHED IN THE SAME AREA. THIS CONDITION WAS CA	USED DURING LOADING FREIGHT AND ACFT FALLING ON TAIL. THE CRUSHED REAR BULKHEAD CONTAINS A LIGHTENING HOLE FOR THE ELEV	ATOR BELLCRANK AND PUSH/PULL TUBE. SLIGHTLY MORE DAMAGE WOULD HAVE INTERFERRED WITH ELEVATOR TRAVEL. SUBMITTER RECOMME	NDS OPERATOR NOTIFICATION AND POSSIBLE PLACARD IN THIS AREA.			1	L	7	2 	3O				A7CE 					 
1995031000592	19950310	00592	EA 	1995	3	10	95ZZZX1101 	2	19950201	G	7414	10682016	DISTRIBUTOR GEAR	BENDIX 	D6LN3000 	CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540J3C5 	41532	EA 					MAG	TEETH STRIPPED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	4949S	157 			3070356	R18201488	L2110340A			ACFT WAS FLOWN ON THE PREVIOUS EVENING. NO PROBLEMS NOTED. NEXT MORNING, ACFT WOULD NOT START. AFTER TROUBLESHOOTING 	ACFT, FOUND MAGNETO PROBLEMS UPON DISASSEMBLY OF MAG. BOTH DISTRIBUTOR GEARS WERE SEVERELY DAMAGED (TEETH WERE STRIPPED	 FROM BOTH GEARS). A NEW MAG WAS INSTALLED AND NO OTHER PROBLEMS WERE ENCOUNTERED. ACFT WAS RELEASED FOR SERVICE.				1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1995031000593	19950310	00593	CE 	1995	3	10	95ZZZX1102 	1	19950127	G	5521	1236232	BRACKET 			CESSNA	210 	T210N 	2073456	CE 										HORIZ STABILIZER	CRACKED 	H			DVPS	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	4894C	3052 				21063658				WHEN INSPECTING ACCORDING TO CESSNA SB SE 84-17, FOUND 2 CRACKS AT LT BRACKET ATTACHMENT SCREW.						1	H	7	1 	3O				3A21 					 
1995031000594	19950310	00594	CE 	1995	3	10	95ZZZX1103 	1	19950221	G	7922	75944	VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	614PW		199 		25759	M2364				WHILE COMPLYING WITH LYCOMING SB 518A, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. ALSO, FOUND THERMO BELLOWS	 DAMAGED. CRIMP NUT LOOSE DUE TO POOR DESIGN.					1	L	7	1 	3O				A1CE 					 
1995031000595	19950310	00595	SO 	1995	3	10	95ZZZX1104 	2	19950131	G	8540	646209	DAMPENER 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520N 	17032	SO 					ACCESSORY CASE	SEPARATED 	B			ETER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	6794D	730 				421C1030				FOUND METAL IN OIL. FOUND REAR ACCESSORY CASE JOURNAL HOLDING STARTER ADAPTER SHAFT SEVERELY WORN AND WALLOWED OUT. VI	SCOUS DAMPENER SEPARATED FROM HUB.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995031000597	19950310	00597	CE 	1995	3	10	95ZZZX1106 	1	19950223	G	5511	073261110	RIB 			CESSNA	182 	R182 	2072734	CE 										HORIZ STAB	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	3726C	8635 				R18200321				DURING ANNUAL, FOUND LEADING EDGE OF HORIZONTAL STABILIZER HAD SAME MOVEMENT AS 200 SERIES CESSNAS WITH BROKEN RIBS. DI	SASSEMBLY SHOWED THAT 3 RIBS ON RIGHT AND 4 RIBS ON LEFT SIDE WERE BROKEN. REPLACED RIBS AND SKINS.					1	H	7	1 	3O			RT	3A13 					 
1995031000598	19950310	00598	CE 	1995	3	10	95ZZZX1107 	1	19950223	G	5511	07326119	RIB 			CESSNA	182 	R182 	2072734	CE 										HORIZ STAB	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	3726C	8635 				R18200321				DURING ANNUAL, FOUND LEADING EDGE OF HORIZONTAL STABILIZER HAD SAME MOVEMENT AS 200 SERIES CESSNAS WITH BROKEN RIBS. DI	SASSEMBLY SHOWED THAT 3 RIBS ON RIGHT AND 4 RIBS ON LEFT SIDE WERE BROKEN. REPLACED RIBS AND SKINS.					1	H	7	1 	3O			RT	3A13 					 
1995031000599	19950310	00599	CE 	1995	3	10	95ZZZX1108 	1	19950223	G	5511	07326118	RIB 			CESSNA	182 	R182 	2072734	CE 										HORIZ STAB	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	3726C	8635 				R18200321				DURING ANNUAL, FOUND LEADING EDGE OF HORIZONTAL STABILIZER HAD SAME MOVEMENT AS 200 SERIES CESSNAS WITH BROKEN RIBS. DI	SASSEMBLY SHOWED THAT 3 RIBS ON RIGHT AND 4 RIBS ON LEFT SIDE WERE BROKEN. REPLACED RIBS AND SKINS.					1	H	7	1 	3O			RT	3A13 					 
1995031000600	19950310	00600	CE 	1995	3	10	95ZZZX1109 	1	19950223	G	5511	07326117	RIB 			CESSNA	182 	R182 	2072734	CE 										HORIZ STAB	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	3726C	8635 				R18200321				DURING ANNUAL, FOUND LEADING EDGE OF HORIZONTAL STABILIZER HAD SAME MOVEMENT AS 200 SERIES CESSNAS WITH BROKEN RIBS. DI	SASSEMBLY SHOWED THAT 3 RIBS ON RIGHT AND 4 RIBS ON LEFT SIDE WERE BROKEN. REPLACED RIBS AND SKINS.					1	H	7	1 	3O			RT	3A13 					 
1995031000601	19950310	00601	NM 	1995	3	10	95ZZZX1110 	1	19950201	G	3250		BRACKET 			PROPJT	200 	200B 	0140306	NM 										NLG STEERING	BENT 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	229RS	2265 				280				NOSE GEAR STEERING BRACKET BENT UPWARDS AT ATTACH EARS. BELIEVE CAUSED BY IMPROPER GROUND HANDLING. RECOMMEND INSPECTI	ON ANY TIME NOSE WELL IS LOOKED AT, OR COMPLAINT OF HARD STEERING BY RUDDER PEDALS.					1	L	7	1 	3O				3A18 					 
1995031000602	19950310	00602	SO 	1995	3	10	95ZZZX1111 	1	19950213	G	3230	502341	BOLT 			PIPER 	PA44 	PA44180 	7104402	SO 										NLG DOWNLOCK	SEVERED 	B			OG5R	O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			GL	21	852ND	3545 				4495006				NOSE GEAR DID NOT INDICATE LOCKED ACFT LANDED. MAINTENANCE DETERMINED VISUALLY LOCKNUT ENGAGED DUE TO SHEARED BOLT. AL	SO FOUND BUSHING PN 95061-191 SEIZED TO BOLT. INSTALLED NEW BOLT/BUSHING.					1	L	7	2 	3O				A19S0 					 
1995031000603	19950310	00603	CE 	1995	3	10	95ZZZX1112 	1	19950125	G	5711	082260040	SPAR 		562010019 	CESSNA	340 	340CESSNA 	2076404	CE 										RT WING AFT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5859M					3400057				RIGHT WING AFT SPAR AT ATTACH POINT CORRODED. SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS AREA THROUGH WHEELWELLS AT EA	CH 100-HOUR OR ANNUAL. REMEMBER, THESE ACFT ARE GETTING OLD. THE TIME ON THE SPAR IS BETWEEN 4-6,000 HOURS.					1	L	7	2 	3O				3A25 					 
1995031000604	19950310	00604	SO 	1995	3	10	95ZZZX1113 	1	19950220	G	5753	400680	BOLT 			PIPER 	PA32 	PA32300 	7103212	SO 										FT FLAP	WRONG PART 	B			MJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	6868D	4559 				3240608				UPON INSPECTING AIRCRAFT DURING 100-HOUR INSPECTION, RIGHT FLAP GAVE WAY, THEN, DETERMINED THE ATTACHMENT HARDWARE WAS N	OT CORRECT PER PARTS MANUAL. REINSTALLED CORRECT PARTS WHICH CURED THE PROBLEM. REPLACED WITH 'AN' BOLT PER SB.					1	L	7	1 	3O				A3SO 					 
1995031000605	19950310	00605	SO 	1995	3	10	95ZZZX1114 	2	19950218	G	8530		ROCKER BOSS 			CESSNA	150 	150L 	2071826	CE 	CONT 	O200 	O200A 	17020	SO 					ENGINE CYLINDER	FAILED 	D				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			SW	17	3XZ		336 			15074013	72IABKA48			CYLINDER EXHAUST AND INTAKE VALVE ROCKER BOSSES SEPARATED DURING FLIGHT RESULTING IN PRECAUTIONARY LANDING DUE TO LOSS O	F ENGINE POWER. CYLINDER REPLACED AND AIRCRAFT RETURNED TO SERVICE. REF. AD 94-05-05.					1	H	7	1 	3O	3	O		3A19 	E252				 
1995031000606	19950310	00606		1995	3	10	95ZZZX1115 	2	19950221	G	7414	ES10382788	WASHER 	BENDIX 	D6LN2031 															MAG	DEFECTIVE 	B			KC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03					R7050544K					THESE WASHERS ARE TO SEAL THE CAP SCREWS THAT HOLD THE DRIVE BEARING RETAINER. THE WASHERS FROM ELECTROSYSTEM ARE IMPRO	PERLY HEAT TREATED AND ARE TOO HARD. THEY DO NOT SEAL PROPERLY AND SOMETIMES ALLOW ENGINE OIL TO LEAK INTO MAGNETO.																		 
1995031000607	19950310	00607		1995	3	10	95ZZZX1116 	2	19950221	G	7414	ES103825881	COIL 	BENDIX 	D6LN2031 															MAG	CRACKED 	B			KC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03					R7050544K					THIS MAGNETO WAS OVERHAULED BY ELECTRO SYSTEMS, INC., IN 1987. AT THAT TIME, ELECTRO SYSTEMS AFTERMARKET COILS WERE INS	TALLED. UPON DISASSEMBLY FOR OVERHAUL, DISCOVERED THE COIL WAS CRACKED IN SEVERAL PLACES.																		 
1995031000608	19950310	00608	SO 	1995	3	10	95ZZZX1117 	2	19950118	G	7324	63432610A9	FLOW DIVIDER 			CESSNA	402 	402B 	207590P	CE 	CONT 	O520 	TSIO520E 	17040	SO 					ENGINE FUEL	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	535A		175 			402B0591	20650271E			PILOT REPORTED LT ENGINE WOULD NOT MAKE A CLEAN SHUT DOWN. INVESTIGATION REVEALED FLOW DIVIDER CHECK VALVE WAS PASSING 	FUEL BELOW PRESET PRESSURE. FOUND RUBER DIAPHRAGM DRIED OUT DUE TO LACK OF USE.					1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995031000609	19950310	00609	SO 	1995	3	10	95ZZZX1118 	2	19950119	G	7322	6462122	FUEL PUMP 			BEECH 	33 	F33A 	1151425	CE 	CONT 	O520 	IO520BA 	17032	SO 					ENGINE	FAILED 	C				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			SW	07	1096W		65 			CE436	569112			ENGINE LOST POWER WHEN REDUCED FOR DESCENT. EFFORTS TO RESTART ENGINE FAILED. AIRCRAFT MADE AN UNEVENTFUL OFF AIRPORT 	LANDING. AFTER AIRCRAFT SAT, ENGINE WAS ABLE TO BE RESTARTED. PUMP WAS REMOVED AND SENT OUT FOR CHECK. MULTIPLE DISCR	EPANCIES WERE FOUND IN VALVE SEAT ALIGNMENT CAUSING ENGINE TO RUN RICH ON POWER REDUCTION. UNIT OVERHAULED LESS THAN 10	0 HOURS PRIOR BY CRS RV3R829L.			1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995031000610	19950310	00610		1995	3	10	95ZZZX1119 	2	19950131	G	7414	ES103571651	COIL 	BENDIX 	S6200 															MAG	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	17										INSTALLED NEW COIL IN BENDIX MAG -- COIL FAILED AFTER 1.6 HOURS OF FLIGHT TIME.																			 
1995031000612	19950310	00612	CE 	1995	3	10	95ZZZX1121 	1	19950131	G	3213	05411241	AXLE 			CESSNA	182 	TR182 	2072735	CE 										MLG	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	736ER	2559 				R18200725				DURING ANNUAL INSPECTION, FOUND BOTH MAIN GEAR AXLES CORRODING. THE LEFT AXLE WAS EXFOLIATING. REPLACED BOTH AXLES.						1	H	7	1 	3O				3A13 					 
1995031000613	19950310	00613	CE 	1995	3	10	95ZZZX1122 	1	19950201	G	3250	1243405200	SHAFT 			CESSNA	210 	210D 	2073414	CE 										NLG STEERING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	524BL	5300 				21058477				NOSE GEAR STEERING SHAFT ASSY CRACKED 75 PERCENT AROUND AT HOLE FOR SHIMMEY DAMPENER ARM ROLL PIN. CRACK NOT VISIBLE UN	TIL PART WAS COMPLETELY REMOVED. ONLY EVIDENCE OF PROBLEM WAS LOOSE ROLL PIN. SUBMITTER RECOMMENDS REGULAR INSPECTION 	OF ROLL PINS FOR LOOSENESS.				1	H	7	1 	3O				3A21 					 
1995031000614	19950310	00614		1995	3	10	95ZZZX1123 	4	19950215	G	2562	ELT10	ELT 	NARCO 		GULSTM	AA5 	AA5B 	3960105	SO 										BATTERY CONNECT	DEFECTIVE 	B			IG1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	23	28464					AA5B0629				ELT BATTERY REMOVED FROM CALENDAR TIME REPLACEMENT. ELT WOULD NOT HAVE FUNCTIONED SINCE THE BATTERY WIRES WERE NOT CONN	ECTED TO THE TRANSMITTER.					1	L	7	1 	3O				A16EA 					 
1995031000615	19950310	00615		1995	3	10	95ZZZX1124 	4	19950206	G	3416	3431	CASTING 	UNITEDINST 	5934P1 	CESSNA	172 	172RG 	2072438	CE 										ALTIMETER	CREEP 	B			EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	9615B				H7013	172RG0920				WHEN THIS INSTRUMENT WAS TESTED, NOTICED IT OPERATED WITH HESITATIONS OF 100 FEET TO 150 FEET WHEN TESTED FROM MINUS 1,0	00 FEET TO 20,000 FEET. ONE HESITATION WHICH OCCURRED AT APPROX 250 FEET HAD A HESITATION OF APPROX 220 FEET DURING WHI	CH IT SLOWLY CAME TO THE PROPER ALTITUDE POSITION. ON DISASSEMBLY, DISCOVERED THERE WAS A VERY TENACIOUS GREASE ON THE 	JEWEL BEARING SURFACES. THIS GREASE COULD NOT BE WIPED OFF EASILY AND HAD TO BE SCRAPED OFF WITH PEG WOOD. THE SHAFT E	ND-SHAKES WERE UNDER THE SPEC TOLERANCE. THEY MEASURED .0007 INCH, .0012 INCH & .0012 INCH. THE P.D.C. FAA APPROVED MO	DIFICATION INCLUDES A STRUT THAT STABILIZES THE MECH. CASTING.	1	H	7	1 	3O				3A17 					 
1995031000617	19950310	00617	GL 	1995	3	10	95ZZZX1126 	3	19950131	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	PROP	CRACKED 	G				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			GL	19	94101	6581 				15285597		BG086		PILOT REPORTED ENGINE RUNNING ROUGH. UPON REMOVING PROP SPINNER, THE FORWARD SPINNER BULKHEAD WAS FOUND CRACKED. FURTH	ER INSPECTION REVEALED THE PROP HUB WAS COMPLETELY CRACKED THROUGH, FORE TO AFT, IN IRREGULAR PATTERN BEGINNING AT ONE B	OLT HOLE ON AFT SIDE OF HUB TO FACE OF HUB. PROP TRACK CHECKED OKAY. AD 89-26-10 AND SB 169B HAD BEEN DONE AT 3727.6 H	RS/9-13-89.			1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995031000618	19950310	00618		1995	3	10	95ZZZX1127 	4	19950131	G	6113		SPINNER 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	PROP	CRACKED 	G				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			GL	19	94101	6581 				15285597		BG086		PILOT REPORTED ENGINE RUNNING ROUGH. UPON REMOVING PROP SPINNER, THE FORWARD SPINNER BULKHEAD WAS FOUND CRACKED. FURTH	ER INSPECTION REVEALED THE PROP HUB WAS COMPLETELY CRACKED THROUGH, FORE TO AFT, IN IRREGULAR PATTERN BEGINNING AT ONE B	OLT HOLE ON AFT SIDE OF HUB TO FACE OF HUB. PROP TRACK CHECKED OKAY. AD 89-26-10 AND SB 169B HAD BEEN DONE AT 3727.6 H	RS/9-13-89.			1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995031000619	19950310	00619	CE 	1995	3	10	95ZZZX1128 	1	19950207	G	2410		BRACKET 			CESSNA	172 	172M 	2072418	CE 										AFT BOLT HOLE	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	1918V	3608 				17263794				ALTERNATOR CIRCUIT BREAKER TRIPPED. WIRE WAS SHORTING ON BACKSIDE OF THE ALTERNATOR. AFTER REMOVAL OF ALTERNATOR, FOUN	D BRACKET BOLTED TO THE BOTTOM FRONT RIGHT OF THE ENGINE WAS BROKE IN TWO AT THE REAR BOLT HOLE. THE ALTERNATOR SEEMED 	SECURE BEFORE REMOVAL. RECOMMEND TO THOROUGHLY CLEAN THE BRACKET AREA OF ALL GREASE AND DIRT AND CHECK THE THROUGH-BOLT	 FOR SECURITY.			1	H	7	1 	3O			NT	3A12 					 
1995031000620	19950310	00620	SO 	1995	3	10	95ZZZX1129 	2	19950206	G	7322		ENGINE 			CESSNA	150 	150M 	2071830	CE 	CONT 	O200 	O200A 	17020	SO 					CARB	RAN ROUGH 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			GL	13	501PA		1772 			15077482	275920R			AD 93-18-03 AND PRECISION AIRMOTIVE SB NR MSA-2 R1, WAS DONE ON THIS CARB. AT 1521 HRS SMOH WHICH IS THE SINGLE PIECE VE	NTURI. IT WAS DONE BY A REPAIR STATION. AT 1771 HRS SMOH, ENGINE BEGAN TO RUN EXTREMELY ROUGH. OAT WAS ABOUT 27 DEGRE	ES FAHRENHEIT. INVESTIGATION FOUND OUT THAT IF SINGLE PIECE VENTURI WAS INSTALLED AND ENGINE RAN ROUGH, IT NEEDED A DIF	FERENT METERING NOZZLE, KIT PN 666-942. THIS WAS DONE AND IT RAN FINE. SUBMITTER SUGGESTS IF SINGLE PIECE VENTURI IS I	NSTALLED, THAT CHANGING THE FUEL NOZZLE IS A MUST. IT IS COVERED IN SB MSA-2.		1	H	7	1 	3O	3	O		3A19 	E252				 
1995032000051	19950320	00051	GL 	1995	3	20	95ZZZX1133 	2	19950223	G	7250	6890040	SHIELD 		6898735 	HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					NR 1 NOZZLE	CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y		961 		479130R	500716D	CAE832750			DURING REPLACEMENT OF NR 1 NOZZLE, NOZZLE SHIELD WAS FOUND CRACKED. PART REPLACED AND SENT IN FOR OVERHAUL.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995032000052	19950320	00052	GL 	1995	3	20	95ZZZX1134 	2	19950223	G	7250	6895021	NOZZLE 		6898735 	HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					NR 1 TURBINE	CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y		961 		C145814	500716D	CAE832750			NR 1 TURBINE NOZZLE REPLACED DUE TO TRAILING EDGE CRACKING BEYOND LIMITS. UPON REMOVAL, DISCOVERED THE 6823481-7000 ROP	E PACKING MISSING. NO INDICATIONS OF POWER LOSS OR TOT RISE. PART RETURNED FOR OVERHAUL.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995032000054	19950320	00054	CE 	1995	3	20	95ZZZX1136 	1	19950215	G	3040	57033	MOTOR 			CESSNA	500 	550 	2076604	CE 										DE FOG BLOWER	BURNED 	H				O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			CL	CLIMB 	1			SO	15	120HC	2596 				5500577				ON CLIMB OUT THROUGH 14,000 FEET, SMELLED SMOKE IN COCKPIT. SMELL IS EVIDENT THROUGHOUT THE CABIN. FOUND ELECTRIC MOTO	R ON COCKPIT DEFOG BLOWER HAD BURNED OUT.					1	L	7	2 	4F				A22CE 					 
1995032000056	19950320	00056	GL 	1995	3	20	95ZZZX1138 	2	19950221	G	7230	23007217	MOUNT ASSY 								ALLSN 	250C 	250C30P 	03013	GL 					COMPRESSOR	MISMANUFACTURED 	B			UP9R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	07		1177 	821 				CAE895130			MOUNT FACE TO MOUNT BOSS HEIGHT LIMITS ARE 1.715 INCHES TO 1.707 INCHES IN THE O/H MANUAL. THIS MOUNT MEASURED 1.770 IN	CHES TO 1.730 INCHES. THE MISALIGNMENT DAMAGED THE SPUR ADAPTER, GEAR SHAFT, COUPLING ADAPTER, AND IMPELLER BORE.										3	U			E1GL				 
1995032000057	19950320	00057	WP 	1995	3	20	95ZZZX1139 	2	19950222	G	7250	3101512	BLADE 		31016031 	MTSBSI	MU2 	MU2B60 	5780460	CE 	GARRTT	TPE331	TPE33110 	01514	WP 					1ST STAGE	FAILED 	B			DQIR	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			J			WARNING INDICATION 			TO	TAKEOFF 	1			NM	07	132BK	6530 			90350120012	1529A	P36236			DURING TAKEOFF POWER APPLICATION, LT ENGINE DEVELOPED HIGHER THAN NORMAL ITT. THE ENGINE WAS VISUALLY INSPECTED AND WAS	 FOUND TO HAVE EJECTED INTERNAL PARTS FROM THE TAILPIPE. TEAR DOWN INSPECTION REVEALED CAUSE TO HAVE BEEN GENERATED FRO	M ONE FIRST STAGE TURBINE BLADE FAILURE. BLADE TSN, 6529.8 - CSN 6988.				1	H	7	2 	3T	4	T	RT	A10SW 	E4WE				 
1995032000058	19950320	00058	CE 	1995	3	20	95ZZZX1140 	1	19950217	G	7830	216821	SWITCH 	ROHR 		CESSNA	500 	560CESSNA 	2076750	CE 										THRUST REV	MISMANUFACTURED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	03	50LT					5600153				NEW SWITCHES MANUFACTURED BY TEXAS INSTRUMENTS FOR INSTALLATION ON ROHR T/R'S ARE POTTED INCORRECTLY FOR THIS INSTALLATI	ON. THE NEW SWITCH MUST BE TRIMMED AND REROUTED IN ORDER FOR PROPER CLERANCE WITH STANG.					2	L	7	2 	4F			RT	A22CE 					 
1995032000059	19950320	00059	SW 	1995	3	20	95ZZZX1141 	1	19950217	G	2730	2744046033	QUADRANT 		2744046037 	SWRNGN	SA227 	SA227AC 	8780603	SW 										ELEV CONTROL	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	57NE	9643 				AC757B				WHILE REPLACING PRIMARY CONTROL CABLES PER AD 87-02-02, THE UPPER CONTROL STOPS WERE REMOVED FROM THE ELEVATOR CONTROL Q	UADRANT. AFTER REMOVAL, THE QUADRANT CASTING WAS FOUND SEVERELY CORRODED AND ELONGATED AT UPPER STOP BOLT HOLE. SUBSTA	NTIAL CASTING MATERIAL WAS ERODED AWAY AT THIS LOCATION.				1	L	7	2 	4T				A8SW 					 
1995032000060	19950320	00060	CE 	1995	3	20	95ZZZX1142 	1	19950210	G	3250	42022SA104	PC BOARD 			LEAR 	24 	24 	5170302	CE 										NLG STEERING	DEFECTIVE 	B			DELR	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			CE	03	124JL				2422	24127				AIRCAFT TT 11,018.1 HRS, LANDINGS 10,996. FOUND NOSE STRUT UNDER-INFLATED AND NOSE STEERING DOES NOT CENTER. AFTER TAK	EOFF, HAD 'UNSAFE GEAR' LIGHT ON NOSE GEAR. REPLACED THE BAD NOSE STEERING, FOLLOW-UP WITH O/H PART, AND NOSE STEERING 	PRINTED CIRCUIT BOARD WITH REPAIRED PART. SERVICED NOSE STRUT PROPERLY. REPLACED NOSE TIRE WITH NEW TIRE (NOSE WHEEL A	SSY WAS O/H). GEAR RETRACTION. LEAK CHECKED, AND OPS CHECKED OKAY.			2	L	7	2 	4J				A10CE 					 
1995032000061	19950320	00061	CE 	1995	3	20	95ZZZX1143 	1	19950210	G	3250	23800777	FOLLOW UP 			LEAR 	24 	24 	5170302	CE 										NLG STEERING	DEFECTIVE 	B			DELR	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			CE	03	124JL				847	24127				AIRCAFT TT 11,018.1 HRS, LANDINGS 10,996. FOUND NOSE STRUT UNDER-INFLATED AND NOSE STEERING DOES NOT CENTER. AFTER TAK	EOFF, HAD 'UNSAFE GEAR' LIGHT ON NOSE GEAR. REPLACED THE BAD NOSE STEERING FOLLOW-UP WITH O/H PART, AND NOSE STEERING P	RINTED CIRCUIT BOARD WITH REPAIRED PART. SERVICED NOSE STRUT PROPERLY. REPLACED NOSE TIRE WITH NEW TIRE (NOSE WHEEL AS	SY WAS O/H). GEAR RETRACTION. LEAK CHECKED, AND OPS CHECKED OKAY.			2	L	7	2 	4J				A10CE 					 
1995032000062	19950320	00062	CE 	1995	3	20	95ZZZX1144 	1	19950124	G	5711		SPAR 			BEECH 	200 	200BEECH 	1152920	CE 										RT WING	DAMAGED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	01	979SR					BB519				WHILE PERFORMING 5-YEAR WING BOLT INSPECTION, NOTED FORWARD LOWER RT WING BOLT/NUT WAS INSTALLED BACKWARDS. LOGBOOKS RE	VEALED BOLT INSTALLED 5 YEARS PREVIOUSLY BY A BEECH SERVICE CENTER AND TORQUE CHECKED AT ANOTHER BEECH SERVICE CENTER AN	D NUMEROUS 150-HOUR INSPECTIONS ACCOMPLISHED WTHOUT BEING DETECTED. UPON REMOVAL, SPAR FITTING FOUND DAMAGED (REMOVAL O	F BOLT CAUSED A WRENCH TO BE BROKEN AND BOLT HAD TO BE WRENCHED ALL THE WAY OUT OF FITTING DUE TO EXCESSIVE PRESSURE ON 	FITTING). ACFT FERRIED TO VNY FOR SPAR REPLACEMENT.		1	L	7	2 	4T				A24CE 					 
1995032000063	19950320	00063	CE 	1995	3	20	95ZZZX1145 	1	19950124	G	5711	80691CF1612	NUT 			BEECH 	200 	200BEECH 	1152920	CE 										RT WING BOLT	MISINSTALLED 	D	P			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	01	979SR					BB519				WHILE PERFORMING 5-YEAR WING BOLT INSPECTION, NOTED FORWARD LOWER RT WING BOLT/NUT WAS INSTALLED BACKWARDS. LOGBOOKS RE	VEALED BOLT INSTALLED 5 YEARS PREVIOUSLY BY A BEECH SERVICE CENTER AND TORQUE CHECKED AT ANOTHER BEECH SERVICE CENTER AN	D NUMEROUS 150-HOUR INSPECTIONS ACCOMPLISHED WTHOUT BEING DETECTED. UPON REMOVAL, SPAR FITTING FOUND DAMAGED (REMOVAL O	F BOLT CAUSED A WRENCH TO BE BROKEN AND BOLT HAD TO BE WRENCHED ALL THE WAY OUT OF FITTING DUE TO EXCESSIVE PRESSURE ON 	FITTING). ACFT FERRIED TO VNY FOR SPAR REPLACEMENT.		1	L	7	2 	4T				A24CE 					 
1995032000064	19950320	00064	NE 	1995	3	20	95ZZZX1146 	2	19950209	G	7261	310426501	OIL PUMP 			CESSNA	500 	550 	2076604	CE 	PWA 	JT15 	JT15D4 	52112	NE 					ENGINE	FAILED 	B	L		YRRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	75HS	3958 	446 			550256	PCE70754			THE ENGINE WAS DISASSEMBLED TO DETERMINE THE REASON FOR THE REPORTED PROBLEMS. DISASSEMBLY OF THE OIL PUMP ASSEMBLY REV	EALED THE POST SB 7185 PLATE HAD BECOME WELDED TO THE SCAVENGE ELEMENT CAUSING IT TO SHEAR THE SHAFT DRIVE PIN. THIS FA	ILURE CAUSED FLOODING OF THE NR 4 BEARING CAVITY, ULTIMATELY RESULTING IN AN OIL FIRE AT THE NR 4 BEARING AREA.				1	L	7	2 	4F	4	F		A22CE 	E1NE				 
1995032000065	19950320	00065	CE 	1995	3	20	95ZZZX1147 	1	19950105	G	3222		SET SCREWS 		664200010 	CESSNA	500 	560CESSNA 	2076750	CE 										NLG STRUT	TIP SHEARED 	B	L		UJJR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	561B	1555 			9	5600008				DURING NLG STRUT DISASSEMBLY FOR REPACK, FOUND UPPER BEARING COULD BE TURNED BY HAND AND WAS UNTHREADED BY 2 TURNS. SET	 SCREWS WERE TIGHT, BUT FOUND TIPS SHEARED.					2	L	7	2 	4F			RT	A22CE 					 
1995032000066	19950320	00066	SO 	1995	3	20	95ZZZX1148 	2	19950112	G	8530		CYLINDERS 			BEECH 	36 	A36TC 	1151603	CE 	CONT 	O520 	TSIO520UB 	17040	SO 					ROCKER SHAFT	EXCESS WORN 	B			CCAR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	48PD	581 				EA75	515609			FACTORY NEW CYLINDERS TT 581.4 HOURS. INSTALLED 2-1-91, LOW COMPRESSION ALL CYLINDERS. CYLINDERS ARE WORN BEYOND SERVI	CEABLE LIMITS AND HAVE SEVERE RING WEAR. ROCKER SHAFTS ARE SEVERELLY WORN AND UNAIRWORTHY.					1	L	7	1 	3O	3	O		3A15 	E8CE				 
1995032000067	19950320	00067	SO 	1995	3	20	95ZZZX1149 	2	19950203	G	8520		CAMSHAFT 			CESSNA	402 	402A 	207590M	CE 	CONT 	O520 	TSIO520E 	17040	SO 					GEAR END	BROKEN 	G				O				OTHER 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			GL	19	4584Q	71 				402A0084	183466R			IN-FLIGHT ENGINE SHUT DOWN. CHECKED PROBLEM AND FOUND NO MOVEMENT IN VALVE TRAIN, ETC., WHEN PROP MOVED. PULLED ENGINE	 AND SENT BACK TO OVERHAUL AGENCY. VERIFIED UPON DISASSEMBLY THAT CAMSHAFT WAS BROKEN NEAR GEAR END.					1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995032000068	19950320	00068	CE 	1995	3	20	95ZZZX1150 	1	19950216	G	3230	92467	RESTRICTOR VALVE	GARKENYON 	ADI7999003 	BEECH 	200 	200BEECH 	1152920	CE 										MLG	SCREEN FAILED 	B	S	A	LX5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	981LL	4605 			ADI204B	BB602				THIS UNIT IS PART OF STC SA 4378WP AVIDESIGN, INC., HYDRAULIC LANDING GEAR SYSTEM. SCREENS DISLODGED ENTERING MAIN ACTU	ATOR. NOTE: THIS IS FOURTH SUCH INCIDENT.					1	L	7	2 	4T				A24CE 					 
1995032000069	19950320	00069	CE 	1995	3	20	95ZZZX1151 	1	19950216	G	7922	75944	VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	6626D		701 		109453	M2179				WHILE COMPLYING WITH LYCOMING SB 518, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. SUBMITTER SUGGESTS CRIMP NU	T LOOSE DUE TO POOR DESIGN.					1	L	7	1 	3O				A1CE 					 
1995032000070	19950320	00070	SO 	1995	3	20	95ZZZX1152 	1	19950207	G	7922	75944	VALVE 			PIPER 	PA28 	PA28236 	7102815	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	8384Y	1848 				288111072				INSPECTION PER LYCOMING SB 518. PHYSICAL INSPECTION OF CRIMP NUT FOUND LOOSE ON THE THERMOSTATIC BYPASS VALVE, PN 75944	, PART REPLACED.					1	L	7	1 	3O				2A13 					 
1995032000071	19950320	00071	SO 	1995	3	20	95ZZZX1153 	1	19950201	G	7922	53E19600	VERNATHERM 			PIPER 	PA31 	PA31325 	7103105	SO 										OIL TEMP REG	CRIMP NUT FAILED	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	27975	1790 				317912047				DURING ENGINE OVERHAUL (TBO), VERNATHERM WAS REMOVED AND FOUND WITH NUT MISSING. SEAT AND SPRING WERE FOUND WITH REST O	F THE PART, NUT WAS FOUND IN OIL COOLER. SUGGEST POSSIBLE REMEDY WOULD BE TO NOT CRUSH THE NUT, BUT TO USE A 'COTTER PI	N' OR 'ROLL PIN'. ON CURRENT DESIGN, IT COCKS WHEN NUT IS CRUSHED. THE THREADS ARE PULLED AWAY FROM SHAFT, THUS, LESS 	GRIP. THIS IS THE SECOND OCCURRENCE ON THIS SAME AIRCRAFT. THE OTHER ENGINE M OR D WAS PREVIOUSLY SUBMITTEDAND APPEARE	D IN THE JANUARY, 1995 AC 43-16 ALERT NR 198.		1	L	7	2 	3O				A20SO 					 
1995032000077	19950320	00077	EA 	1995	3	20	95ZZZX1159 	2	19950220	G	7414	ES103910881	COIL 	ELECTROSYS 	103493653 	PIPER 	PA34 	PA34200 	7103405	SO 	LYC 	O360 	LIO360C1E6 	41515	EA 					MAGNETO	CRACKED 	B			QKKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01					0110063					DURING INSPECTION PER CUSTOMER INSTRUCTIONS, COIL CRACK WAS NOTED. REMOVED AND TESTED COIL. FOUND HIGH VOLTAGE LEAK OU	T FROM CRACK. SUSPECT CAUSE MAY BE FROM MANUFACTURE DATE STAMP IN INSULATION. CRACK LOCATION ABOUT 1 INCH FROM OUTPUT 	TAB.				1	L	7	2 	3O	3	O		A7SO 	1E10				 
1995032000078	19950320	00078	SO 	1995	3	20	95ZZZX1160 	1	19950111	G	2140	4022161	STABILIZER 			AYRES 	S2 	S2RNORMAL 	7630202	SO 										HORIZ STABILIZER	MISMANUFACTURED 	B		A	YDYR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	15	3100N	2243 				T65003DC				WHILE COMPLYING WITH SB-AG-37 (HORIZ STABILIZER SPAR) 6 RIBS IN THE LEADING EDGE WERE FOUND TO HAVE IMPROPERLY SHOT RIVE	TS WHICH COULD BE SEEN AS SMOKING RIVITS. RIVETS WERE FOUND SPACED TO CLOSE TO EDGE, WRONG GRIP LENGTHS, DOUBLE DRILLED	 HOLES; HOLES DRILLED INTO RADIUS OF RIB, DOUBLE DRILLED FIGURE 8 HOLE DRILLED INTO THE FWD SPAR. ALL DAMAGE PHOTOGRAPH	ED AND AVAILABLE AT THE REPAIR STATION.			1	L	7	1 	3R			NC	A3SW 					 
1995032000079	19950320	00079	SO 	1995	3	20	95ZZZX1161 	1	19950111	G	5531	5403067	STABILIZER 			AYRES 	S2 	S2RNORMAL 	7630202	SO 										VERT FWD SPAR	MISMANUFACTURED 	B		A	YDYR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	15	3093M	3744 	3215 			T41X				WHILE COMPLYING WITH SB 37 AND SB 38 ON THE HORIZONTAL AND VERTICAL STABILIZERS, FOUND THE VERTICAL STABILIZER FORWARD S	PAR WAS INCORRECTLY INSTALLED DURING MANUFACTURE. EIGHTY-FIVE PERCENT OF RIVETS WERE KEY HOLED. THE HORIZONTAL HAD ONE	 LEADING EDGE RIB WITH ONLY 20 PERCENT OF THE RIVETS SHOT INTO THE RIB. ALL FORWARD RIBS HAD NUMEROUS RIVETS INCORRECTL	Y BUCKED. ALL STATE DEPARTMENT AIRCRAFT HAVE BEEN GROUNDED AND A ONE-TIME INSPECTION AND REPAIR IS ONGOING. ALL DAMAGE	 HAS BEEN VIDIO TAPED AND A COPY IS AVAILABLE AT THE REPAIR STATION.		1	L	7	1 	3R			NC	A3SW 					 
1995032000080	19950320	00080	SO 	1995	3	20	95ZZZX1162 	1	19950111	G	5531	4022161	STABILIZER 			AYRES 	S2 	S2RNORMAL 	7630202	SO 										HORZ STAB LE RIB	MISMANUFACTURED 	B			YDYR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	15	3093M	3744 	3215 			T41X				WHILE COMPLYING WITH SB 37 AND SB 38 ON THE HORIZONTAL AND VERTICAL STABILIZERS, FOUND THE VERTICAL STABILIZER FORWARD S	PAR WAS INCORRECTLY INSTALLED DURING MANUFACTURE. EIGHTY-FIVE PERCENT OF RIVETS WERE KEY HOLED. THE HORIZONTAL HAD ONE	 LEADING EDGE RIB WITH ONLY 20 PERCENT OF THE RIVETS SHOT INTO THE RIB. ALL FORWARD RIBS HAD NUMEROUS RIVETS INCORRECTL	Y BUCKED. ALL STATE DEPARTMENT AIRCRAFT HAVE BEEN GROUNDED AND A ONE-TIME INSPECTION AND REPAIR IS ONGOING. ALL DAMAGE	 HAS BEEN VIDIO TAPED AND A COPY IS AVAILABLE AT THE REPAIR STATION.		1	L	7	1 	3R			NC	A3SW 					 
1995032000081	19950320	00081	EA 	1995	3	20	95ZZZX1163 	2	19950206	G	8540	71667	LOCK PLATE 			PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	IO540C1B5 	41532	EA 					IDLE GEAR	FAILED 	D				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			Y			ENGINE STOPPAGE 			CR	CRUISE 	1			SO	03	6792Y					274130	L526048			DURING PART 91 OPERATION, LEFT ENGINE QUIT RUNNING AND PILOT FEATHERED PROP AND LANDED AT AIRPORT. INSPECTION FOUND LOC	K TAB FOR BOLT ON IDLE GEAR HAD BROKEN OFF AND BOLT BACKED OUT AND ENGINE JUMPED TIME AND QUIT.					1	L	7	2 	3O	3	O		1A10 	1E4				 
1995032000082	19950320	00082	CE 	1995	3	20	95ZZZX1164 	1	19950221	G	3230		RETRACT ARM 			BEECH 	58 	58P 	1152744	CE 										NLG ACTUATOR	MISINDEXED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	112Z					TJ371				DURING AN INSPECTION OF THE LANDING GEAR SYSTEM, THE NOSE LANDING GEAR RETRACT ROD WAS FOUND CONTACTING THE AIRCRAFT STR	UCTURE IN TWO PLACES WITH THE GEAR DOWN AND LOCKED. IT WAS DETERMINED THE NOSE GEAR ACTUATOR RETRACT ARM WAS POSITIONED	 INCORRECTLY. PROPER INDEXING OF THE NOSE GEAR ACTUATOR RETRACT ARM WILL PREVENT THIS SITUATION FROM OCCURRING.				1	L	7	2 	3O				A23CE 					 
1995032000083	19950320	00083	SO 	1995	3	20	95ZZZX1165 	2	19950216	G	8540	643257	SHAFT GEAR 		643259A5 	CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520L 	17032	SO 					STARTER CLUTCH	FAILED 	B			QX2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	88604	429 				421C0604	608427			DURING DISASSEMBLY OF THIS ENGINE, THE 'NEW STYLE' STARTER CLUTCH (REF: SB M92-10) GEAR TEETH WERE STARTING TO FAIL. A	LSO, REF: CRITICAL SB 94-4.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995032000084	19950320	00084	SO 	1995	3	20	95ZZZX1166 	2	19950216	G	8540	643257	SHAFT GEAR 		643259A5 	CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520L 	17032	SO 					STARTER CLUTCH	FAILED 	B			QX2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	88604	429 				421C0604	604981			DURING DISASSEMBLY OF THIS ENGINE, THE 'NEW STYLE' STARTER CLUTCH (REF: SB M92-10) GEAR GEETH WERE STARTING TO FAIL. A	LSO, REF: CRITICAL SB 94-4.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995032000085	19950320	00085	GL 	1995	3	20	95ZZZX1167 	3	19950213	G	6111	T101738	BLADE 			BEECH 	90 	C90 	1152913	CE 						HARTZL	HCB3T	HCB3TN3 	GL 	BLADE BORE	CORRODED 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1335 						BV1736		INSPECTION OF PROP FOUND HEAVY CORROSION IN BLADE BORE OF BLADE NR 1.						1	L	7	2 	3T				3A20 		6	C	P15EA	 
1995032000086	19950320	00086	GL 	1995	3	20	95ZZZX1168 	3	19950213	G	6111	T101738	BLADE 			BEECH 	90 	C90 	1152913	CE 						HARTZL	HCB3T	HCB3TN3 	GL 	BLADE BORE	CORRODED 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1335 						BV1736		INSPECTION OF PROP FOUND HEAVY CORROSION IN BLADE BORE OF BLADE NR 2.						1	L	7	2 	3T				3A20 		6	C	P15EA	 
1995032000087	19950320	00087	GL 	1995	3	20	95ZZZX1169 	3	19950213	G	6111	T101738	BLADE 			BEECH 	90 	C90 	1152913	CE 						HARTZL	HCB3T	HCB3TN3 	GL 	BLADE BORE	CORRODED 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1335 						BV1736		INSPECTION OF PROP FOUND HEAVY CORROSION IN BLADE BORE OF BLADE NR 3.						1	L	7	2 	3T				3A20 		6	C	P15EA	 
1995032000088	19950320	00088	GL 	1995	3	20	95ZZZX1170 	3	19950213	G	6110	C30641	BULKHEAD 			BEECH 	90 	C90 	1152913	CE 						HARTZL	HCB3T	HCB3TN3 	GL 	PROP	CRACKED 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1335 						BV1736		INSPECTION FOUND LARGE CRACKS IN PROP BULKHEAD.						1	L	7	2 	3T				3A20 		6	C	P15EA	 
1995032000089	19950320	00089	SW 	1995	3	20	95ZZZX1171 	1	19950221	G	3020	1173T423	SWITCH 			GULSTM	560 	560 	0141402	SW 										RT ENG AI	DEFECTIVE 	B			AC1R	O				OTHER 				J			WARNING INDICATION 			DE	DESCENT 	1			SO	01	70TG	2040 			0476	5600069				PILOTS SQUAWKED THE RT ENGINE ANTI-ICE LIGHT CAME ON DURING DESCENT WHEN THE POWER WAS REDUCED TO 76 PERCENT N2. TROUBL	ESHOOTING THE SYSTEM REVEALED TWO PROBLEMS. NR 1: THE 300 DEGREE TEMPERATURE SWITCH WAS ACTUATING AT 340 DEGREES. NR 	2: THE RAM AIR DUCT THAT PROVIDES COOLING FOR THE WING ANTI-ICE AIR WAS TORN. THE TEAR WAS LOCATED IN THE AREA OF THE 	COUPLING AT FS 315.0. A NEW 300 DEGREE SWITCH WAS ORDERED AND INSTALLED. ALSO, THE FORWARD RAM AIR DUCT WAS REPLACED. 	 THIS WAS THE FIRST SQUAWK ON THE ENGINE ANTI-ICE SYSTEM SINCE SB 560-30-03, REPLACEMENT OF THE 300 DEGREE ANTI-ICE TEMP	ERATURE SENSORS WITH 350 DEGREE SENSORS. SWITCH PN 1173T42-3, DUCT PN X2292S4-11.	1	H	7	2 	3O				6A1 					 
1995032000090	19950320	00090	SW 	1995	3	20	95ZZZX1172 	1	19950221	G	3010	X2292S411	DUCT 			GULSTM	560 	560 	0141402	SW 										WING AI	TORN 	B			AC1R	O				OTHER 				J			WARNING INDICATION 			DE	DESCENT 	1			SO	01	70TG	2040 				5600069				PILOTS SQUAWKED THE RT ENGINE ANTI-ICE LIGHT CAME ON DURING DESCENT WHEN THE POWER WAS REDUCED TO 76 PERCENT N2. TROUBL	ESHOOTING THE SYSTEM REVEALED TWO PROBLEMS. NR 1: THE 300 DEGREE TEMPERATURE SWITCH WAS ACTUATING AT 340 DEGREES. NR 	2: THE RAM AIR DUCT THAT PROVIDES COOLING FOR THE WING ANTI-ICE AIR WAS TORN. THE TEAR WAS LOCATED IN THE AREA OF THE 	COUPLING AT FS 315.0. A NEW 300 DEGREE SWITCH WAS ORDERED AND INSTALLED. ALSO, THE FORWARD RAM AIR DUCT WAS REPLACED. 	 THIS WAS THE FIRST SQUAWK ON THE ENGINE ANTI-ICE SYSTEM SINCE SB 560-30-03, REPLACEMENT OF THE 300 DEGREE ANTI-ICE TEMP	ERATURE SENSORS WITH 350 DEGREE SENSORS. SWITCH PN 1173T42-3, DUCT PN X2292S4-11.	1	H	7	2 	3O				6A1 					 
1995032000092	19950320	00092	NM 	1995	3	20	95ZZZX1174 	1	19950217	G	2130	588208	VALVE FITTING 			PIPER 	PA60 	PA60602P 	7106015	NM 										PRESS BLKHD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	27	6899R	1572 				608265017				EMERGENCY EXIT WINDOW AND CABIN DOOR SEAL LEAKAGE CAUSING CYCLING OF SEAL PRESSURE SWITCH. PILOT WAS SEEING CONSTANT GY	RO PRESSURE FLUCTUATIONS ON COCKPIT INSTRUMENT PRESSURE GAUGE AND PREMATURE PRESSURE PUMP FAILURE. CAUSE WAS FOUND TO B	E A CRACKED BULKHEAD .25 INCH PIPE ALUMINUM FITTING, NO PART NUMBER GIVEN IN PARTS MANUAL.				1	M	7	2 	3O			RT	A17WE 					 
1995032000426	19950320	00426	SO 	1995	3	20	95ZZZX1198 	1	19950201	G	2140	460681	ELBOW 			PIPER 	PA23 	PA23250 	7102308	SO 										HEATER SHUT OFF	CRACKED 	B	S	A	B2ER	K				NONE 				B	K		SMOKE/FUMES/ODORS/SPARKS 	FLUID LOSS 		IN	INSP/MAINT 	1			EA	23	5064C	4050 				277405376				PILOT COMPLAINT OF FUEL SMELL IN COCKPIT. REMOVAL OF FUEL SYSTEM CONTROL BOX FOUND HEATER SHUT OFF VALVE ELBOW CRACKED.	 SUSPECT POSSIBLY CAUSED BY FREEZING WATER.					1	L	7	2 	3O				1A10 					 
1995032000427	19950320	00427	GL 	1995	3	20	95ZZZX1199 	2	19950109	G	7260	23034102	OIL TUBE 		23001936 						ALLSN 	250B 	250B17 	03012	GL 					GEARBOX	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99		390 	36 		BN23205		CAE880173			ENGINE INSPECTION FOUND OIL DELIVERY TUBE DEFECTIVE.											3	T			E10CE				 
1995032000428	19950320	00428	CE 	1995	3	20	95ZZZX1200 	1	19950203	G	3020	625260079	INLET ASSY 			CESSNA	650 	650 	2076802	CE 										ANTI-ICE TUBE LT	CRACKED 	B	L	A	JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	650TC	4197 				6500064				LEFT ENGINE INLET ANTI-ICE RING FOUND FRACTURED AT THE 6:00 AND 9:00 POSITIONS. REPAIRED BY WELDING AND INSTALLING REIN	FORCING GUSSETS. SUBMITTER SUGGESTS REDESIGNING INLET ANTI-ICE RING WITH SLIP COUPLING OR FLEXIBLE CORRECTION TO ALLOW 	FOR EXPANSION AND CONTRACTION. THE EXISTING RING IS RIGIDLY ATTACHED AT 3 POINTS. THERE IS NO PROVISION TO ALLOW EXPANS	ION AND CONTRACTION OF RING.			2	L	7	2 	4F				A9NM 					 
1995032000429	19950320	00429	EA 	1995	3	20	95ZZZX1201 	2	19950215	G	8530	72255	TUBE 			PIPER 	PA31 	PA31 	7103102	SO 	LYC 	O540 	TIO540A2C 	41532	EA 					NR 4 PUSH ROD	HOLE CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	333BW		193 			317401237	L429661A			DURING ANNUAL INSPECTION, FOUND LT BAFFLE TIE ROD, PN 4197500, HAD RUBBED A HOLE IN BOTH INTAKE AND EXHAUST PUSH ROD TUB	ES ON NR 4 CYLINDER. THE ROUTING OF THE TIE RODS ARE VERY CLOSE TO THE PUSH ROD TUBES. SUBMITTER SUGGESTS THAT ALL BAFF	LE TIE RODS BE LOOKED AT CAREFULLY FOR PROPER ROUTING DURING SCHEDULED MAINTENANCE OR WHEN LOOKING FOR OIL LEAKS. THIS 	COULD CAUSE A LARGE LOSS OF ENGINE OIL.			1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995032000430	19950320	00430	EA 	1995	3	20	95ZZZX1202 	2	19950215	G	8530	72257	TUBE 			PIPER 	PA31 	PA31 	7103102	SO 	LYC 	O540 	TIO540A2C 	41532	EA 					NR 4 PUSH ROD	HOLE CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	333BW		193 			317401237	L429661A			DURING ANNUAL INSPECTION, FOUND LT BAFFLE TIE ROD, PN 4197500, HAD RUBBED A HOLE IN BOTH INTAKE AND EXHAUST PUSH ROD TUB	ES ON NR 4 CYLINDER. THE ROUTING OF THE TIE RODS ARE VERY CLOSE TO THE PUSH ROD TUBES. SUBMITTER SUGGESTS THAT ALL BAFF	LE TIE RODS BE LOOKED AT CAREFULLY FOR PROPER ROUTING DURING SCHEDULED MAINTENANCE OR WHEN LOOKING FOR OIL LEAKS. THIS 	COULD CAUSE A LARGE LOSS OF ENGINE OIL.			1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995032000431	19950320	00431	SO 	1995	3	20	95ZZZX1203 	1	19950123	G	2720	6342003	BAR ASSY 			PIPER 	PA28 	PA28180 	7102808	SO 										RUDDER PEDAL	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	15378	5774 				287305067				DURING ANNUAL INSPECTION, A CRACK WAS FOUND IN THE RUDDER PEDAL ASSEMBLY CONNECTING TUBE. THE CRACK WAS APPROXIMATELY .	25 INCH LONG AND LOCATED ON THE AFT SIDE OF A TUBE WELD. (REF: AC 43-16-, ALERT NR 198, JANUARY, 1995, PAGE 11.)					1	L	7	1 	3O				2A13 					 
1995032000432	19950320	00432	CE 	1995	3	20	95ZZZX1204 	1	19950215	G	7900	52518021	OIL SEPARATOR 			CESSNA	402 	402C 	207590R	CE 										ENG BREATHER	FROZEN 	D		A		A				UNSCHED LANDING 				B			SMOKE/FUMES/ODORS/SPARKS 			CL	CLIMB 	1			GL	17	67850	6351 				402C0410				AIRCRAFT LEFT THE AIRPORT WITHOUT A PREHEAT AND TEMPS IN THE 20'S DEGREE FAHRENEIT. SHORTLY AFTER TAKEOFF, ENGINE START	ED SMOKING, AIRCRAFT RETURNED SAFELY TO THE AIRPORT. CAUSE OF THE PROBLEM WAS FROZEN MOISTURE IN THE OIL SEPARATOR WHIC	H DID NOT ALLOW CASE PRESSURE TO BE RELIEVED THROUGH THE BREATHER LINE. CESSNA DOES NOT USE ANY METHOD OF BYPASS ON THI	S AIRCRAFT SHOULD THE BREATHER LINE EVER BECOME PLUGGED SUCH AS THIS EXAMPLE.			1	L	7	2 	3O				A7CE 					 
1995032000433	19950320	00433	SO 	1995	3	20	95ZZZX1205 	1	19950123	G	2720	6345100	SUPPORT 			PIPER 	PA28 	PA28180 	7102808	SO 										RUDDER BAR	CRACKED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	15378	5774 				287305067				DURING ANNUAL INSPECTION, THE RUDDER PEDAL BAR SUPPORT ASSEMBLY WAS FOUND CRACKED AT THE AFT LEFT CORNER. THE CRACK WAS	 ABOUT 1 INCH LONG.					1	L	7	1 	3O				2A13 					 
1995032000434	19950320	00434	SO 	1995	3	20	95ZZZX1206 	1	19950307	G	5311		FABRIC 			PIPER 	PA16 	PA16 	7101602	SO 										FUSELAGE	DEFECTIVE 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	03	5640H	12 				16251				AIRCRAFT RECOVERED IN JULY, 1990, WITH BLUE RIVER 7600 PROCESS. AIRCRAFT TIED DOWN OUTSIDE AT ALL TIMES. FAILURE OF FI	NAL FINISH (CRACKING, FLAKING, CHIPPING) TO EXTENT OF MAKING REFINISHING IMPOSSIBLE. ENTIRE AIRCRAFT BEING RECOVERED WI	TH STITTS PROCESS. SUSPECT POOR PRODUCT. TOLD BY BLUE RIVER NOT TO USE IT ANYMORE.				1	H	7	1 	3O				1A1 					 
1995032000435	19950320	00435	CE 	1995	3	20	95ZZZX1207 	1	19950227	G	3230	3581512514	ROD ASSY 			BEECH 	58 	58 	1152740	CE 										RT MLG	FAILED 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			EA	21	58WC	3288 				TH766				BRACE ROD ASSEMBLY ON RIGHT GEAR MALFUNCTIONED CAUSING GEAR COLLAPSE ON LANDING.						1	L	7	2 	3O				3A16 					 
1995032000436	19950320	00436	EA 	1995	3	20	95ZZZX1208 	2	19950215	G	7322	2525033	REGULATOR BODY 	BENDIX 	RSA10 						LYC 	O540 	IO540* 	41532	EA 					FUEL INJECT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09										FOUND CRACK AT THE CENTERBODY BELLOWS OPENING WITH O.E.M.'S BRASS BELLOWS ALREADY INSTALLED. RECOMMENDATIONS - HAVE A B	ETTER BELLOWS INSTALLING TOOL AND BIGGER BODY SUPPORT.										3	O			1E4				 
1995032000437	19950320	00437	EA 	1995	3	20	95ZZZX1209 	2	19950217	G	8520		CONNECT ROD 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	LTIO540J2BD 	41533	EA 					NR 1,2,3 CYLS	FAILED 	D				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	CL	CLIMB 	1			EA	21	3581C	4998 	606 			318052091	L110068A			AFTER TAKEOFF, RIGHT ENGINE BECAME VERY ROUGH. ENGINE WAS FEATHERED, AIRCRAFT RETURNED TO AIRPORT AND LANDED. INSPECTI	ON FOUND CONNECTING ROD CAPS HAD SEPARATED FROM NR 1, NR 2, AND NR 3 RODS. CONNECTING ROD PENETRATED BOTH BOTTOM AND TO	P OF ENGINE CASE.				1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995032000438	19950320	00438	SO 	1995	3	20	95ZZZX1210 	1	19950208	G	3230	42042	ARM 			PIPER 	PA31 	PA31310 	7103103	SO 										RT MLG	CRACKED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	27275					317712066				INSPECTION OF THE RT MLG REVEALED A CRACK IN THE RADIUS ADJACENT TO THE CENTER BOLT HOLE. CRACK ORIGINATING FROM EDGE A	ND PROPAGATING TOWARD HOLES. SUSPECT FROM FATIGUE. THIS IS THE SECOND FAILURE OF THIS PART IN THIS WAY.					1	L	7	1 	3O			RT	A20SO 					 
1995032000443	19950320	00443	CE 	1995	3	20	95ZZZX1215 	1	19950215	G	2434	ALT9422	ALTERNATOR 	PRESTOLITE 		CESSNA	310 	310R 	2074245	CE 										END BEARING	FAILED 	E				O				OTHER 				H			ELECT. POWER LOSS-50 PC 			CR	CRUISE 	1			GL	23	8476T					310R0035				LEFT ALTERNATOR FAILED IN FLIGHT. APPEARS END BEARING FAILED CAUSING ROTOR TO WOBBLE, IN TURN, FRONT BEARING FAILED AND	, PN 640934, HUB ASSY WAS SEVERELY DAMAGED. ALTERNATOR WAS OVERHAULED BY CLYDESDALE ENGINE IN COLUMBUS, OHIO.					1	L	7	2 	3O				3A10 					 
1995032000444	19950320	00444	NM 	1995	3	20	95ZZZX1216 	1	19950215	G	2434	ALU8421R	ALTERANTOR 	PRESTOLITE 		PIPER 	PA60 	PA60600A 	7106002	NM 										PLUS TERMINAL	DEFECTIVE 	B			WC7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	3643D				2071965	600835816123				PILOT REPORT: RIGHT ALT INOP. FOUND PLUS TERMINAL ON ALTERNATOR LOOSE IN CASE. DIODE BLOCK SEEMED LOOSE INTERNALLY. 	POSITIVE LEAD AT CURRENT LIMITER HAD A LOOSE TERMINAL (CRIMPED AMP CONNECTOR) LOOSE ON WIRE. BRUSHES APPEARED GLAZED.					1	M	7	2 	3O			RT	A17WE 					 
1995032000445	19950320	00445		1995	3	20	95ZZZX1217 	1	19950221	G	7312	101050A1	VALVE ASSY 	CHNDLREVANS 							PWA 	JT9 	JT9* 	52054	NE 					FUEL DEICE	MISOVERHAULED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	03										CLEAR SILICONE COMPOUND USED FOR POTTING IN SWITCH CAVITY INSTEAD OF SILASTIC 'E' RTV. REMOVED TO CONVERT TO 101050A1. 	 WIRE ENDS LEFT SUSPENDED IN CLEAR SILICONE. ORIGINAL PART NUMBER AND PARTS LIST NUMBER CROSSED OUT ON NAMEPLATE AND NE	W P/N VIBROPEENED IN INCORRECT LOCATION. UNIT WAS RECEIVED FROM FEDERAL EXPRESS FOR OVERHAUL.									4	F			E20EA				 
1995032000446	19950320	00446		1995	3	20	95ZZZX1218 	2	19950222	G	7414	M3525	COIL 	SLICK 	4371 															MAGNETO	CRACKED 	B			KC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03		400 			91070431					CUSTOMER SAID MAG INOPERATIVE. BENCH TEST CONFIRMED. INSPECTION SHOWED CRACKED COIL. COIL RESISTANCES MEET SPECS, BUT	 MAG DOES NOT SPARK CONSISTENTLY. INSTALLED NEW COIL (PN M3975) AND RE-TESTED. MAG TESTS GOOD. CONDENSER TESTED GOOD.	 SUSPECT SECONDARY CIRCUIT OUTPUT ARCING TO GROUND INTERNALLY.																	 
1995032000447	19950320	00447	SO 	1995	3	20	95ZZZX1219 	1	19950220	G	3230	2251200	STUD 			PIPER 	PA24 	PA24260 	7102406	SO 										MLG SIDE BRACE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8612P	3538 				244064				WHILE INSPECTING THE LANDING GEAR SYSTEM, THE SIDE BRACE STUDS WERE REMOVED FOR CLOSE VISUAL AND N.D.I. INSPECTION. THE	 LEFT STUD WAS FOUND CRACKED AND WORN BEYOND LIMITS. SUSPECT NORMAL WEAR. SUBMITTER RECOMMENDS MORE FREQUENT REQUIRED 	DISASSEMBLY AND DETAILED INSPECTION OF THIS PART.				1	L	7	1 	3O				1A15 					 
1995032000448	19950320	00448	CE 	1995	3	20	95ZZZX1220 	1	19950126	G	3230	3581512514	RETRACT ROD 			BEECH 	58 	58 	1152740	CE 										RT MLG	FAILED 	D				K				NONE 				O			OTHER 			AP	APPROACH 	1			SO	07	40JB	3661 				TH338				FROM EVIDENCE SEEN, HARD LANDING BENT RT RETRACT ROD. WHEN GEAR WAS RETRACTED, THIS CAUSED RT GEAR TO COME UP TOO FAR, 	AND JAMMED UPLOCK BLOCK INTO SKIN. WHEN GEAR WAS LOWERED, RT RETRACT ROD FAILED CAUSING RT GEAR NOT TO EXTEND. RESULT,	 PROP STRIKE RT ENGINE, RT FLAP, AND AILERON DAMAGED, RT WING TIP DAMAGED.				1	L	7	2 	3O				3A16 					 
1995032000449	19950320	00449	EA 	1995	3	20	95ZZZX1221 	2	19950123	G	8530	76038	VALVE COVER 			PIPER 	PA31 	PA31P 	7103120	SO 	LYC 	O541 	TIGO541E1A 	41539	EA 					NR 4 CYL	CRACKED 	D	L			K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	09	11AB					31P7300169	L77962			OPERATOR/OWNER COMPLAINED OF OIL LEAK ON LEFT ENG. REMOVED COWLING AND FOUND OIL AROUND 2-4-6 CYLINDER AREAS. WASHED D	OWN ENGINE. RAN AND SHUT DOWN ENGINE, FOUND OIL SEEPING FROM AROUND NR 4 CYLINDER VALVE COVER/GASKET. WASHED AREA AND 	RAN ENGINE AGAIN. FOUND OIL LEAKING AT SURFACE OF VALVE COVER. REMOVED VALVE COVER, FOUND COVER, PN 76038, CRACKED WHE	RE INTAKE ROCKER ARM HAD BEEN HITTING.			1	L	7	2 	3O	3	O		A8EA 	E19EA				 
1995032000450	19950320	00450	EU 	1995	3	20	95ZZZX1222 	1	19950308	G	7713	T67683305	INDICATOR 			SLNSBY	T67 	T67M260 	8323006	EU 										MANIFOLD PRESS	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17										SEVERAL (13) MANIFOLD FUEL PRESSURE GAUGES HAVE BEEN FOUND BY THE AIRCREW TO BE SLOW TO RESPOND. INST. WAS SENT TO UNITE	D INST. FOR REPAIR. UNITED INSTS. SAID HEY FOUND THE ADJUSTMENT SCREW HAD BEEN MOVED. INSTS. WERE INSTALLED ON AIRCRAF	T IN PRODUCTION.				1	L	7	1 	3O			NT	A73EU 					 
1995032000451	19950320	00451		1995	3	20	95ZZZX1223 	4	19950226	G	2312	KX170A	FREQ INDICATOR 	KING 		PIPER 	PA28 	PA28R200 	7102811	SO 										NAV/COM	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	16362					28R7335135				NAV. FREQ. INDICATOR JUMPS OUT OF ALIGNMENT. FOUND MISSING TEETH ON PLASTIC GEAR. APPEARED TO BE DAMAGED FROM INCORREC	T SPRAY CLEANER. NO BROKEN TEETH FOUND IN RADIO. COVER AND SCREWS AND HOLD-DOWNS MISSING FROM NAV. SMO - 'REQUIRED PA	RT' COULD ALLOW RF FROM XMIT IN NAV - POTENTIALLY DANGEROUS. C-212 - ELECTROLITIC CAP, SHOULD BE MYLAR CAP PER KING PART	 LIST.			1	L	7	1 	3O				2A13 					 
1995032000452	19950320	00452	EU 	1995	3	20	95ZZZX1224 	1	19950308	G	2710	T67G20507	PIN SUPPORT 			SLNSBY	T67 	T67M260 	8323006	EU 										OUTB AILERON	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	7020D	573 				2109				ON INSPECTION OF FLIGHT CONTROL, THE LT AILERON WAS FOUND WITH TOO MUCH PLAY. AILERON WAS REMOVED FOR INSPECTION. FURT	HER INSPECTION FOUND PIN SUPPORT PLATE WAS WORN.					1	L	7	1 	3O			NT	A73EU 					 
1995032000453	19950320	00453	EU 	1995	3	20	95ZZZX1225 	1	19950308	G	7160		AIR BOX 			SLNSBY	T67 	T67M260 	8323006	EU 										INTAKE	DOOR LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3011Q	346 				2128				AFTER INSPECTION OF THE ENGINE AIR BOX, THE REAR FLAPPER HINGED DOOR WAS FOUND LOOSE. THE HINGE HAD WORN AND WORKED ITS	ELF LOOSE. THE ONLY OTHER ATTACHMENT IS A SPRING TO HOLD DOOR CLOSED. IF THE SPRING WOULD HAVE COME LOOSE, IT WOULD BE	 POSSIBLE FOR THE DOOR TO BE SUCKED UP INTO THE FUEL SERVO. THERE IS NO PART NUMBER IN THE SLINGSBY MANUAL FOR THIS FLA	PPER DOOR.			1	L	7	1 	3O			NT	A73EU 					 
1995032000454	19950320	00454	CE 	1995	3	20	95ZZZX1226 	1	19950228	G	3213		BEARING 			CESSNA	421 	421 	2076010	CE 										MLG LT	CRACKED 	B			DJFR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	4564L					4210164				C/W AD 90-02-13 STRUCTURAL INTEGRITY OF THE MAIN GEAR BARREL INNER BEARING, PER CESSNA SB MEB88-7A. FOUND RT AND LT INN	ER BEARINGS CRACKED PER EXAMPLE IN SB. REPLACED BEARINGS WITH NEW TYPE, PN 5141109-1.					1	L	7	2 	3O			RT	A7CE 					 
1995032000455	19950320	00455	CE 	1995	3	20	95ZZZX1227 	1	19950228	G	3213		BEARING 			CESSNA	421 	421 	2076010	CE 										MLG RT	CRACKED 	B			DJFR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	4564L					4210164				C/W AD 90-02-13 STRUCTURAL INTEGRITY OF THE MAIN GEAR BARREL INNER BEARING, PER CESSNA SB MEB88-7A. FOUND RT AND LT INN	ER BEARINGS CRACKED PER EXAMPLE IN SB. REPLACED BEARINGS WITH NEW TYPE, PN 5141109-1.					1	L	7	2 	3O			RT	A7CE 					 
1995032000456	19950320	00456		1995	3	20	95ZZZX1228 	4	19950227	G	2562	ELT10	ELT 	NARCO 		PIPER 	PA28 	PA28161 	7102803	SO 										CIRCUIT BOARD	BURNED 	D				K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			IN	INSP/MAINT 	1			SW	15	5893F	3635 			63883	287790142				WHILE TESTING ELT FOR FUNCTIONAL TEST ON BENCH. UNIT BEGAN TO SMOKE. REMOVED HEAD AND BATTERY AND NOTED BURNED AREA ON	 CIRCUIT BOARD. RETURNED TO MANUFACTURER FOR REPAIR.					1	L	7	1 	3O				2A13 					 
1995032000457	19950320	00457	SO 	1995	3	20	95ZZZX1229 	1	19950131	G	2140	07D70	EXHANGER 	JANITROL 	B2030 	PIPER 	PA30 	PA30 	7103002	SO 										DRAIN TUBE	MISMANUFACTURED 	B	S		IS4R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	09					2650639					DRAIN HOLE FOR OVERBOARD FUEL DRAIN WAS NEVER DRILLED FROM THE FACTORY. REF: B/P 07D70.						1	L	7	2 	3O				A1EA 					 
1995032000564	19950320	00564	SW 	1995	3	20	95ZZZX1234 	1	19950126	G	6300	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1078N		317 			45389				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 2 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL OPERATION CAUSES PARTS TO WEAR OUT TOO SOON. S	PACERS, BEARINGS, AND BOLTS TT 316.9.				1	G	7	1 	3U				H2SW 					 
1995032000565	19950320	00565	SW 	1995	3	20	95ZZZX1235 	1	19950126	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1078N		317 			45389				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 2 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL OPERATION CAUSES PARTS TO WEAR OUT TOO SOON. S	PACERS, BEARINGS, AND BOLTS TT 316.9.				1	G	7	1 	3U				H2SW 					 
1995032000735	19950320	00735	SO 	1995	3	20	95ZZZX1250 	1	19950201	G	5330		SKIN 			PIPER 	PA28 	PA28* 		SO 										TOP INST. PANEL	CORRODED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	5311W					28365				FUSELAGE SKIN PANELS ACROSS TOP OF INST. PANEL SEVERELY CORRODED. WATER MOST LIKELY ENTERED THROUGH A WINDSHIELD LEAK. 	 (THIS IS 2ND PA 28 OF THIS VINTAGE FOUND WITH THIS DEFECT IN LAST 3 YEARS). RECOMMEND INSPECTION BELOW VINYL AND REMOV	AL OF FOAM BACKED VINYL COVERING. REPLACE WITH PLAIN VINYL OR PAINT PANELS.				1	L	7	1 	3O				2A13 					 
1995032000736	19950320	00736	SO 	1995	3	20	95ZZZX1251 	1	19950201	G	2916	752636	O-RING 	GARKENYON 	953802 	PIPER 	PA46 	PA46310P 	7104605	SO 										HYD RESERVOIR	FAILED 	H	S			O				OTHER 				O	K		OTHER 	FLUID LOSS 		AP	APPROACH 	1			GL	17	4378S				0412	468508009				PILOT ATTEMPTED TO LOWER GEAR FOR LANDING. BOTH MAIN GEARS CAME DOWN AND LOCKED, BUT NOSE GEAR FAILED TO LOCK DOWN. FU	RTHER ATTEMPTED TO OPERATE GEAR NORMALLY. FAILED. AFTER NOSE GEAR WAS EXTENDED AND LOCKED BY ALTERNATE MEANS. AIRCRAFT	 LANDED AND WAS TAKEN TO MAINTENANCE. UPON INSPECTION, FOUND LOWER O-RING IN THE HYDRAULIC RESERVOIR WAS PINCHED. THIS	 ALLOWED HYDRAULIC FLUID TO LEAK OUT, AND CAUSED THE FAILURE OF THE LANDING GEAR SYSTEM.			1	L	7	1 	3O				A25SO 					 
1995032000737	19950320	00737		1995	3	20	95ZZZX1252 	4	19950201	G	3457	GPS155	RECEIVER 			MOONEY	M20 	M20K 	5870220	SW 										GPS SYSTEM	MISINSTALL 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	05	231RD					205427				THE GARMIN GPS-155 INSTALLATION DOCUMENT DOES NOT ALERT THE INSTALLING AGENCY OF THE POSSIBILITY THAT THE NAV 1 SYSTEM W	ILL DISPLAY ERRONEOUS INFORMATION WHEN THE GPS-155 IS INSTALLED IAW GARMIN DOCUMENT 190-00065-02, REV G, 9-13-94. THIS 	SITUATION WILL OCCUR WHEN PILOT SELECTS 'GPS' MODE, & THE OBS INPUTS TO THE NAV 1 RECEIVER ARE LEFT OPEN-CIRCUITED. ON 	FIGURES 1-3, PAGE 24 (GARMIN GPS-155 INSTALL), THE NAV 1 SOURCE ON THE SCHEMATIC IS NOT DEFINDED TO A SPECIFIC MODEL OF 	NAV RECEIVER. THERE ARE SEVERAL NAV SYSTEM (I.E., KING KNS-80, KNS-81, ETC.) THAT WILL NOT OPERATE CORRECTLY WITH THE O	BS LINES OPEN-CIRCUITED.	1	L	7	1 	3O				2A3 					 
1995032000738	19950320	00738	SO 	1995	3	20	95ZZZX1253 	2	19950301	G	8520		CRANKSHAFT 			BEECH 	35 	V35B 	1151548	CE 	CONT 	O550 	IO550B 		SO 					NR 3 CRANK CHEEK	BROKEN 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	1693W		1006 			D9389	249112R			ENGINE DISASSEMBLY REVEALED THE CRANKSHAFT HAD FAILED THROUGH THE NR 3 CRANK CHEEK. THE FRACTURE FACE WAS EXAMINED BY T	HE TCM METALLURGIST WHO CONFORMED THE FAILURE WAS IN BENDING OVERLAOD. THE NR 1 AND NR 2 MAIN BEARINGS WERE HAMMERED OU	T TO EXTRUDE THE BEARINGS. THE CRANKCASE PARTING SURFACE WAS SEVERELY FRETTED AT THE NR 2 MAIN BEARING SUPPORT. FRETTI	NG WAS ALSO PRESENT, BUT TO A LESSER DEGREE, ON THE NR 1 AND NR 3 MAIN BEARING SUPPORTS. BEARING AND ALUMINUM DEBRIS WA	S PRESENT IN THE OIL SUMP.		1	L	7	1 	3O	3	O		3A15 	E3SO				 
1995032000739	19950320	00739	SO 	1995	3	20	95ZZZX1254 	1	19950301	G	5350	JF451	LATCH 			LKHEED	1329 	1329 	5263102	SO 										RADOME	NOT LATCHED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	428DA					5048				TOP 2 LATCHES WERE NOT LATCHED PERFECTLY ALLOWING PRESSURE SEAL TO BLOW OUT AT THE TOP BETWEEN THE LATCHES. SUBMITTER S	UGGESTION IS TO LATCH THE 2 TOP LATCHES FIRST TO INSURE THEIR INTEGRITY.					2	L	7	4 	4J				2A15 					 
1995032000740	19950320	00740	CE 	1995	3	20	95ZZZX1255 	1	19950217	G	7830	216821	SWITCH 	ROHR 	2C20001503 	CESSNA	500 	560CESSNA 	2076750	CE 										LT DEPLOY	FAILED 	D				O				OTHER 				P			NO WARNING INDICATION 			LD	LANDING 	1			GL	03	502T	1262 			2664	5600153				LT DEPLOY LIGHT FAILED TO COME ON AT LANDING AND REVERSER DEPLOYMENT. DEPLOY SWITCH FAILED IN OPEN POSITION. PINNED RE	VERSER FOR DURATION OF TRIP. BETTER QUALITY CONTROL AT MANUFACTURE AND CLOSER ATTENTION TO INSTALLATION CLEARANCES.					2	L	7	2 	4F			RT	A22CE 					 
1995032000741	19950320	00741	CE 	1995	3	20	95ZZZX1256 	1	19950217	G	2121	BC61A9012	BLOWER 			CESSNA	500 	560CESSNA 	2076750	CE 										VENT BOX	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	502T	216 			250	5600153				OVERHEAD BLOWER FAN FAILED AFTER 215.8 HRS TSO. THIS INSTALLATION IS EXTREMELY TIME CONSUMING TO GET TO. IT IS NOT COS	T EFFECTIVE TO GET IN THERE AND CHANGE THIS BLOWER EVERY 4 MONTHS. SUBMITTER SUGGESTION AS TO BETTER QUALITY CONTROL IN	 OVERHAUL PROCESS WOULD ASSURE BETTER PERFORMANCE.				2	L	7	2 	4F			RT	A22CE 					 
1995032000742	19950320	00742	CE 	1995	3	20	95ZZZX1257 	1	19950217	G	2612	37702808	CONTROL 			CESSNA	500 	560CESSNA 	2076750	CE 										FIRE WARNING	FAILED 	D				K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			GL	03	503T	2405 			9126011	5600154				RT FIRE WARNING FAILED TO TEST DURING PREFLIGHT CHECK. A 2 HOUR DELAY DUE TO LOCATION AND MOUNTING PROCEDURE UNIT IS NO	T REPAIRABLE, COST OF NEW, $1,401.00. SUBMITTER SUGGESTION THAT DELAY COULD HAVE BEEN MINIMIZED IF NUTPLATES WERE USED 	FOR MOUNTING.				2	L	7	2 	4F			RT	A22CE 					 
1995032000743	19950320	00743	CE 	1995	3	20	95ZZZX1258 	1	19950217	G	2730	S2800223	POTENTIOMETER 			CESSNA	500 	560CESSNA 	2076750	CE 										ELEVATOR	SHAFT SHEARED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	503T	952 				560154				DURING REPLACEMENT OF LT ELEVATOR DUE TO LIGHTNING STRIKE DAMAGE, DISCOVERED POTENTIOMETER FOR F.D.R. ELEVATOR POSITION 	SHAFT WAS SHEARED. REPLACED POTENTIOMETER. SINCE THEN, ONE OTHER AIRCRAFT HAD SAME PROBLEM. DISCOVERED BRACKET MISALI	GNMENT. REALIGNED - SO FAR, SO GOOD.				2	L	7	2 	4F			RT	A22CE 					 
1995032000744	19950320	00744	GL 	1995	3	20	95ZZZX1259 	3	19950216	G	6111		BLADE 			BEECH 	200 	C12A 		CE 						HARTZL	HCB3T	HCB3TN3 	GL 	PROP	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	7069A	3703 	14 			BC54		BU12085		THE PROPELLER WAS RECENTLY OVERHAULED BY AN APPROVED O/H FACILITY. AFTER INSTALLATION ON THE AIRCRAFT, THE PROPELLER WO	ULD EMIT A LOUD NOISE AND VIBRATION AT/OR NEAR 100 PERCENT POWER. THIS VIBRATION AND NOISE IS BELIEVED TO BE FROM BLADE	 FLEX ON THE PROPELLER AND IS MAINLY PRESENT DURING STATIC POWER RUNS.				1	L	7	2 	4T				A24CE 		6	C	P15EA	 
1995032000745	19950320	00745	EU 	1995	3	20	95ZZZX1260 	1	19950215	G	7830	MS279934	SWITCH 			AMD 	FALC10	FALCON10 	2730101	EU 										THROTTLE QUAD	FAILED 	D				K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			GL	05	174B	5000 				142				THE THRUST REVERSERS HORN WOULD SOUND WITH ANY MOVEMENT OF THE NR 2 THROTTLE CONTROL ASSY. (NO DEPLOY LIGHTS WOULD ILLU	MINATE AT THAT TIME.) FOUND SWITCH NR S-18 FAILING IN THE CLOSED POSITION WHEN MOVED. THIS IS THE DEPLOY POSITION OF T	HIS SWITCH.				2	L	7	2 	4F				A33EU 					 
1995033100428	19950331	00428		1995	3	31	95ZZZX1263 	4	19950124	G	3457	TNL2000T	GPS 			HAMFLU	HFB320	HFB320 	4071204	EU 										COCKPIT	WIRE CHAFED 	C				K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			GL	15	171GA					1039				GPS LOST POWER - SPARK IN AREA OF CAPTAIN'S LEFT KNEE. SMOKE FILLED AREA OF COCKPIT. BROKEN WIRE GOING TO GPS WIRE CHA	FED. NOT PROPERLY SECURED. ENSURE WIRES ARE SECURED PROPERLY. OPER CONTROL NR GXDA543E					2	L	7	2 	4J				A14EU 					 
1995032000752	19950320	00752		1995	3	20	95ZZZX1268 	4	19950222	G	6122	210940	GOVERNOR 	WOODWARD 		BEECH 	100 	B100 	1152919	CE 										PROP	ARM DETACHED 	D	S			C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			J			WARNING INDICATION 			TO	TAKEOFF 	1			GL	25	990SV		871 			BE112				DURING TAKEOFF, PILOT NOTICED A SURGE AND OVERTEMP FROM LT ENGINE. THE TAKEOFF WAS ABORTED. AFTER INVESTIGATING, FOUND	 ARM ON THE SPLINED SHAFT OF THE PROP GOVERNOR HAD FALLEN OFF. ALL OF THE SAFETY WIRE AND OTHER LINKAGE ATTACHED TO THE	 ARM WERE STILL INTACT AND SECURED. THE ARM ON THE PROP GOVERNOR WAS INSTALLED AT THE PLACE OF OVERHAUL. ALSO, ENGINE 	TURBINE SECTION WAS SEVERELY DAMAGED. SUGGEST CHECKING THIS ARM FOR SECURTIY AT THE NEXT ACCESS AND EVERY INSPECTION.			1	L	7	2 	4T				A14CE 					 
1995032000753	19950320	00753	CE 	1995	3	20	95ZZZX1269 	1	19950222	G	2432	40576	BATTERY 	SAFT 		BEECH 	300 	300BEECH 	1152930	CE 										CELLS	DAMAGED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	100FL				070858	FA34				BATTERY MFG 11-93, PUT INTO SERVICE ON 6-29-94, RETIRED 2-21-95. STD CHARGE RATE USED: ONE-HALF C1 2 HRS, PLUS ONE-TEN	TH C1 4 HRS. DURING SECOND HALF OF 4 HRS, TO CHARGE 6 CELLS SHOWED VOLTAGE DROPS OF 0.15V TO 0.20V WITH ABNORMAL HEAT B	UILD UP IN THESE CELLS AND A TOTAL VOLTAGE DROP OF JUST OVER 1.0V. SEPARATOR DAMAGE INDICATED. SEE BEECH KA-300 MM 24-	32-00, PAGE 3 (JUNE 24, 1994) FOR GAS BARRIER CHECK PROCEDURE.			2	L	7	2 	4T				A24CE 					 
1995032000754	19950320	00754	SW 	1995	3	20	95ZZZX1270 	1	19950201	G	3213		STRUT 	OZONE 		SWRNGN	SA226 	SA226TC 	8780404	SW 										MLG	FAILED 	H	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	220AM					TC234				FAILURE OF THE FORGED ALUMINUM PNEUMATIC HOUSING ON A LANDING GEAR STRUT ON SA226TC ACFT RESULTED AFTER APPROXIMATELY 27	,000 HOURS SERVICE. THE FAILED, LOWER PORTION OF THIS STRUT ASSEMBLY, AND AN ADDITIONAL STRUT ASSEMBLY FROM AN UNIDENTI	FIED AIRCRAFT CONTAINING A SIMILAR CRACK IN THE ALUMINUM HOUSING AND INCLUDING THE INTACT STEEL CYCLINDER ASSEMBLY, WERE	 SUBMITTED FOR EXAMINATION.			1	L	7	2 	4T				A8SW 					 
1995032000755	19950320	00755	SO 	1995	3	20	95ZZZX1271 	1	19950228	G	7430	487782	SWITCH 	BENDIX 		PIPER 	PA22 	PA22150 	7102210	SO 										IGNITION	DEFECTIVE 	D				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CL	CLIMB 	1			SW	15	6813B					224108				DEFECTIVE BENDIX SWITCH FAILED ON TAKEOFF RESULTING IN ENGINE STOPPAGE AND SUBSTANTIAL DAMAGE TO AIRCRAFT. AD 76-7-12 W	AS COMPLIED WITH 80 HOURS (THIS IS TO CORRECT A TYPOGRAPHICAL ERROR OF TIME SINCE ACCOMPLISHED 76-7-12 (80 HRS) PRIOR TO	 INCIDENT. ALSO, THE ROUTINE MAG CHECK PRIOR TO TAKEOFF WAS NORMAL. HOWEVER, ON CLOSE INSPECTION, THE SWITCH GOES 'OFF	' IN THE 'BOTH ON' POSITION WHEN MOVED AXIALLY WITH KEY. AD 76-7-12 IS A ROTATIONAL TEST AND WILL NOT REVEAL DEFECTIVE 	CONTACTS. RECOMMEND AD 76-7-12 INCLUDE AXIAL MOVEMENT IN 'BOTH ON' POSITION, SWITCH HAD 3532 HRS.		1	H	7	1 	3O				1A6 					 
1995032000756	19950320	00756	CE 	1995	3	20	95ZZZX1272 	1	19950214	G	3297		WIRE 			BEECH 	36 	A36 	1151604	CE 										MLG LIGHTS	CHAFED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			WP	25	8204M					E2667				THE WIRING BUNDLE FROM THE LANDING GEAR INDICATOR LIGHTS AND LANDING GEAR SELECTOR HANDLE ASSEMBLY CHAFED AGAINST THE LI	GHTING BUS BAR ASSEMBLY PENETRATING THE INSULATION AND SHORTING THE WIRE TO THE BUS BAR. THIS ALLOWED UNREGULATED CURRE	NT FLOW THROUGH THE ACFT CAUSING EXTENSIVE ELECTRICAL DAMAGE.				1	L	7	1 	3O			 	3A15 					 
1995032000757	19950320	00757		1995	3	20	95ZZZX1273 	1	19950209	G	2434	902014	BEARING 	PRESTOLITE 	ALT9422 															SLIP RING END	FAILED 	B			CYKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07		100 			3B000914					BEARING INNER RACE DOES NOT SEEM TO BE PROPERLY HARDENED. MARKINGS ON BEARINGS: PEER TRI 13307E JAPAN.																			 
1995032000759	19950320	00759	CE 	1995	3	20	95ZZZX1275 	1	19950303	G	5610	5042006931	WINDSHIELD 	PPG 		BEECH 	90 	C90 	1152913	CE 										PILOT'S	SCREWS CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	2050A	7450 				LJ813				WHEN REMOVING PILOT'S WINDSHIELD FOR REPLACEMENT, ALL ATTACH SCREWS WERE FOUND SEVERELY CORRODED TO THE POINT THE SCREWS	 BROKE WHEN REMOVAL WAS ATTEMPTED. BEECH RECOMMENDS REPLACEMENT AT 12,000 HOURS.					1	L	7	2 	3T				3A20 					 
1995032000760	19950320	00760	CE 	1995	3	20	95ZZZX1276 	1	19950225	G	3230	1521257	PISTON SPRING 	TEIJINSEIKI 	99101399 	CESSNA	402 	402C 	207590R	CE 										NLG ACTUATOR	BROKEN 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			WP	19	816AN				806	402C0261				ON LANDING, NOSE GEAR COLLAPSED. INSPECTION OF LANDING GEAR AND COMPLIANCE WITH MEB91-12 RESULTED IN NO DEFECTS NOTED I	N GEAR SYSTEM. REMOVED AND SENT NOSE GEAR ACTUATOR OUT FOR INSPECTION. TEAR-DOWN REVEALED LOCK INDICATOR PISTON SPRING	 BROKEN.				1	L	7	2 	3O				A7CE 					 
1995032000761	19950320	00761		1995	3	20	95ZZZX1277 	4	19950309	G	2562	EB2BCD	ELT 	MARTECH 																BATTERY	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99					15018					THIS ELT HAS HAD 2 BATTERY PACKS CORRODE AND DAMAGE ELT IN THE LAST 2 YEARS AND HAS BEEN RETURNED TO FACTORY FOR REPAIR.	 FACTORY INSTALLED BATTERIES. ANOTHER LIKE UNIT HAS HAD 3 BATTERIES CORRODE AND DAMAGE UNIT IN PAST 3 YEARS, 2 OF THOS	E BATTERIES WERE FACTORY INSTALLED.																	 
1995032000762	19950320	00762	SO 	1995	3	20	95ZZZX1278 	1	19950228	G	7810	3121202	PIPE 			PIPER 	PA23 	PA23250 	7102308	SO 										LT EXH CROSSOVER	CHAFES 	B			DSBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	13981					274599				EXHAUST CROSSOVER PIPE IS CHAFING LOWER COWL AND LOWER PART OF NOSE BOWL. THIS IS FROM ENGINE SAG AND VIBRATION. POSSI	BLE PREVENTION WOULD BE TO SHIM MOUNTS OR SOME MODIFICATION OF EXHAUST PIPE.					1	L	7	2 	3O				1A10 					 
1995032000763	19950320	00763	SO 	1995	3	20	95ZZZX1279 	1	19950228	G	7810	3122605	CROSSOVER PIPE 			PIPER 	PA23 	PA23250 	7102308	SO 										RT EXHAUST	CHAFE COWL 	B			DSBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	13981					274599				EXHAUST CROSSOVER PIPE IS CHAFING LOWER COWL AND LOWER PART OF NOSE BOWL. THIS IS FROM ENGINE SAG AND VIBRATION. POSSI	BLE PREVENTION WOULD BE TO SHIM MOUNTS OR SOME MODIFICATION OF EXHAUST PIPE.					1	L	7	2 	3O				1A10 					 
1995032000764	19950320	00764	EA 	1995	3	20	95ZZZX1280 	2	19950209	G	7414	M3525	COIL 	SLICK 	4281 	CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					LT MAG	DEFECTIVE 	B			OF1R	A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			EA	25	89414	2596 			042090	15282737	L2230215			ENGINE LOST 125 RPM IN-FLIGHT, LANDED WITHOUT INCIDENT, MAG CHECK REVEALED LT MAGNETO DEAD. TROUBLESHOT AND FOUND NO DE	FECTS IN MAG AFTER DISASSEMBLY. REPLACED COIL AND RAN UP AND OPS CHECKED OKAY.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995032000765	19950320	00765		1995	3	20	95ZZZX1281 	4	19950303	G	6113	D4247	BULKHEAD 			BEECH 	23 	C23 	1151242	CE 										SPINNER	CRACKED 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	6700G	72 				M2227				DURING PROPELLER REMOVAL, FOUND CRACKS AT EACH BOLT HOLE. BULKHEAD WAS INSTALLED WITH NEW A-4227-1 SHOULDER WASHERS AT I	NITIAL INSTALLATION 72 HOURS PRIOR. SUSPECT CRACKS DUE TO POOR DESIGN AND POOR MANUFACTURING.					1	L	7	1 	3O				A1CE 					 
1995032000766	19950320	00766	SO 	1995	3	20	95ZZZX1282 	1	19950215	G	5740	62448002	FITTING 			PIPER 	PA28 	PA28140 	7102802	SO 										LT WING SPAR AFT	CORRODED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	3961K	4327 				2823841				DURING AN ANNUAL INSPECTION, LEFT AND RIGHT WING REAR ATTACH FITTINGS WERE FOUND TO HAVE CONSIDERABLE AMOUNT OF CORROSIO	N ON LOWER PORTION OF FITTINGS. PIPER SB 977 PERTAINS TO THIS MATTER. ALSO, NOTED WAS CORROSION FOUND ON BOTH FITTINGS	 WHERE THEY PASS THROUGH THE FUSELAGE TO THE AFT WING SPAR. THE ONLY WAY THIS CORROSION WOULD HAVE BEEN FOUND WAS BY RE	MOVAL OF THE FITTINGS. THIS AREA SHOWED APPROX THE SAME AMOUNT OF CORROSION AS DID THE LOWER PORTION OF THE FITTINGS.			1	L	7	1 	3O				2A13 					 
1995032000767	19950320	00767	SO 	1995	3	20	95ZZZX1283 	1	19950215	G	5740	62448003	FITTING 			PIPER 	PA28 	PA28140 	7102802	SO 										RT WING SPAR AFT	CORRODED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	3961K	4327 				2823841				DURING AN ANNUAL INSPECTION, LEFT AND RIGHT WING REAR ATTACH FITTINGS WERE FOUND TO HAVE CONSIDERABLE AMOUNT OF CORROSIO	N ON LOWER PORTION OF FITTINGS. PIPER SB 977 PERTAINS TO THIS MATTER. ALSO, NOTED WAS CORROSION FOUND ON BOTH FITTINGS	 WHERE THEY PASS THROUGH THE FUSELAGE TO THE AFT WING SPAR. THE ONLY WAY THIS CORROSION WOULD HAVE BEEN FOUND WAS BY RE	MOVAL OF THE FITTINGS. THIS AREA SHOWED APPROX THE SAME AMOUNT OF CORROSION AS DID THE LOWER PORTION OF THE FITTINGS.			1	L	7	1 	3O				2A13 					 
1995032000769	19950320	00769	EU 	1995	3	20	95ZZZX1285 	1	19950217	G	2720	68570631	CONTROL CABLE 			PARTEN	P68 	P68 	6780102	EU 										RUDDER	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	28FG	3494 				325180B				THESE CABLES WRE REMOVED TO COMPLY WITH PARTENAVIA SB 72. THE WEAR OCCURRED WHERE THE CABLE WAS ROUTED AROUND THE PHOTO	 PORT. THE ORIGINAL CONTROL CABLES DO NOT SEEM TO HAVE A GOOD SERVICE LIFE.					1	H	7	2 	3O			 	A31EU 					 
1995032000770	19950320	00770	EU 	1995	3	20	95ZZZX1286 	1	19950217	G	2720	68540693	CONTROL CABLE 			PARTEN	P68 	P68 	6780102	EU 										RUDDER	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	28FG					325180B				WEAR OCCURRED AT PULLEYS IN VERTICAL FIN. WEAR WAS NOT VISIBLE UNTIL REMOVED FROM AIRCRAFT. THE ORIGINAL CONTROL CABLE	S DO NOT SEEM TO HAVE A LONG SERVICE LIFE.					1	H	7	2 	3O			 	A31EU 					 
1995032000771	19950320	00771	EU 	1995	3	20	95ZZZX1287 	1	19950217	G	2730	685302101	CONTROL CABLE 			PARTEN	P68 	P68 	6780102	EU 										ELEVATOR	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	28FG	3494 				325180B				WEAR WAS AT PULLEYS UNDER FLOOR. WEAR WAS NOT VISIBLE UNTIL REMOVED FROM AIRCRAFT. IT APPEARS THAT THESE ORIGINAL CABL	ES DO NOT HAVE A GOOD SERVICE LIFE.					1	H	7	2 	3O			 	A31EU 					 
1995032000772	19950320	00772	CE 	1995	3	20	95ZZZX1288 	1	19950307	G	2930	228000128	LINE 			CESSNA	182 	TR182 	2072735	CE 										UNDER PANEL	CHAFED 	D				O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			WP	09	6449T	4016 				R18202028				DURING FLIGHT, CREW NOTED AMMETER SHOWING AN ERRATIC FULL SCALE DISCHARGE. SOON AFTER THE LANDING GEAR 'UP' LIGHT BEGAN	 BLINKING. HYDRAULIC FLUID WAS NOTED LEAKING FROM UNDER THE INSTRUMENT PANEL. THE GEAR WAS HAND PUMPED DOWN. MAINTENA	NCE FOUND PN 2280001-28 HYD LINE CHAFED BY THE THROTTLE CABLE CAUSING A PINHOLE LEAK. REPLACED LINE AND ROUTED IT AWAY 	FROM OTHER CABLES AND WIRES. SUBSEQUENT GEAR CYCLES OKAY.			1	H	7	1 	3O				3A13 					 
1995032000773	19950320	00773	EA 	1995	3	20	95ZZZX1289 	2	19950302	G	7414	104001667	CAM ASSY 	BENDIX 	D4RN2021 	CESSNA	172 	172 	2072402	CE 	LYC 	O320 	O320H2AD 	41508	EA 					MAIN BODY	CRACKED 	B			TY5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03					22596K					MAGNETO WAS OVERHAULED AND IMPULSE COUPLING WAS THE NEW SNAP RING TYPE AS SPECIFIED IN TCM MSB NR 645. MAG WAS INSTALLE	D ON ENGINE. ENGINE FIRED SEVERAL TIMES, BUT DID NOT START. THEN ENGINE WOULD NOT FIRE AT ALL. NO IMPULSE CLICKING NO	ISE WAS NOTED. MAG WAS REMOVED. IMPULSE FLYWEIGHTS SEEMED TO NOT BE ENGAGING THE STOP PINS. COUPLING REMOVED AND IT F	ELL APART IN 2 PIECES IN HAND. BROKEN-THROUGH TAPER. ANOTHER CRACK IN TAPER WAS NOTED. INSTALLATION OF COUPLING WAS P	ERFORMED IAW TCM SB NR 639.		1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995032000774	19950320	00774	EA 	1995	3	20	95ZZZX1290 	2	19950302	G	7414	104001679	CAM ASSY 	BENDIX 	D4LN3000 						LYC 	O360 	IO360A3B6 	41514	EA 					MAIN BODY	CRACKED 	B			TY5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03					1353					MAGNETO WAS DISASSEMBLED FOR OVERHAUL. PREVIOUSLY, HAD NEW SNAP RING IMPULSE COUPLING INSTALLED. COUPLING CAM ASSY APP	EARED TO BE IN GOOD CONDITION AND LOW TIME. CAM ASSY WAS INSPECTED IAW TCM MSB NR 645, SECT. I AND FOUND GOOD. THEN CA	M WAS MAGNAFLUX INSPECTED IAW MIL-STD1949A AND FOUND 1 CRACK AT CORNER OF KEYWAY AND AT LEAST 7 OTHER LONGITUDINAL CRACK	ED NEAR THE LARGE END OF CENTER TAPERED HOLE. DO NOT KNOW WHETHER COUPLING WAS INSTALLED IAW TCM SB NR 639.								3	O			1E10				 
1995032000775	19950320	00775		1995	3	20	95ZZZX1291 	2	19950302	G	7414	ES652	COIL 	BENDIX 	S4LN20 															MAG	DEFECTIVE 	B			TY5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03		50 			26557					MAG WAS OVERHAULED AND PUT IN SERVICE 12-94. NEW NR ES652 COIL WAS INSTALLED AT THAT TIME. COIL BECAME INTERMITTENT IN	 ABOUT 50 HOURS TIME IN SERVICE. COIL WAS REPLACED WITH NEW NR ES10-357164-1 WHICH SOLVED PROBLEM. OCCASIONALLY, MAG W	OULD QUIT COMPLETELY. COIL MFG. DATE - 11/90. COIL TESTED OKAY WITH OHM METER. COIL TESTED INTERMITTENT WIHT COIL TES	TER.																 
1995032000776	19950320	00776	CE 	1995	3	20	95ZZZX1292 	1	19950227	G	2460		SHIELDED WIRE 			BEECH 	23 	A23 	1151204	CE 										UNDER FLOOR	SHORTED 	D				K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			GL	17	1445L					M840				SHIELDED WIRE FROM INSTRUMENT PANEL TO AFT OF BAGGAGE COMPARTMENT UNDER FLOOR WAS NOT CONNECTED TO ANYTHING. SHIELDING 	WAS GROUNDED AT INSTRUMENT PANEL. WIRE WAS LOOSE IN AREA OF BATTERY BOX AND MASTER SWITCH. IN-FLIGHT, WIRE APPARENTLY 	TOUCHED AGAINST THE TERMINAL ON THE MASTER SWITCH CAUSING A DIRECT SHORT TO GROUND BURNING THE INSULATION ON THE WIRE IN	SIDE THE SHIELDING CAUSING SMOKE IN THE COCKPIT. RECOMMEND ANYTIME ELECTRICAL WIRES ARE DISCONNECTED, THEY BE REMOVED F	ROM THE AIRCRAFT.		1	L	7	1 	3O				A1CE 					 
1995032000777	19950320	00777	SW 	1995	3	20	95ZZZX1293 	1	19950301	G	3230	ES10119	SPACER 		750039 	GULSTM	500 	500S 	0141107	SW 										NLG	STUD FRACTURED 	D				O				OTHER 				P			NO WARNING INDICATION 			LD	LANDING 	1			SO	13	19WL					3160				PILOT REPORTED NO NOSE GEAR LIGHT. GROUND PERSONNEL REPORTED SEEING THE NOSE GEAR OUT. UPON LANDING, AIRCRAFT STARTED 	LEFT. WHEN CORRECTION WAS MADE, THE NOSE GEAR COLLAPSED. INVESTIGATION FOUND THE SHIMMY DAMPENER ROD END UNATTACHED AT	 THE STRUT COLLAR ASSEMBLY. ON EXTENSION OF THE GEAR, THE SHIMMY DAMPENER CONTACTED THE RADOME. THIS PREVENTED THE NOS	E GEAR FROM LOCKING INTO PLACE. SUSPECT CAUSE WAS NOSE GEAR TURNED PASSED THE TURNING LIMITS DURING GROUND HANDLING. R	OLL PIN SECURING THE MOUNTING STUD INSIDE SPACER ES10119 FRACTURED, ALLOWING THE STUD AND NUT TO DEPART THE AIRCRAFT.		1	H	7	2 	3O				6A1 					 
1995032000778	19950320	00778		1995	3	20	95ZZZX1294 	4	19950228	G	3416	3431	CASTING 	UNITEDINST 	5934PD1 	PIPER 	PA28 	PA28236 	7102815	SO 										ALTIMETER	CREEP 	B			EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	422DJ				P9631	287911281				THIS IS A FACTORY SEALED INSTRUMENT MFG IN 4-79. DISC POINTER HAD CIRCULAR SCRATCH WERE IT CONTACTED ONE OF THE DIAL SC	REWS. IN SIMILAR ALTIMETERS, PILOTS HAVE REPORTED HANG-UPS OF UP TO 1,000 FEET, IN DESCENT, DUE TO THIS PROBLEM. ONE C	RITICAL MECHANISM SHAFT HAD AN END SHAKE OF .0012 INCH, THE SPEC MIN IS .0020 INCH. A TENACIOUS BLACK DEPOSIT WAS SEEN O	N TRACKING AREA OF HAND STAFF PINION. A TENACIOUS YELLOW DEPOSIT WAS SEEN ON TRACKING SURFACE OF HAIR SPRING PINION. T	HESE DEPOSITS APPEARED TO BE A POLISHING ROUGE. HEAVY MOLY/KOTE WAS REMOVED FROM BEARING SURFACES OF THE TOP PLATE. WH	EN THIS DEPOSIT WAS REMOVED, FRICTION IN THE TOP PLATE WAS REDUCED TO ONE-SIXTH THE ORIGINAL VALUE.	1	L	7	1 	3O				2A13 					 
1995032000779	19950320	00779		1995	3	20	95ZZZX1295 	4	19950228	G	3416	34120C	DISC POINTER 	UNITEDINST 	5934PD1 	PIPER 	PA28 	PA28236 	7102815	SO 										BACK SURFACE	CHAFE SCREW 	B			EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	422DJ				P9631	287911281				THIS IS A FACTORY SEALED INSTRUMENT MFG IN 4-79. DISC POINTER HAD CIRCULAR SCRATCH WERE IT CONTACTED ONE OF THE DIAL SC	REWS. IN SIMILAR ALTIMETERS, PILOTS HAVE REPORTED HANG-UPS OF UP TO 1,000 FEET, IN DESCENT, DUE TO THIS PROBLEM. ONE C	RITICAL MECHANISM SHAFT HAD AN END SHAKE OF .0012 INCH, THE SPEC MIN IS .0020 INCH. A TENACIOUS BLACK DEPOSIT WAS SEEN O	N TRACKING AREA OF HAND STAFF PINION. A TENACIOUS YELLOW DEPOSIT WAS SEEN ON TRACKING SURFACE OF HAIR SPRING PINION. T	HESE DEPOSITS APPEARED TO BE A POLISHING ROUGE. HEAVY MOLY/KOTE WAS REMOVED FROM BEARING SURFACES OF THE TOP PLATE. WH	EN THIS DEPOSIT WAS REMOVED, FRICTION IN THE TOP PLATE WAS REDUCED TO ONE-SIXTH THE ORIGINAL VALUE.	1	L	7	1 	3O				2A13 					 
1995032400059	19950324	00059	CE 	1995	3	24	95ZZZX1303 	1	19950113	G	5312	05130079	BULKHEAD 			CESSNA	172 	172F 	2072414	CE 										FWD OF DR POST	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	7843U	3656 				17251843				DURING REPLACEMENT OF THE FIREWALL, THE FORWARD BULKHEAD OF THE FRONT DOOR POST BULKHEAD ASSEMBLY WAS FOUND CRACKED. TH	ERE WAS A CRACK APPROXIMATELY 3 INCHES IN LENGTH WHERE THE ELEVATOR CONTROL BRACKET ATTACHES TO THE BULKHEAD. THE CRACK	 APPEARS TO HAVE ORIGINATED FROM THE UPPER RIVET THAT ATTACHES THE BRACKET TO THE BULKHEAD. REPLACEMENT OF PART AS FIX.				1	H	7	1 	3O			NT	3A12 					 
1995032400063	19950324	00063	EA 	1995	3	24	95ZZZX1307 	1	19950214	G	5730		SKIN 			SCWZER	G164 	G164A 	3952704	EA 										RT WING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	9041Q	3776 				1697				CRACK IN WING SKIN, EMANATING FROM NOSE PIECE SUPPORT OF AUTO FLAGGER. THIS ITEM INSTALLED IN WING SKIN AFT OF FRONT SP	AR. SUBMITTER STATED DRAWING REQUIRES THIS ITEM BE LOCATED/INSTALLED IN UPPER REAR FLANGE OF FRONT SPAR: FOLLOW INSTRU	CTIONS WHEN INSTALLING EQUIPMENT!! FLAGGER PN MDL4, SN 6323.				1	Q	7	1 	3R				1A16 					 
1995032400064	19950324	00064	CE 	1995	3	24	95ZZZX1308 	1	19950302	G	3230		SCISSORS 			CESSNA	421 	421B 	2076014	CE 										MLG LT	FAILED 	G		A		O				OTHER 				O			OTHER 			LD	LANDING 	1			EA	01	918WK	3137 				421B0956				LEFT MLG COLLAPSED ON LANDING ROLL. GEAR COLLAPSED DUE TO SCISSORS BOLT AND BUSHINGS SLIDING OUT OF SCISSORS, THEREFORE	, ALLOWING MAIN WHEEL TO ROTATE SIDEWAYS AND SUBSEQUENTLY BREAKING GEAR FROM ITS MOUNT. INVESTIGATION REVEALED CORRECT 	HARDWARE INSTALLED AT SCISSORS (IAW PARTS MANUAL), HOWEVER, CORRECT WASHER WILL ALLOW BOLT, WASHERS, AND BUSHINGS TO SLI	DE OUT OF SCISSORS. SUBMITTER STATES CESSNA DOES HAVE A SERVICE KIT TO PREVENT THIS AND IS HIGHLY RECOMMENDED.			1	L	7	2 	3O				A7CE 					 
1995032400065	19950324	00065	EA 	1995	3	24	95ZZZX1309 	2	19950216	G	7414	ES10357424	DIST BLOCK 	BENDIX 	S4LN200 	MOONEY	M20 	M20F 	5870214	SW 	LYC 	O360 	IO360A1A 	41514	EA 					MAGNETO	LOOSE BUSHING 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	3205F	971 			409402	680002	RL274451A			ON DISASSEMBLING THE MAG FOR INSPECTION, THE CENTER BRONZE BUSHING IN THE DISTRIBUTOR BLOCK WAS FOUND LOOSE IN THE PLAST	IC MATERIAL OF THE BLOCK. THIS IS THE SECOND ELECTRO SYSTEMS DISTRIBUTOR BLOCK FOUND IN THIS CONDITION IN LAST MONTH, T	HE OTHER BLOCK WAS P/N ES10-357426.				1	L	7	1 	3O	3	O		2A3 	1E10				 
1995032400067	19950324	00067	SO 	1995	3	24	95ZZZX1311 	1	19950228	G	2700		CONTROL CABLE 			PIPER 	PA18 	PA18A 	7101804	SO 										SLEEVE	MISMANUFACTURED 	B			SPDR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11										DURING AN ANNUAL INSPECTION ON A PIPER SUPPER CUB PA-18A, FOUND NEW STAINLESS CABLES HAD BEEN PREVIOUSLY INSTALLED. INSP	ECTION OF THE CABLES SHOWED THE COPPER N1COMPRESS SLEEVES WERE INSTALLED ON THE STAINLESS CABLES IN PLACE OF THE SILVER 	COLORED N1COMPRESS SLEEVES -- THIS SILVER IN COLOR N1COMPRESS SLEEVE IS TO BE USED ON STAINLESS CABLES TO PREVENT DISSIM	ILAR METAL CORROSION CALLED ELECTROLYSIS, A MORE IN-DEPTH INSPECTION REVEALED THE N1COMPRESS SLEEVE WAS VERY SLOPPILY IN	STALLED AND SEVERAL N1COMPRESS SLEEVES ONLY HAD TWO CRIMPS INSTEAD OF THREE. SUBMITTER SUGGESTS WHEN NOT SURE, MAKE REF	ERENCE TO A.C. 43.13/4.	1	H	7	1 	3O			 	1A2 					 
1995032400070	19950324	00070	EA 	1995	3	24	95ZZZX1314 	2	19950130	G	7414	10507464	DISTRIBUTOR GEAR	BENDIX 	S4LN204 	ENSTRM	F28 	F28A 	3300406	GL 	LYC 	O360 	IO360C1A 	41514	EA 					RT MAG	TEETH FAILED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			WP	13	9087		603 		8017066	211	L1627651AC			TEN MINUTES INTO A TOUR FLIGHT, ENGINE BECAME MOMENTARILY ROUGH. UPON RETURNING TO THE HELIPAD, A MAG CHECK REVEALED TH	E RIGHT MAG WAS DEAD. UPON REMOVAL AND INSPECTION, FOUND MORE THAN HALF OF THE PLASTIC TEETH WERE MISSING (BROKEN OFF) 	OF THE LARGE DISTRIBUTOR GEAR.				1	G	7	1 	3O	3	O		H1CE 	1E10				 
1995032400072	19950324	00072	WP 	1995	3	24	95ZZZX1316 	1	19950130	G	3213	369H600151	STRUT ASSY 			HUGHES	369 	369HS 	4470728	WP 										AFT LT GEAR	CRACKED 	B		A	CYHR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	91GG	13200				690S				AFTER FLIGHT, THE PILOT NOTED THAT THE HELICOPTER WAS SITTING VERY LOW ON THE AFT LEFT SIDE. AN INSPECTION WAS CONDUCTE	D AND FOUND AFT LEFT LANDING GEAR STRUT ASSY CRACKED AT THE INSIDE RIVET HOLE. THE RIVET ATTACHES THE SUPPORT FOR THE L	OWER GUIDE AND FILLET. PREVIOUS INSPECTION IN THIS AREA SHOWED NO CRACKS. SUSPECT CAUSE HIGH TIME ON THE ASSY.				1	G	7	1 	3U				H3WE 					 
1995032400077	19950324	00077	SW 	1995	3	24	95ZZZX1321 	1	19950217	G	2730	2744046037	CONTROL QUADRANT			SWRNGN	SA227 	SA227AC 	8780603	SW 										ELEVATOR	BEARING SEIZED 	B		A	NF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	58NE	9817 				758B				WHILE REPLACING PRIMARY CONTROL CABLES PER AD 87-02-2, CORROSION WAS EVIDENT AT ELEVATOR CABLE ATTACH HORN BOLT HOLES. F	URTHER INVESTIGATION AFTER QUADRANT REMOVAL FOR CORROSION REPAIR SHOWED FROZEN PIVOT BEARING PRESSED INTO MAGNESIUM CAST	ING. ATTEMPTS TO REMOVE BEARING FOR REPLACEMENT WERE UNSUCCESSFUL USING HEAT, PENETRANT, AND HYDRAULIC PRESS. CASTING 	EVENTUALLY FAILED AND BECAME UNSERVICEABLE. BEARING NEVER EVEN BUDGED. SUBSTANTIAL CORROSION BETWEEN STEEL BEARING AND	 MAGNESIUM CASTING WAS OBVIOUS. BEARING PN KP4.		1	L	7	2 	4T				A8SW 					 
1995032400078	19950324	00078	NM 	1995	3	24	95ZZZX1322 	1	19950302	G	3340	3017003	LIGHT ASSY 	GRIMES 		ISRAEL	1125 	1125 		NM 										WING TIP	BASE BREAKS 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	90UG	2821 				030				UPON REMOVAL OF WING TIP FOR PAINT, WIRING MUST BE DISCONNECTED FROM LIGHT. DUE TO LIMITED ACCESS, THE SOCKET BASE, MA	NUFACTURED OF A PLASTIC OR COMPOSITE, CANNOT BE FURTHER SUPPORTED, AND THE BASE BREAKS.					2	L	7	2 	4F			RT	A16NM 					 
1995032400079	19950324	00079	NM 	1995	3	24	95ZZZX1323 	1	19950302	G	3340	3017003	LIGHT ASSY 	GRIMES 		ISRAEL	1125 	1125 		NM 										WING TIP	BASE BREAKS 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	30AJ				021	047				UPON REMOVAL OF WING TIP FOR PAINT, WIRES MUST BE DISCONNECTED FROM LIGHT. DUE TO LIMITED ACCESS, THE SOCKET BASE, MANU	FACTURED OF A PLASTIC OR COMPOSITE, CANNOT BE FURTHER SUPPORTED, AND BASE BREAKS. SUBMITTER SUGGESTS A QUICK DISCONNECT	 IN WIRING SO SCREW REMOVAL IS NOT NECESSARY.				2	L	7	2 	4F			RT	A16NM 					 
1995032400080	19950324	00080	CE 	1995	3	24	95ZZZX1324 	1	19950201	G	3233	26558027522	CYLINDER HEAD 		30658012612 	RKWELL	NA265 	NA26540 	6402608	CE 										RT MLG ACTUATOR	HOLE BROKEN 	D	S	A		O				OTHER 				J	E		WARNING INDICATION 	VIBRATION/BUFFET 		CL	CLIMB 	1			CE	03	333NM	9632 			0L28	28245				FLIGHT ORIGINATED IN ROCHESTER, MN (RST). ON TAKEOFF CLIMB, WHEN GEAR HANDLE WAS PLACED IN UP POSITION, RED LIGHTS IN G	EAR HANDLE STARTED FLASHING AND AIRCRAFT STARTED VIBRATING. CYCLED LANDING GEAR WITH SAME RESULTS. CONTINUED FLIGHT AT	 180 KNOTS AND LANDED AT PERRYVILLE AIRPORT (K02). FOUND BROKEN RT MLG ACTUATOR AT INBD ATTACH POINT FROZEN UP AND RUST	Y. IMPROPER INSPECTION INTERVALS AND IMPROPER RIGGING OF MLG. THIS COULD HAVE BEEN A CATASTROPHIC INCIDENT. RECOMMEND	 FOLLOWING INSPECTION AND MAINTENANCE PRACTICES OF MM. LANDINGS, 6,518.		2	L	7	2 	4J				A2WE 					 
1995032400081	19950324	00081	CE 	1995	3	24	95ZZZX1325 	1	19950305	G	2160	465M0126K1	SENSOR FAN 			CESSNA	650 	650 	2076802	CE 										CABIN TEMP AFT	INOP 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	38WP					6500032				CABIN TEMP INDICATES MID-50'S REGARDLESS OF 'REAL' TEMP IN CABIN. SEEMS TO RUN FULL-HOT IN AUTOMATIC, OKAY IN MANUAL. D	ISCOVERED AFT SENSOR FAN DEAD. REPLACED AFT SENSOR FAN AND ON RUN-UP, TEMPERATURE CONTROL FUNCTIONED NORMAL IN AUTO AND	 MANUAL.				2	L	7	2 	4F				A9NM 					 
1995032400134	19950324	00134	SW 	1995	3	24	95ZZZX1326 	1	19950305	G	7810	206064300005	STACK 			BELL 	206 	206L4 	1182110	SW 										EXHAUST WELD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	404W	597 				52055				EXHAUST STACK CRACKED IN WELD SEAM AT 2 LOCATIONS. REPLACED STACK ASSEMBLY.						1	G	7	1 	3U			NC	H2SW 					 
1995032400135	19950324	00135	SW 	1995	3	24	95ZZZX1327 	1	19950303	G	6230	206040036005	BEARING 			BELL 	206 	206B3 	1181506	SW 										M/R MAST	MISINSTALLED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	09	5743H	2962 	2435 			3042				UPON INSPECTION OF M/R MAST BEARING DUE TO METAL CONTAMINATION, IT WAS DISCOVERED THE BEARING HAD BEEN INSTALLED UPSIDE 	DOWN AND THE INNER RACE WAS DAMAGED BEYOND LIMITS. BELL INSTRUCTIONS ARE SPECIFIC ON THE ORIENTATION OF THE BEARING ON 	INSTALLATION.				1	G	7	1 	3U				H2SW 					 
1995032400136	19950324	00136	EU 	1995	3	24	95ZZZX1328 	1	19950222	G	6210	117150071	BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	BULGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	214AE	4103 			713	7206				MAIN ROTOR BLADE BALANCE WEIGHT IS COMPRESSING DUE TO CENTIFUGAL FORCE WHICH CAUSES A BULGE IN THE BLADE OUTER SKIN BEYO	ND MFG'S LIMITS, RENDERING THE BLADE UNSERVICEABLE.					1	G	7	2 	3U				H13EU 					 
1995032400137	19950324	00137	SW 	1995	3	24	95ZZZX1329 	1	19950105	G	5320	205030280127	SERVICE DECK 			BELL 	212 	212 	1181420	SW 										LT ENGINE	VOIDS 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	754H					35034				DURING ROUTINE INSPECTION, FOUND LT ENGINE SERVICE DECK VOIDED 6 INCHES BY 8 INCHES (OVAL). RECOMMEND INCREASING ADHESI	VE STRENGTH IN BONDED HONEYCOMB PANELS BY MFG.					1	G	7	1 	4U				H4SW 					 
1995032400138	19950324	00138	SW 	1995	3	24	95ZZZX1330 	1	19950112	G	6210		BLADE 			BELL 	212 	212 	1181420	SW 										M/R	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	736H	2963 			A2189	35048				DURING INSPECTION, FOUND 9 INCH CRACK ON LOWER SIDE, 7 FEET FROM ROOT END.						1	G	7	1 	4U				H4SW 					 
1995032400268	19950324	00268	EA 	1995	3	24	95ZZZX1334 	2	19950308	G	7310	3022660	ACCUMULATOR 			SKRSKY	S58T 	S58JT 	8141807	NE 	PWA 	PT6T 	PT6T6 	52045	EA 					FUEL	LEAKING 	H			JSYL	K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			NM	09	581SR					581539	CPPS72005			DURING POWER PLANT OPERATION, FUEL ACCUMULATOR STARTED TO LEAK FUEL FROM THE FRONT SEAM. ACCUMULATOR WAS REPLACED AT TH	AT TIME.					2	G	7	2 	4U	4	U		1H11 	E22EA				 
1995032400269	19950324	00269	NE 	1995	3	24	95ZZZX1335 	1	19950201	G	6410	S6117030201041	BLADE 			SKRSKY	S61 	S61A 	814210C	NE 										T/R	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1048Y	9141 			61VR893890	61161				TAIL ROTOR BLADE SKIN CRACK OUTBOARD SIDE APPROXIMATELY 18 INCHES FROM ROOT END OF BLADE. SUBMITTER RECOMMENDATION - CL	EAN AND INSPECT DAILY PER SIKORSKY INSPECTION PROGRAM.					2	G	7	2 	4U				H2EA 					 
1995032400270	19950324	00270	NE 	1995	3	24	95ZZZX1336 	1	19950201	G	6410	6117030201041	BLADE 			SKRSKY	S61 	S61A 	814210C	NE 										T/R	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1048Y				61VR901898	61161				TAIL ROTOR BLADE SKIN CRACK OUTBOARD SIDE APPROXIMATELY 20 INCHES FROM ROOT END OF BLADE. RECOMMENDATIONS - CLEAN AND I	NSPECT DAILY PER SIKORSKY INSPECTION PROGRAM.					2	G	7	2 	4U				H2EA 					 
1995032400271	19950324	00271	NE 	1995	3	24	95ZZZX1337 	1	19950201	G	6410	6117030201041	BLADE 			SKRSKY	S61 	S61A 	814210C	NE 										T/R	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1043T	5757 			61VR899895	61083				TAIL ROTOR BLADE SKIN CRACK OUTBOARD SIDE APPROXIMATELY 20 INCHES FROM ROOT END OF BLADE. RECOMMENDATIONS - CLEAN AND I	NSPECT DAILY PER SIKORSKY INSPECTION PROGRAM.					2	G	7	2 	4U				H2EA 					 
1995032400272	19950324	00272	NE 	1995	3	24	95ZZZX1338 	1	19950201	G	6410	6117030201041	BLADE 			SKRSKY	S61 	S61A 	814210C	NE 										T/R	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1043T	9491 			61VR896892	61083				TAIL ROTOR BLADE SKIN CRACK OUTBOARD SIDE APPROXIMATELY 19 INCHES FROM ROOT END OF BLADE. SUBMITTER RECOMMENDATIONS - C	LEAN AND INSPECT DAILY PER SIKORSKY INSPECTION PROGRAM.					2	G	7	2 	4U				H2EA 					 
1995032400273	19950324	00273	NE 	1995	3	24	95ZZZX1339 	1	19950201	G	6410	S6117030101045	BLADE 			SKRSKY	S61 	S61N 	8142104	NE 										T/R	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	9119S	7827 				61703				TAIL ROTOR BLADE HAS A SKIN CRACK .25 INCH LONG ON INBOARD SKIN 11.50 INCHES FROM ROOT OF BLADE NEAR TRAILING EDGE. SUB	MITTER RECOMMENDATIONS - CLEAN AND INSPECT BLADE DAILY.					2	G	7	2 	4U				1H15 					 
1995032400274	19950324	00274	NE 	1995	3	24	95ZZZX1340 	1	19950201	G	6420	SB15002	BEARING 			SKRSKY	S61 	S61A 	814210C	NE 										T/R HEAD	WORN 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1048Y	1817 			A12911	61161				BEARING INNER RACE HAD METAL REMOVED, APPROXIMATELY .0625 INCH WIDE BY .1875 INCH LONG. OUTER RACE HAD SMALL INDENTATIO	NS FROM BALL BEARINGS WITH NO METAL REMOVAL. BALL BEARINGS APPEARED NORMAL. SIKORSKY AIRCRAFT SAID THIS IS CAUSED FROM	 LACK OF PROPER LUBRICATION. HAVE INSTRUCTED CREWS TO PURGE BEARINGS IAW SIKORSKY MM.				2	G	7	2 	4U				H2EA 					 
1995032400275	19950324	00275	NE 	1995	3	24	95ZZZX1341 	1	19950201	G	6320	S6135200605	REAR COVER 			SKRSKY	S61 	S61N 	8142104	NE 										MAIN GEARBOX	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	9119S		1614 		A14A2464580	61703				REAR COVER LEFT SIDE LOWER WEB HAS 1 INCH CRACK ON FORWARD SIDE 5.25 INCHES INBOARD OF MOUNT BOLT. SUBMITTER STATED PER	FORM INSPECTION PER SAFETY CHECK 1, ITEM 13.					2	G	7	2 	4U				1H15 					 
1995032400276	19950324	00276	NE 	1995	3	24	95ZZZX1342 	1	19950201	G	5415	S6120661172	HINGE 			SKRSKY	S61 	S61A 	814210C	NE 										PYLON	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	318Y		5522 		A12176	61094				UPPER PYLON HINGE LT EAR CRACKED THROUGH BOLT HOLE. HINGE WAS FOUND DURING WALK-AROUND INSPECTION AT FUEL STOP. THIS W	AS 3.7 HOURS AFTER PRE-FLIGHT INSPECTION AND 23.6 HOURS AFTER AD 76-08-01 WAS C/W. SUBMITTER RECOMMENDATIONS - KEEP HIN	GE BUSHINGS TIGHT AND SHIM AS REQUIRED, REPLACE BOLTS WHEN WORN. DO VISUAL INSPECTION AS OFTEN AS POSSIBLE.				2	G	7	2 	4U				H2EA 					 
1995032400277	19950324	00277	NE 	1995	3	24	95ZZZX1343 	1	19950201	G	6320	S6135200606	REAR COVER 			SKRSKY	S61 	S61A 	814210C	NE 										MAIN GEARBOX	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1043T	22249	1022 			61083				REAR COVER WAS FOUND CRACKED ON NR 2 GENERATOR BOSS. THIS WAS A SURFACE CRACK ON INSIDE OF GEARBOX REAR COVER, AND WAS 	FOUND AT OVERHAUL.					2	G	7	2 	4U				H2EA 					 
1995032400282	19950324	00282	SW 	1995	3	24	95ZZZX1348 	1	19950307	G	2621	209062908001	EXTINGUISHER 			BELL 	412 	412 	1182202	SW 										NR 1 ENGINE	DISC FAILED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2FOR	3849 				33213				AIRCRAFT WAS PARKED. FIRE EXTINGUISHER DISCHARGED. UPON REMOVAL, FOUND FRANGIBLE DISC RUPTURED. THE SQUIB WAS NOT DIS	CHARGED. THE FRANGIBLE DISC FAILED. THE FIRE EXTINGUISHER WAS HYDROSTATICALLY TESTED AND SERVICED JANUARY, 1990.					1	G	7	2 	4U				H4SW 					 
1995032400283	19950324	00283	NE 	1995	3	24	95ZZZX1349 	1	19950210	G	6230	SR192L	INSERT 			SKRSKY	S76 	S76A 	8143006	NE 										SWASHPLATE	NOT STAKED 	B			ALGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										ON INSPECTION WHEN REMOVING 76104-08013-101 RETAINER HARDWARE, 2 EACH INSERTS, PN SR 192L, BACKED OUT OF STATIONARY SWAS	HPLATE. OTHER INSERTS WERE FOUND NOT PROPERLY STAKED.					1	G	7	2 	3U				H1NE 					 
1995032400284	19950324	00284	NE 	1995	3	24	95ZZZX1350 	1	19950210	G	6230	SB5007102	BEARING 			SKRSKY	S76 	S76A 	8143006	NE 										UNIBALL	MISMANUFACTURED 	B			ALGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										ON INSPECTION WHEN INSTALLING NEW UNIBALL INTO STATIONARY SWASHPLATE, UNIBALL (OUTER RACES) WOULD NOT FIT INTO SWASHPLAT	E DUE TO THE SHIM BEING BONDED ON INCORRECTLY. ALSO, OUTER RACES HAD EXCESSIVE PAINT CAUSING A 'TOO TIGHT' FIT. COMPON	ENT PN 7610408010043.				1	G	7	2 	3U				H1NE 					 
1995032400285	19950324	00285	SW 	1995	3	24	95ZZZX1351 	1	19950307	G	6320	S1635200592	SHAFT 		S16352000017	SKRSKY	S58T 	S58T 	8141800	SW 										TRANSMISSION	CRACKED 	H			GKIG	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	1078T	2452 			3697	581016				TRANSMISSION DISASSEMBLED FOR OVERHAUL. PERFORMED MAGNAFLUX INSPECTION OF MAST FOLLOWING STRUCTURAL FAILURE OF ANOTHER 	MAST IN ANOTHER AIRCRAFT. FOUR INCH CRACK INDICATION FOUND BEGINNING AT DOWEL PIN HOLE TO UNDERCUT IN MAST BASE THEN UP	 MAST THROUGH BEARING MOUNT AREA. AIRCRAFT HAS BEEN LOGGING FOR THE LAST 1,210 HOURS.				2	G	7	1 	4U			NC	1H11 					 
1995032400286	19950324	00286	SW 	1995	3	24	95ZZZX1352 	1	19950307	G	6320	S1635200592	SHAFT 		S16352000017	SKRSKY	S58T 	S58T 	8141800	SW 										TRANSMISSION	CRACKED 	H	S		GKIG	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	1099T	2499 			3732	581646				TRANSMISSION DISASSEMBLED FOR OVERHAUL. PERFORMED MAGNAFLUX INSPECTION OF MAST FOLLOWING STRUCTURAL FAILURE IN ANOTHER 	AIRCRAFT; .3750 INCH CRACK INDICATION FOUND BEGINNING AT DOWEL PIN HOLE TO UNDERCUT AT MAST BASE. AIRCRAFT HAS BEEN LOG	GING FOR THE LAST 1146 HOURS.				2	G	7	1 	4U			NC	1H11 					 
1995032400287	19950324	00287	SO 	1995	3	24	95ZZZX1353 	1	19950314	G	3221		BOLT 		7642603 	PIPER 	PA28 	PA28R200 	7102811	SO 										NLG DRAG LINK	MISINSTALLED 	H			KO8V	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	17	4995S					28R35720				BOTH UPPER DRAG LINK TO ENGINE MOUNT ATTACHING BOLTS INSTALLED BACKWARDS. BOLT HEADS FACING OUTBOARD, NUTS VISIBLE IN C	ENTER OF WHEELWELL. LARGE DIAMETER STEEL WASHERS AND TEFLON WASHER MISSING. PARTS MANUAL OR SERVICE MANUAL CLEARLY DEP	ICT HARDWARE ARRANGEMENT. FAR 141.				1	L	7	1 	3O				2A13 					 
1995032400289	19950324	00289	CE 	1995	3	24	95ZZZX1355 	1	19950307	G	7922	75944	VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	1851Z		1065 		34139	M2343				WHILE COMPLYING WITH LYCOMING SB 518A FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. SUBMITTER SUGGESTS CRIMP NU	T LOOSE DUE TO POOR DESIGN.					1	L	7	1 	3O				A1CE 					 
1995032400290	19950324	00290		1995	3	24	95ZZZX1356 	4	19950307	G	6113	D4247	BULKHEAD 			TCRAFT	19 	19 	9230702	GL 										SPINNER	CRACKED 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	5112R	498 				MB646				DURING PROPELLER REMOVAL, FOUND CRACKS AT EACH BOLT HOLE. BULKHEAD WAS INSTALLED WITH NEW A-4227-1 SHOULDER WASHERS AT 	INITIAL INSTALLATION 498.1 HOURS PRIOR. SUSPECT CRACKS DUE TO POOR MANUFACTURING. SUBMITTER SUGGESTS THIS REPAIR STATI	ON HAS REPLACED MANY BULKHEADS WITH CRACKS AT VERY LOW TIMES.				1	H	7	1 	3O				1A9 					 
1995032400291	19950324	00291	SO 	1995	3	24	95ZZZX1357 	1	19950224	G	7922	75944	VALVE 			PIPER 	PA28 	PA28R201 	7102816	SO 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	9436C		425 			28R7837198				WHILE COMPLYING WITH LYCOMING SB 518A, FOUND CRIMP NUT LOOSE SHOWN IN STEP 2 OF BULLETIN. SUBMITTER SUGGESTS CRIMP NUT 	LOOSE DUE TO POOR DESIGN.					1	L	7	1 	3O				2A13 					 
1995032400292	19950324	00292	CE 	1995	3	24	95ZZZX1358 	1	19950223	G	7922	75944	VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	65503		296 			M2378				WHILE COMPLYING WITH LYCOMING SB 518A, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. SUBMITTER SUGGESTS CRIMP N	UT LOOSE DUE TO POOR DESIGN.					1	L	7	1 	3O				A1CE 					 
1995032400293	19950324	00293	CE 	1995	3	24	95ZZZX1359 	1	19950228	G	7922	75944	VALVE 			CESSNA	150 	152 	2071835	CE 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	4829P		936 		100951	15284824				WHILE COMPLYING WITH LYCOMING SB 518A, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. SUBMITTER SUGGESTS CRIMP N	UT LOOSE DUE TO POOR DESIGN.					1	H	7	1 	3O			NT	3A19 					 
1995032400294	19950324	00294	CE 	1995	3	24	95ZZZX1360 	1	19950309	G	7922	75944	VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	5117R		1603 		88802	M1946				WHILE COMPLYING WITH LYCOMING SB 518A, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. SUBMITTER SUGGESTS CRIMP N	UT LOOSE DUE TO POOR DESIGN.					1	L	7	1 	3O				A1CE 					 
1995032400404	19950324	00404	CE 	1995	3	24	95ZZZX1361 	1	19950309	G	2810		CAP 			CESSNA	177 	177RG 	2073709	CE 										FUEL TANK	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	35850					177RG1061				REPLACED ORIGNAL GAS CAP WITH CAPS MFG BY MONARCH AIR & DEVELOPMENT, INC., AND APPROVED BY FAA STC SA2458CE.						1	H	7	1 	3O				A20CE 					 
1995032400405	19950324	00405	SO 	1995	3	24	95ZZZX1362 	1	19950302	G	3211		BOLT 			PIPER 	PA28 	PA28RT201 	7102818	SO 										MLG TRUNNION	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	2859D					28R7918204				DURING A 100-HOUR INSPECTION THE 4 EACH AN5-11A BOLTS THAT MOUNT THE FORWARD MLG TRUNNIONS, PN 67040-14 LEFT, AND PN 670	40-15 RIGHT, TO THE MAIN INBOARD WING SPAR, PN 67069-22 LEFT, AND PN 67069-03 RIGHT, WERE FOUND BACKING OUT. AN5-11A BO	LTS WERE BACKED OUT 1 TO 3 THREADS, LEAVING THE LANDING GEAR IN AN UNSTABLE AND UNSAFE CONDITION.				1	L	7	1 	3O				2A13 					 
1995032400406	19950324	00406	EA 	1995	3	24	95ZZZX1363 	2	19950228	G	8530	73806P	PUSH ROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					ENGINE CYLNDER	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	6145K					15285553	L232U415			FOUND 1 BROKEN AND 3 OTHERS CRACKED. ALL DAMAGE ON END OF THE TUBE NEAR INSERT OPPOSITE END OF TUBE WHERE PART NUMBER I	S LOCATED. AD95-03-10 PERTAINS TO ASSEMBLY NR 73806 AND 'V' OR 'W' REVISION. PART TT UNKNOWN.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995032400408	19950324	00408		1995	3	24	95ZZZX1365 	4	19950202	G	2215	12531	TENSION WASHER 		0106R9 	CESSNA	172 	172P 	2072436	CE 										SERVO CLUTCH	CORRODED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	99930	2000 			6146A	17276528				ROLL SERVO WOULD NOT ENGAGE. REMOVED SERVO. UPON INSPECTION, DISCOVERED ROLL PIN ON OUTPUT GEAR WAS SHEARED. REPLACED	 PIN AND DURING TORQUE TEST, FOUND TORQUE EXTREMELY HIGH (80 INCHES\POUNDS). DISASSEMBLED CLUTCH AND FOUND CORROSION ON	 TENSION WASHERS. REPLACED 3 DEFECTIVE WASHERS, RESET TORQUE MFG SPECS. SUBMITTER SUGGESTS CORROSION TO BE CAUSE OF IN	CREASED TORQUE. A PERIODIC INSPECTION OF THE SERVO (INCLUDING CLUTCH ASSY) WOULD DETECT THIS PROBLEM.			1	H	7	1 	3O			NT	3A12 					 
1995032400409	19950324	00409	EA 	1995	3	24	95ZZZX1366 	2	19950222	G	8550	LW13306	GASKET 			MOONEY	M20 	M20M 	5870222	SW 	LYC 	O540 	TIO540AF1A 	41532	EA 					OIL SUMP PAN	BROKEN 	B			GN1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NE	01	1085W	232 				270043	L912161A			NEW MOONEY M20M AT 124.6, ENGINE OIL PAN GASKET LEAKING. REMOVED AND REPLACED WITH 06B2132C, REVISED PART NUMBER AND GA	SKET. THE TURBO MOUNT IS LOCATED ON THE SIDE OF THE OIL PAN. BOTH GASKETS LEAKED AT THE LT REAR SIDE. BOTH LW-13306 G	ASKETS WERE FOUND BROKEN AT THE SAME LOCATION. LYCOMING IS NOW USING THE OLD STYLE TIO-540 OIL PAN GASKET USED ON OTHER	 ENGINES. SEE FAA AC43-16 DATED 2-95. SUBMITTER RECOMMENDS SB FOR GASKET REPLACEMENTS.			1	L	7	1 	30	3	O	RT	2A3 	E14EA				 
1995032400410	19950324	00410	NE 	1995	3	24	95ZZZX1367 	2	19950216	G	8510	96657	COUPLING 			DOUG 	DC3 	DC3G102A 	3021404	WP 	PWA 	R1830 	R183094M1 	52020	NE 					ENG FRONT SEC	BROKEN 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	13JA		945 			4082	145873			REMOVED SN 145873 ENGINE DUE TO INCREASING AMOUNTS OF STEEL IN OIL SCREEN OVER A PERIOD OF 108 HRS. TSMOH WAS 2-1/2 YRS	 AND 945 HRS. TWO OIL ANALYSES DURING THAT TIME REPORTED ALL WEAR CHECKS NORMAL. UPON EXAMINING REMOVED ENGINE, FND PN	 96657 COUPLING ASSY CRACKED COMPLETELY THROUGH. ALSO, AN APPROX 1 SQUARE INCH PIECE WAS BROKEN AWAY, BUT RETAINED IN P	LACE BY CHANNEL DESIGN OF MATING PN 92991 COUPLING ASSY. ONLY REASON GEARS ARE TIMED IS SO MAGNETO TIMING CAN BE CHECKE	D VIA A TIMING PIN THROUGH A SIGHTING HOLE IN NOSE CASE. NOTED GEAR NOT TIMED, BROKEN PIECE WAS THROUGH THE GROOVE OF T	HE TOOTH WITH RIVET HOLE AND TIMING PIN (PN 93407) WAS NOT INSTALLED.	2	L	7	2 	4R	4	R		A618 	5E4				 
1995032400411	19950324	00411	NE 	1995	3	24	95ZZZX1368 	2	19950216	G	8510	96657	COUPLING 			DOUG 	DC3 	DC3G102A 	3021404	WP 	PWA 	R1830 	R183094M1 	52020	NE 					ENG FRONT SEC	BROKEN 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	13JA		1064 			4082	BP600184			ENGINE HAD BEEN SHOWING SMALL AMOUNTS OF STEEL IN THE OIL SCREEN FOR 138 HRS. TSMOH WAS 2-1/2 YRS AND 1064 HRS. DECIDE	D TO REMOVE FRONT SECTION AGAIN PN 96657 COUPLING ASSEMBLY FOUND BROKEN. THIS TIME, NOT ALL THE WAY THROUGH, BUT .75 IN	CH OF THE 1.50 INCH LONG TOOTH WITH THE RIVET HOLE WAS BROKEN LOOSE. AGAIN, HELD IN PLACE BY THE DESIGN OF CHANNEL SHAP	ED PN 92991 MATING COUPLING ASSY. THE TIMING RIVET FROM PN 96657 COUPLING ASSY HAD ALSO BEEN REMOVED AND THE COUPLING R	ANDOMLY INSTALLED.		2	L	7	2 	4R	4	R		A618 	5E4				 
1995032400412	19950324	00412	NE 	1995	3	24	95ZZZX1369 	2	19950216	G	8510	96657	COUPLING 			DOUG 	DC3 	DC3G102A 	3021404	WP 	PWA 	R1830 	R183094M1 	52020	NE 					ENG FRONT SEC	BROKEN 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	13JA		119 			4082	BP600309			UPON EXAMINING REMOVED ENGINE, FOUND PN 96657 COUPLING ASSY CRACKED COMPLETELY THROUGH. ALSO, AN APPROX 1 SQUARE INCH P	IECE BROKEN AWAY, BUT RETAINED IN PLACE BY CHANNEL DESIGN OF MATING PN 92991 COUPLING ASSY. PN 96657 COUPLING ASSY CONN	ECTS THE POWER SECTION TO THE FRONT SECTION. NOTICED PN 73137 TIMING RIVET HAD BEEN PREVIOUSLY REMOVED WHICH IS PART OF	 THE BROKEN PN 96657 COUPLING ASSY. THE RIVET IS USED TO MATE WITH A TIMING SLOT OF PN 92991 COUPLING ASSY. THE ONLY R	EASON GEARS ARE TIMED IS SO MAGNETO TIMING CAN BE CHECKED VIA A TIMING PIN THROUGH SIGHTING HOLE IN NOSE CASE. GEAR NOT	 TIMED, BROKEN PIECE WAS THROUGH THE GROOVE OF THE TOOTH WITH RIVET HOLE AND TIMING PIN (PN 93407) WAS NOT INSTALLED.	2	L	7	2 	4R	4	R		A618 	5E4				 
1995032400413	19950324	00413	NE 	1995	3	24	95ZZZX1370 	2	19950221	G	7250	411101007	GP NOZZLE 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					INNER SHROUD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117VU	578 				7211	LE45528E			UPON INSPECTION OF ENGINE ASSY FOR CAUSE OF LOW POWER, (MINUS 86 DEGREES CENTRIGRADE), THE G.P. NOZZLE WAS FOUND TO HAVE	 A LARGE CIRCUMFERENTIAL CRACK ON THE INNER SHROUD TO VANE ASSY WELD (8.50 INCH CRACK). CIRCUMFERENCE OF INNER SHROUD I	S APPROXIMATELY 19 INCHES. OPER CONTROL NR OHI 2012.				1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995032400414	19950324	00414	SW 	1995	3	24	95ZZZX1371 	1	19950124	G	6310	222044672101	COUPLING 	222044006109		BELL 	222 	222U 	1182140	SW 										DRIVE SHAFT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	222DE	4214 			A12177	47520				CORROSION ON SPLINES MAKES THIS PART UNSERVICEABLE. SUSPECT DEFECTIVE GREASE, PN 204-040-755-005. OPER CONTROL NR OHI 	2005.					1	G	7	2 	3U				H9SW 					 
1995032400415	19950324	00415	SW 	1995	3	24	95ZZZX1372 	1	19950201	G	6310	222044685101	SHAFT 			BELL 	222 	222U 	1182140	SW 										MAIN DRIVE	REQ REPLACEMENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	4273 	60 		A399	47520				IN COMPLIANCE WITH ASB 222U-95-46, SHAFT RECALL AND REPLACEMENT. REMOVED SHAFT FROM MAIN DRIVE SHAFT ASSY, PN 222-044-0	06-109, SN A-48. OPER CONTROL NR 2009.					1	G	7	2 	3U				H9SW 					 
1995032400416	19950324	00416	SW 	1995	3	24	95ZZZX1373 	1	19950202	G	6310	222044672101	COUPLING 			BELL 	222 	222U 	1182140	SW 										MAIN DRIVE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	4273 	60 			47520				EXCESSIVE CORROSION PITTING IN SPLINES OF COUPLING AFTER 63.7 HOURS. IMPROPER HEAT TREATMENT COULD HAVE BEEN A FACTOR I	N THE MALFUNCTION. OPER CONTROL NR OHI 2011.					1	G	7	2 	3U				H9SW 					 
1995032400417	19950324	00417	SW 	1995	3	24	95ZZZX1374 	1	19950131	G	6310	222044607003	COUPLING 		222044006109	BELL 	222 	222U 	1182140	SW 										MAIN DRIVE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	4273 	60 		A1000	47520				INNER COUPLING, TT 59.6 HRS, HAS CORROSION PTTING ON SPLINE TEETH. COUPLING GREASE, PN 204-040-755-5, COULD BE DEFECTIV	E, BREAKING DOWN UNDER NORMAL USAGE. THE DRIVE SHAFT ASSY ONLY HAD 59.6 HRS SINCE LAST INPSECTION AND REPACK COUPLING O	NLY HAD 59.6 HRS SINCE NEW. OPER CONTROL NR OHI 2008.				1	G	7	2 	3U				H9SW 					 
1995032400418	19950324	00418	SW 	1995	3	24	95ZZZX1375 	1	19950202	G	6310	222044607003	COUPLING 		222044006109	BELL 	222 	222U 	1182140	SW 										MAIN DRIVE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	4273 	60 		A815	47520				EXCESSIVE CORROSION PITTING ON SPLINES OF COUPLING AFTER 6,317 HRS. IMPROPER HEAT TREATMENT COULD HAVE BEEN A FACTOR IN	 THE MALFUNCTION. OPER CONTROL NR 2010.					1	G	7	2 	3U				H9SW 					 
1995032400419	19950324	00419	SW 	1995	3	24	95ZZZX1376 	1	19950310	G	2150	1001	STUB SHAFT 			AIRTRC	AT400 	AT402 	0390205	SW 										AIR COND DRIVE	EXCESS WEAR 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	9185K	433 				4020908				DURING 100-HOUR INSPECTION, NOTED EXCESSIVE BACKLASH IN AIR CONDITIONER DRIVE PULLEY. REMOVED DRIVE BRACKET INSTALLED U	NDER STC SA00144AT. STUB SHAFT BETWEEN ENGINE AND DRIVE BRACKET WORN CAUSING PRE-LOAD ON ENGINE GEAR AND BEARINGS. THI	S IS 3RD OCCURRENCE. COMPONENTS SHOULD BE REMOVED FROM SERVICE.				1	L	7	1 	3T			NC	A17SW 					 
1995032400420	19950324	00420	SW 	1995	3	24	95ZZZX1377 	1	19950303	G	2150	1001	STUB SHAFT 			AIRTRC	AT400 	AT402 	0390205	SW 										AIR COND DRIVE	EXCESS WEAR 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	9192P					4020913				DURING 100-HOUR INSPECTION, NOTED EXCESSIVE BACKLASH IN WAG CORP. AIR CONDITION DRIVE PULLEY. REMOVED PN 100-H BRACKET 	FROM ENGINE. FOUND EXCESSIVE WEAR ON SPLINES CAUSING DAMAGE TO ENGINE. REMOVED PART FROM SERVICE. MANUFACTURER HAS NO	 KNOWN FIX FOR THIS PROBLEM. STC SA00144AT.				1	L	7	1 	3T			NC	A17SW 					 
1995032400421	19950324	00421	SW 	1995	3	24	95ZZZX1378 	1	19950302	G	2150		STUB SHAFT 			AIRTRC	AT500 	AT502 	0390303	SW 										AIR COND DRIVE	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	9184T	389 			1001	5020199				PILOT NOTED AIR CONDITIONER INOP. REMOVED DRIVE BRACKET ASSY FROM ENGINE. SPLINES WORN OFF OF SHAFT. SPLINES IN ENGIN	E SHAFT NOT SERVICEABLE. SUBMITTER SUGGESTED ALL SUCH COMPONENTS SHOULD BE REMOVED FROM SERVICE. SECOND SUCH OCCURRENC	E. STC SA0144AT.				1	L	7	1 	3T			NC	A9SW 					 
1995032400422	19950324	00422	CE 	1995	3	24	95ZZZX1379 	1	19950222	G	3230	V3101D8	SWITCH 			BEECH 	200 	200BEECH 	1152920	CE 										EMERG EXTEND	FAILED 	B			HAXR	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			SW	11	356GA	5000 				BB447				LANDING GEAR DID NOT RETRACT ON TAKEOFF. TROUBLESHOOTING REVEALED LANDING GEAR EMERGENCY EXTENSION SWITCH WAS NOT CLOSI	NG. REPLACED SWITCH AND ADJUSTED IAW BEECH MM FOR 200 SERIES CHAPTER 32-30-00, RIGGING MANUAL EXTENSION SYSTEM, PARAGRA	PH (A). CHECKED GEAR SWING IAW CHAPTER 32-00-00.				1	L	7	2 	4T				A24CE 					 
1995032400423	19950324	00423	WP 	1995	3	24	95ZZZX1380 	2	19950312	G	7321	8977807	FUEL CONTROL 	WOODWARD 		BAG 	JETSTM	JETSTM3101 	1500215	EU 	GARRTT	TPE331	TPE33110UA 	01514	WP 					RT ENGINE	FAILED 	B			UN7R	A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			SW	19	608JX		34 		1945014	608	P42026			DURING REPOSITION FLIGHT FROM CIT TO BWI 20 MINUTES INTO FLIGHT, RT ENGINE STARTED BYPASSING FUEL, REDUCED POWER AND CON	TINUED CLIMB. AT 19,000 FEET, NOTICED EGT AT 655. REDUCTION OF POWER DID NOT CHANGE EGT. POWER LEVER REDUCED TO FLIGH	T IDLE, EGT WENT TO 650 DEGREES CENTIGRADE AT 80 PERCENT TORQUE. ON DESCENT BACK TO LIT, EGT AND POWER REDUCED ON ITS O	WN (10,000 FEET EGT 600 DEGREES CENTIGRADE TORQUE 60 PERCENT) (2,000 FEET 400 DEGREES CENTIGRADE AND 6 PERCENT TORQUE). 	 LANDED AT LIT WITHOUT INCIDENT. PILOTS SHUT RT ENGINE DOWN FOR TAXI. INSPECTED ENGINE FOR ANY EXTERNAL DEFECTS, NONE 	NOTED. REMOVED FUEL CONTROL FROM ENGINE FOR INSPECTION AT WOODWARD AND TO PERFORM SB TPE 331-73-0228 PER AD 94-26-07.	2	L	7	2 	4T	4	T	RT	A21EU 	E4WE				 
1995032400424	19950324	00424	SO 	1995	3	24	95ZZZX1381 	1	19950308	G	3040		WIRE 			GULSTM	G1159 	GIV 	3980115	SO 										WINDSHIELD HEAT	SHORTED 	D				O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			EA	11	2600	3108 				1088				THERE WAS SMOKE IN THE COCKPIT FOLLOWED BY A CIRCUIT BREAKER TRIPPING FOR THE WINDSHIELD HEAT. THE WINDSHIELD WIRING GO	ES THROUGH A HOLE IN A VERTICAL BEAM AFT OF THE WINDSHIELD. THIS IS WHERE THE WIRE SHORTED. REF: GULFSTREAM CB. 39.					2	L	7	2 	4F			RT	A12EA 					 
1995032400425	19950324	00425		1995	3	24	95ZZZX1382 	4	19950307	G	2215	40005238501	SERVO 			MTSBSI	MU2 	MU2B35 	5780411	CE 										ROLL SERVO	FAILED 	G		A		A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			CR	CRUISE 	1			EA	01	3330K				8461	551				THE AIRCRAFT WAS AT CRUISE LEVEL FLIGHT WITH AUTOPILOT ENGAGED WHEN AIRCRAFT BEGAN GENTLE RIGHT TURN. PILOT DISENGAGED 	AUTOPILOT. ACFT CONTINUED IN RT TURN. PILOT FOUND ROLL CONTROL WAS BINDING, PULLED THE AUTOPILOT CIRCUIT BREAKER AND T	HIS DID NOT RELIEVE THE BINDING. PILOT DECLARED AN EMERGENCY AND LANDED SAFELY. INVESTIGATION REVEALED AUTOPILOT ROLL 	SERVO BOUND UP INTERNALLY. OVERHAULED ROLL SERVO. INSTALLED AND AUTOPILOT NORMAL.			1	H	7	2 	3T			RT	A10SW 					 
1995032400427	19950324	00427	EU 	1995	3	24	95ZZZX1384 	1	19950203	G	5753	T700A5755060000	CARRIAGE 			SOCATA	TBM 	TBM700 	8682000	EU 										LT FLAP INBD	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	969RF	805 				9				DURING FLAP CARRIAGE INSPECTION PER TBM SB 70-048, FOUND LT INBOARD CARRIAGE CRACKED AT LOWER WEB AREA (.5 INCH IN LENGT	H). SUSPECT CAUSE IS INSUFFICIENT WEB STRENGTH AND/OR FLAP EXTENSION AT HIGH SPEEDS. REPLACEMENT WITH NEW STYLE CARRIA	GE REQUIRED PER TBM MANDATORY SB 70-048.				1	L	7	1 	3T			RT	A60EU 					 
1995032400428	19950324	00428	WP 	1995	3	24	95ZZZX1385 	1	19950217	G	3213	ARG74841	STOP 		ARG7002503 	DOUG 	DC10 	DC1010 	3022110	WP 										MLG SHOCK STRUT	FAILED 	B	L		B4GR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	68044	8409 			LC0019RC	46903				STOP, PART OF SHOCK STRUT, PN ARG7002-503, SN LC0-019RC, FAILED & DESTROYED. SHOCK STRUT DISASSEMBLED, HOWEVER, WAS IN 	STORAGE FOR AN UNKNOWN PERIOD TO TIME (EST. 1 YR) PRIOR TO DISASSEMBLY. FAILED PART IS ONLY FUNCTIONAL WHEN SHOCK STRUT	 DEFLATED & UNSERVICED. DURING NORMAL OPERATION, 'STOP' IS NOT REQUIRED FOR GEAR OPERATION. CYCLES, 8,409.				2	L	7	3 	4F				A22WE 					 
1995033100378	19950331	00378	CE 	1995	3	31	95ZZZX1411 	1	19950214	G	7602	5838901223	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										RT ENG MIX	BROKEN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	18447	521 				TH883				CONTROL CABLE BROKEN ON THE ENGINE END AT THE POINT WHERE INNER CABLE ATTACHES TO THREADED STEEL END. SUBMITTER STATED 	THIS IS A CONTINUING PROBLEM ON SEVERAL AIRCRAFT. BEECHCRAFT HAS BEEN NOTIFIED AND HAVE NOT RESPONDED SINCE FIRST NOTIF	IED LAST OCTOBER.				1	L	7	2 	3O			 	3A16 					 
1995033100379	19950331	00379	CE 	1995	3	31	95ZZZX1412 	1	19950306	G	5510	9562001085	CHANNEL 			BEECH 	58 	58P 	1152744	CE 										HORIZ STABILIZER	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	6487E					TJ423				DURING ANNUAL INSPECTION FOUND BOTH LEFT AND RIGHT CHANNELS CRACKED AND NUMEROUS WORKING RIVETS. REPLACED BOTH CHANNELS	 WITH NEW PARTS. RECOMMEND CLOSER INSPECTION EVERY 100 HOURS.					1	L	7	2 	3O				A23CE 					 
1995033100380	19950331	00380	SO 	1995	3	31	95ZZZX1413 	1	19950120	G	3020	651802	MOTOR 			PIPER 	PA31T 	PA31T 	7103124	SO 										ICE DOOR	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	21	131MP					31T7820039				ICE DOOR MOTOR PIPER PN 475-194 WAS ORDERED. RECEIVED PN 651-802. WAS TOLD BY PARTS PEOPLE WAS DIRECT REPLACEMENT. EV	EN THOUGH WIRE HARNESS WAS DIFFERENT, AND MODIFIED MOUNTING BRACKET, THERE WAS NO PAPERWORK TO VERIFY IT AS KIT OF APPLI	CATION OTHER THAN PARTS BOOK, CROSS-REFERENCE. INTERMITTENTLY OPERATED WHEN ICE DOOR DEPLOYED AFTER INSTALLATION. GENE	RATOR WOULD TRIP OFF LINE. AFTER MUCH TROUBLESHOOTING, SERVICEABLE 475-194 WAS LOCATED AND INSTALLED. CORRECTED PROBLE	M.		1	L	7	2 	3T				A8EA 					 
1995033100381	19950331	00381	GL 	1995	3	31	95ZZZX1414 	1	19950313	G	7922		VALVE 			TCRAFT	19 	19 	9230702	GL 										THERMO BYPASS	CRIMP NUT LOOSE 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	5105R					MB639				WHILE COMPLYING WITH LYCOMING SB 518A, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. CRIMP NUT LOOSE DUE TO POO	R DESIGN.					1	H	7	1 	3O				1A9 					 
1995033100382	19950331	00382	CE 	1995	3	31	95ZZZX1415 	1	19950302	G	3230	MS203921C21	CLEVIS PIN 			CESSNA	210 	210 	2073402	CE 										NLG UPLOCK	FAILED 	B		A	PR5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	24K					21057265				NOSE GEAR WOULD NOT EXTEND. THIS AIRCRAFT HAD AN STC INSTALLED WHERE NOSE DOORS ARE MECHANICALLY HOOKED TO THE NOSE GEA	R. THE HYDRAULIC CYLINDER THAT PULLS THE UPLOCK HOOK TO RELEASE THE NOSE GEAR AND DOORS, CLEVIS PIN, MS20392-1C21, HAD 	EITHER FALLEN OUT OR WAS SHEARED OFF FROM NORMAL OPERATION. NOSE GEAR FELL INTO PLACE AND LOCKED DOWN ONCE HOOK WAS REL	EASED.			1	H	7	1 	3O			RT	3A21 					 
1995033100383	19950331	00383	EA 	1995	3	31	95ZZZX1416 	2	19950227	G	7314	LW15473	PUMP 			PIPER 	PA28 	PA28R201 	7102816	SO 	LYC 	O360 	IO360C1C6 	41514	EA 					ENGINE FUEL	WASHER FAILED 	B		A	OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	802ND					2837002	L2528051A			OIL QUICK DRAIN WOULD NOT SHUT OFF. FOUND 2 PARTS OF STEEL WASHER IN QUICK DRAIN. FOUND OTHER 2 PARTS OF WASHER IN PAN	. WASHER IS FROM JUST BELOW LEVER SLOT OF PUMP WHERE IT SLIDES OVER PUMP VERTICAL PLUNGER SHAFT. THIS IS THE SECOND OC	CURRENCE OF THIS FAILURE BY THIS OPERATOR (OTHER FAILED PUMP HAD 641 TSN).				1	L	7	1 	3O	3	O		2A13 	1E10				 
1995033100384	19950331	00384	CE 	1995	3	31	95ZZZX1417 	1	19950214	G	7603	5838901223	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										LT ENG THROTTLE	LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	18447					TH883				SWAGED SLEEVE AT ENGINE END OF THROTTLE CABLE WAS FOUND LOOSE AND SLIDING ON CABLE FREELY. FOUND DURING ANNUAL INSPECTI	ON. THIS PROBLEM CONTINUES TO EXIST ON MANY AIRCRAFT ON ALL ENGINE CONTROL CABLES.					1	L	7	2 	3O			 	3A16 					 
1995033100390	19950331	00390	EA 	1995	3	31	95ZZZX1423 	2	19950303	G	8530	65427	VALVE SPRING 			PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E3D 	41508	EA 					OUTER	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	01	3975K					2823861	L2497427AC			CUSTOMER REPORTED ENGINE 'BACKFIRING' INTERMITTENTLY AT HIGH IDLE. VALVE TRAIN PROBLEMS SUSPECTED & COLD CYLINDER TESTE	R DISCLOSED NR 3 CYL SLIGHTLY COOL (COMPRESSION WAS EXCELLENT). CLOSER INSP DISCLOSED INCORRECT SPRINGS PN 65427 INSTAL	LED INSTEAD OF LW-11800. NO RECORD OF MX ON THIS CYL SINCE O/H. PN 65427 SPRING HAS ABOUT 35 POUNDS LESS LOAD THAN COR	RECT SPRING & IS USED IN O-235/O-290 SERIES ENGINES. VALVE & GUIDE WEAR WERE CHECKED & WITHIN LIMITS, BUT ENOUGH MUST H	AVE CHANGED SINCE ENG HAS RUN 1620 HRS SMOH W/O COMPLAINT OF BACKFIRING. IN THIS CASE, 'WEAK' SPRINGS ALLOWED VALVES TO	 RESONATE OR BOUNCE IN A NARROW RPM RANGE (1200-1500 RPM) & RESULTED IN 'AFTERFIRING'. REPLACING SPRINGS CURED PROBLEM.	1	L	7	1 	3O	3	O		2A13 	E274				 
1995033100391	19950331	00391	SO 	1995	3	31	95ZZZX1424 	1	19950308	G	5720	6206104	DOUBLER 			PIPER 	PA28 	PA28161 	7102803	SO 										WALKWAY SKIN	CRACKED 	D			HR8S	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	39954	6266 				287916014				FOUND A CRACK IN THE WALKWAY SKIN DOUBLER. AREA IS ALMOST IMPOSSIBLE TO VIEW BECAUSE THERE IS NO INSPECTION OPENINGS IN	 THIS AREA. CRACK WAS SEEN THROUGH A SMALL RIB CUT OUT AREA. SUBMITTER RECOMMENDS AN INSPECTION PLATE BE INSTALLED IN 	THIS AREA FOR INSPECTION. TOP SKIN IS NOT CRACKED, ONLY INSIDE DOUBLER. THIS IS WHERE PILOT STANDS TO OPEN AND CLOSE D	OOR, APPROX 12 INCHES AFT OF MAIN SPAR.			1	L	7	1 	3O				2A13 					 
1995033100392	19950331	00392		1995	3	31	95ZZZX1425 	2	19950301	G	7414	M3525	COIL 	SLICK 	6264 															MAGNETO	CRACKED 	B			KC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03		57 			89070078					COIL MFG DATE 7-19-89. MAG SHOWED SLIGHT MISS DURING BENCH TEST. INSPECTION SHOWED COIL SECONDARY CIRCUIT OPEN AND COI	L CRACKED ON END NEAR CORE LAMINATIONS. SUBMITTER STATED SEEING SAME PROBLEM MANY TIMES WITH THIS SERIES COIL. CONTINU	ED USE OF THIS COIL WOULD LEAD TO COMPLETELY DEAD MAG.																	 
1995033100393	19950331	00393	SO 	1995	3	31	95ZZZX1426 	2	19950228	G	7414		IMPULSE COUPLING	SLICK 	662 	CESSNA	206 	U206F 	2073333	CE 	CONT 	O520 	IO520F 	17032	SO 					MAGNETO	STOP BROKE 	B			OENR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	7487Q		876 		7110470	U20602221	16942273F			THE IMPULSE COUPLING STOP ON LEFT MAG BROKE OFF AND FELL DOWN INTO OIL SUMP. IT MADE THE IMPULSE COUPLING INOPERATIVE F	OR STARTING, BUT DID NOT HARM NORMAL OPERATION OF MAG. THE STOP PIECES COULD HAVE DAMAGED ACCESSORY DRIVE GEARS, BUT DI	D NOT. SUBMITTER RECOMMENDS MAGNAFLUX AT OVERHAUL AND AGAIN AT 1,000 HRS TT.				1	H	7	1 	3O	3	O		A4CE 	E5CE				 
1995033100394	19950331	00394	SO 	1995	3	31	95ZZZX1427 	2	19950201	G	8530		CYLINDERS 			CESSNA	210 	T210L 	2073449	CE 	CONT 	O520 	TSIO520R 	17040	SO 					ENGINE	WORN 	B			BJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	210MG					21060838	506427			ENGINE RUN SMOH WITH MOBIL AV-1 ENGINE OIL. ENG STARTED SHOWING HIGH READINGS OF IRON, CHROMIUM, ALUMINUN ON OIL ANALYS	IS. CYLS REMOVED FOR INSP. ALL OIL CONTROL RINGS FND STUCK W/LEAD BUILD-UP & ALL CYL WALLS FND WORN UP TO .014 INCH. E	NG REMOVED FROM ACFT & DISASSEMBLED. FND VERY HIGH SLUDGE BUILD-UP IN ENG CAUSING PARTIAL BLOCKAGE OF MAIN OIL GALLEY. 	 THIS CAUSED PREMATURE MAIN & CONNECTING ROD BRNG WEAR TO NEAR FAILURE. CRANKSHAFT ALSO FND SCORED AT PROP TRANSFER COL	LAR AREA. CAM FOLLOWERS FND PITTED. ENG O/H 2-1/2 YEARS EARLIER W/ALL NEW CYLS, BRNGS, & CAMSHAFT FOLLOWERS INSTALLED.	 SUBMITTER STATED SEEING SIMILAR DAMAGE IN OTHER ENG RUN ON THIS OIL. RECOMMEND INSP OF ENG WITH THIS OIL.	1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995033100395	19950331	00395		1995	3	31	95ZZZX1428 	4	19950306	G	3416	3431	CASTING 	UNITEDINST 	5934PD1 	PIPER 	PA32 	PA32301 	7103207	SO 										ALTIMETER	CREEP 	B			EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	8165A				R7766	328006014				(FACTORY SEALED INST MFG 11/79). CRITICAL SHAFT END SHAKES OUT OF SPEC. FACTORY SPEC. SUBMITTER STATED ALL OF END SHA	KES WERE UNDER BOTH THE O/H SPEC. AND THE FACT. SPEC. THE CASTING APPARENTLY CLOSED IN DUE TO STRESS RELIEVING AFTER LE	AVING THE FACTORY. ADDITIONAL CLOSING IN COUPLED WITH A LOW TEMP CONDITION COULD CAUSE A POINTER HANG-UP CONDITION. HE	AVY CONGEALED MOLY/KOTE WAS REMOVED FROM TOP PLATE BEARINGS WHICH REDUCED TOP PLATE FRICTION TO ONE-SIXTH ORIGINAL VALUE	.		1	L	7	1 	3O				A3SO 					 
1995033100396	19950331	00396	EA 	1995	3	31	95ZZZX1429 	2	19950224	G	7414	1068256013	HOUSING 		D6LN3000 	PIPER 	PA32 	PA32RT300 	7103215	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					CLAMP FLANGE	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	16	6240C		250 		A139406GB	32R7885022				ENGINE WAS LEAKING OIL. INVESTIGATION REVEALED CRACKED MAG HOUSING AT LOWER HOLD DOWN FLANGE. GASKET SURFACE WAS CLEAN	, CLAMP BLOCKS WERE PROPERLY POSITIONED AND TORQUED. CRACKED OUT SECTION REVEALED LARGE AREAS OF AIR POCKETS IN CASTING	. SUSPECT CRACK STARTED FROM PRESSED IN IMPULSE PINS AGGREVATED BY INTERNAL WEAKNESS DUE TO FLAWED CASTING.				1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995033100397	19950331	00397	EA 	1995	3	31	95ZZZX1430 	2	19950303	G	8520	SL78290	PLUNGER ASSY 	SUPAIRPART 		PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E3D 	41508	EA 					TAPPET	LOOSE 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			SO	01	3975K	1620 				2823861	L2497427AC			DURING COURSE OF TROUBLESHOOTING A ROUGH RUNNING ENGINE, THE HYDRAULIC PLUNGER ASSEMBLIES WERE REMOVED FROM THE TAPPETS.	 THE 'STEMS' OF 7 OF THE 8 UNITS WERE LOOSE AND WOULD SPIN IN THE BODY OF THE PLUNGER ASSEMBLY. NO CLUE WAS FOUND TO I	NDICATE WHAT MADE THE STEMS LOOSE. THAT PART OF THE UNIT RIDES ONLY IN OIL, ONLY NORMAL WEAR NOTED, AND ONLY IN THE NOR	MAL PLACES. THIS DEFECT ALLOWED LIFTERS TO BLEED DOWN UNUSUALLY QUICKLY. PARTS WERE REPLACED AND DEFECTIVE LIFTERS RET	URNED TO MANUFACTURER FOR FURTHER EVALUATION.		1	L	7	1 	3O	3	O		2A13 	E274				 
1995033100398	19950331	00398	CE 	1995	3	31	95ZZZX1431 	1	19950309	G	3222	908201005	SHOCK ASSY 			BEECH 	200 	200BEECH 	1152920	CE 										NLG	CORRODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	300TR	4652 	840 			BB6				CORROSION, PITTING ON THE INTERNAL PART OF THE NOSE GEAR SHOCK ABSORBER -- FABRIC PAD RETAINS MOISTURE AND CAUSES PITTIN	G, ETC. SUBMITTER STATED FIVE YEAR/7500 HOUR INSPECTION IN CHAPTER FIVE MM GETS THIS ITEM INSPECTED BEFORE A FAILURE. M	AYBE THIS ITEM NEEDS TO BE REDIESIGNED TO PREVENT MOISTURE COLLECTING AND NOT DRYING.				1	L	7	2 	4T				A24CE 					 
1995033100399	19950331	00399	GL 	1995	3	31	95ZZZX1432 	1	19950206	G	6100		BOLT 			AMTR 	KR2 	KR2 		GL 										PROPELLER	FAILED 	G				A				UNSCHED LANDING 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			SO	05	612W					001				AIRCRAFT IN CRUISE AT 6000 M.S.L. WHEN THE PROPELLER SEPARATED FROM THE ENGINE. THE AIRCRAFT LANDED IN A FIELD AND HAD 	SUBSTANTIAL DAMAGE. THE PILOT WAS NOT INJURED. SUSPECT IMPROPER BOLTS USED WHEN PROPELLER WAS ATTACHED. THE BOLTS AND	/OR PROPELLER WERE NOT RECOVERED.				1	L	7	1 	3O				EXPA1L71					 
1995033100400	19950331	00400	SO 	1995	3	31	95ZZZX1433 	2	19950303	G	7414	S6LN21	MAGNETO 	BENDIX 		CESSNA	172 	172 	2072402	CE 	CONT 	O300 	O300A 	17022	SO 					ENGINE RT	DEFECTIVE 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			SO	11	6110E	1586 			2422862R	46210	159337AK			AIRCRAFT LANDED ON ROAD 15 MINUTES AFTER TAKEOFF DUE TO ROUGH ENGINE AND NOT ABLE TO MAINTAIN ALTITUDE. AIRCRAFT HAS NO	T RUN IN A LONG TIME. RAN AIRCRAFT ON GROUND 15 TO 20 MINUTES. MAGS CHECKED GOOD UP UNTIL THEN. STARTED GETTING REAL 	ROUGH, BOTH MAGS AND THEN WORSE. AIRCRAFT IN LICENSE - AD 94-01-03R1 NOT COMPLIED WITH ON MAG COILS AND ROTATING MAGNET	S.			1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995033100401	19950331	00401	SO 	1995	3	31	95ZZZX1434 	2	19950303	G	7414	S6LN21	MAGNETO 	BENDIX 		CESSNA	172 	172 	2072402	CE 	CONT 	O300 	O300A 	17022	SO 					ENGINE LT	DEFECTIVE 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			SO	11	6110E	1586 				46210	159337AK			AIRCRAFT LANDED ON ROAD 15 MINUTES AFTER TAKEOFF DUE TO ROUGH ENGINE AND NOT ABLE TO MAINTAIN ALTITUDE. AIRCRAFT HAS NO	T RUN IN A LONG TIME. RAN AIRCRAFT ON GROUND 15 TO 20 MINUTES. MAGS CHECKED GOOD UP UNTIL THEN. STARTED GETTING REAL 	ROUGH, BOTH MAGS AND THEN WORSE. AIRCRAFT IN LICENSE - AD 94-01-03R1 NOT COMPLIED WITH ON MAG COILS AND ROTATING MAGNET	S.			1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995033100402	19950331	00402	CE 	1995	3	31	95ZZZX1435 	1	19950301	G	3230	504501018	TORQUE TUBE 			CESSNA	310 	310R 	2074245	CE 										MLG RETRACT	CRACKED 	B		A	AHTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	5162C	5496 				310R1511				DURING ANNUAL INSPECTION, RIGHT MLG TORQUE TUBE WAS FOUND CRACKED. THE CRACK IS APROXIMATELY .3750 INCH LONG AND IS LOC	ATED ON THE WELD AT THE BOSS FOR THE FORK BOLTS. THE CRACK WAS DETECTED BY A VISIBLE LINE, (RUSTY), IN THE PAINT ON THE	 PART. LIQUID PENETRANT AND MAGNETIC PARTCLE INSPECTION VERIFIED THE CRACK. SUBMITTER STATED THIS IS THE SECOND AIRCRA	FT FOUND WITH THIS CONDITION.			1	L	7	2 	3O				3A10 					 
1995033100403	19950331	00403		1995	3	31	95ZZZX1436 	4	19950304	G	6113	43940008	SPINNER 			PIPER 	PA31 	PA31350 	7103110	SO 										FRONT MOUNT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	4079B	48 				318152073				SPINNER AND REAR BULKHEAD HAD BEEN PREVIOUSLY CHANGED FOR CRACKS AND PIPER PARTS REINSTALLED. AFTER 48 HOURS DURING OIL	 CHANGE, LIGHT CRACKS NOTED IN BACKPLATE AND SPINNER DOME NUT WAS FOUND LYING IN SPINNER CAP WITH SAFETY WIRE STILL INST	ALLED. RECOMMEND PRE-FLIGHT CHECK FOR SPINNER INTEGRITY AND 50 HOUR CHECK OF SPINNER ASSEMBLY PER MFG INSP PROGRAM.				1	L	7	2 	3O				A20SO 					 
1995033100404	19950331	00404		1995	3	31	95ZZZX1437 	4	19950304	G	6113	43933008	BULKHEAD 			PIPER 	PA31 	PA31350 	7103110	SO 										MOUNT HOLES	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	4079B	48 				318152073				SPINNER AND REAR BULKHEAD HAD BEEN PREVIOUSLY CHANGED FOR CRACKS AND PIPER PARTS REINSTALLED. AFTER 48 HOURS DURING OIL	 CHANGE, LIGHT CRACKS NOTED IN BACKPLATE AND SPINNER DOME NUT WAS FOUND LYING IN SPINNER CAP WITH SAFETY WIRE STILL INST	ALLED. RECOMMEND PRE-FLIGHT CHECK FOR SPINNER INTEGRITY AND 50 HOUR CHECK OF SPINNER ASSEMBLY PER MFG INSP PROGRAM.				1	L	7	2 	3O				A20SO 					 
1995033100405	19950331	00405	CE 	1995	3	31	95ZZZX1438 	1	19950308	G	5720	05234063	CHANNEL 			CESSNA	150 	150H 	2071818	CE 										LT WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S					15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, LT CHANNEL FOUND BAD. PART REPLACED AND WING RETURNED TO SERVICE. RECOMMEND 	BETTER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100406	19950331	00406	CE 	1995	3	31	95ZZZX1439 	1	19950308	G	5720	0523309	ANGLE 			CESSNA	150 	150H 	2071818	CE 										WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S	3228 				15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, ANGLE FOUND BAD. PART WAS REPLACED AND WING RETURNED TO SERVICE. SUBMITTER R	ECOMMENDS BETTER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100407	19950331	00407	CE 	1995	3	31	95ZZZX1440 	1	19950308	G	5720	05233091	ANGLE 			CESSNA	150 	150H 	2071818	CE 										RT WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S					15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, RT ANGLE FOUND BAD. PART REPLACED AND WING RETURNED TO SERVICE. RECOMMEND BE	TTER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100408	19950331	00408	CE 	1995	3	31	95ZZZX1441 	1	19950308	G	5720	05232322	CHANNEL 			CESSNA	150 	150H 	2071818	CE 										WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S					15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, CHANNEL FOUND BAD. PART REPLACED AND WING RETURNED TO SERVICE. RECOMMEND BET	TER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100409	19950331	00409	CE 	1995	3	31	95ZZZX1442 	1	19950308	G	5720	042640017	CHANNEL 			CESSNA	150 	150H 	2071818	CE 										RT WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S					15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, RT CHANNEL FOUND BAD. PART REPLACED AND WING RETURNED TO SERVICE. RECOMMEND 	BETTER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100410	19950331	00410	CE 	1995	3	31	95ZZZX1443 	1	19950308	G	5720	0426306	CAP PLATE 			CESSNA	150 	150H 	2071818	CE 										WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S					15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, CAP PLATE FOUND BAD. PART REPLACED AND WING RETURNED TO SERVICE. RECOMMEND B	ETTER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100411	19950331	00411	CE 	1995	3	31	95ZZZX1444 	1	19950308	G	5720	0426307	CAP ANGLE 			CESSNA	150 	150H 	2071818	CE 										LT WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S					15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, CAP ANGLE FOUND BAD. PART REPLACED AND WING RETURNED TO SERVICE. RECOMMEND B	ETTER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100412	19950331	00412	CE 	1995	3	31	95ZZZX1445 	1	19950308	G	5720	05234062	CHANNEL 			CESSNA	150 	150H 	2071818	CE 										RT WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S					15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, CHANNEL FOUND BAD. PART REPLACED AND WING RETURNED TO SERVICE. RECOMMEND BET	TER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100413	19950331	00413	CE 	1995	3	31	95ZZZX1446 	1	19950308	G	5720	042640018	CHANNEL 			CESSNA	150 	150H 	2071818	CE 										LT WING	CORRODED 	B			A5OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6444S					15067244				DURING HIDDEN DAMAGE INSPECTION OF WINGS, CHANNEL FOUND BAD. PART REPLACED AND WING RETURNED TO SERVICE. RECOMMEND BET	TER HEAT TREATING AND CORROSION PROTECTION DURING MANUFACTURE.					1	H	7	1 	3O				3A19 					 
1995033100414	19950331	00414	CE 	1995	3	31	95ZZZX1447 	1	19950317	G	2434	EQ5820	DRIVE 	FORD 	DOFF10300E 	CESSNA	172 	R172F 		CE 										ALTERNATOR	SHEARED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	758CM	402 			43495	R1722989				PILOT REPORT: INTERMITTENT ALT OPS REMOVED AND INSPECTED. FOUND SHAFT SHEARED ON ALTERNATOR.						1	H	7	1 	3O				3A17 					 
1995033100416	19950331	00416		1995	3	31	95ZZZX1449 	4	19950206	G	3416	3431	CASTING 	UNITEDINST 	5934P1 	CESSNA	150 	152 	2071835	CE 										ALTIMETER	CREEP 	B			EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	25449				LE3659	15280669				THE END SHAKES WERE CHECKED ON THIS INSTRUMENT AND FOUND CONSIDERABLY UNDER THE SPECIFIED TOLERANCE CALLED OUT IN THE O/	H MANUAL. THE O/H MANUAL CALLS OUT AN END-SHAKE OF .0020 INCH TO .0030 INCH ON ALL 3 OF THE CRITICAL MECHANISM SHAFTS. 	 THIS INSTRUMENT MEASURED .0004 INCH ON ONE SHAFT, AND .0005 INCH ON THE OTHER SHAFT. THIS MINIMAL END-SHAKE CONDITION 	COULD CAUSE INSTRUMENT TO HANG UP WHEN EXPOSED TO A COLD CONDITION THAT CAN BE EXPECTED IN AN AIRCRAFT ENVIRONMENT.			1	H	7	1 	3O			NT	3A19 					 
1995033100417	19950331	00417	CE 	1995	3	31	95ZZZX1450 	1	19950304	G	7810	99103007	WYE COLLECTOR 			CESSNA	421 	421C 	2076016	CE 										EXHAUST	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	100QC					421C0689				DURING A ROUTINE INSPECTION, THE EXHAUST Y-COLLECTOR WAS FOUND WITH A ONE INCH CRACK. AN EXHAUST STAIN WAS PRESENT. RE	COMMEND A THOROUGH INSPECTION OF THE EXHAUST SYSTEM EVERY 100 HOURS, ESPECIALLY ON LARGE TURBOCHARGED ENGINES. AD 75-23	-08 R5 PERTAINS TO THIS SUBJECT.				1	L	7	2 	3O				A7CE 					 
1995033100418	19950331	00418		1995	3	31	95ZZZX1451 	4	19950228	G	2562	4520130	BATTERY 		ELT1104 	BEECH 	76 	76 	1153005	CE 										ELT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	6701C				50796	ME280				ELT ACTIVATED ON RAMP. REMOVED UNIT, FOUND HEAVY CORROSION ON BATTERY PACK AND MOUNTING SPACES, ELT WAS MFG 2-93. BATT	ERY REPLACEMENT WAS DUE 3-95. UNIT WAS INSTALLED NEW 8-93. LAST ELT INSPECTION PER FAR 91.52 WAS COMPLETED 9-94.					1	L	7	2 	3O				A29CE 					 
1995033100419	19950331	00419		1995	3	31	95ZZZX1452 	4	19950228	G	2562	ELT10	ELT 	NARCO 		BEECH 	76 	76 	1153005	CE 										BAT CONNECTOR	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	6630K				43664	ME355				ELT ACTIVATED ON GROUND. RESET BUTTON CURED ACTIVATION. CONDUCTED INSPECTION PER 91.52, FOUND CORROSION ON BATTERY CON	NECTOR AND PC BOARD. CLEANED CORROSION. INSTALLED NEW BATTERY. G-SWITCH COULD NOT BE ACTIVATED BY FORCE. LAST INSPEC	TION, 12-94. SUGGESTED USING SOME TYPE OF CORROSION PREVENTATIVE ON PC BOARD AND CONNECTIONS. BATTERY SEALANT WAS INTA	CT.			1	L	7	2 	3O				A29CE 					 
1995033100420	19950331	00420	SO 	1995	3	31	95ZZZX1453 	1	19950218	G	7810	07A19981	BRACKET 			PIPER 	PA46 	PA46350P 		SO 										EXH CROSS-OVER	BOLT FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	1818W	238 				4622151				ON INSPECTION, LEFT SUPPORT ON EXHAUST CROSS-OVER HAD MISSING ATTACHING HARDWARE. FOUND BROKEN BOLT SHANK AND NUT IN FI	REWALL FLANGE PARTIALLY PAINTED COLOR OF AIRCRAFT (WHICH MEANS BOLT WAS BROKEN AT FACTORY INSTALLATION PRIOR TO PAINTING	). NO RECORD OF COMPLIANCE WITH LYCOMING SB 512 (EACH 200 HOURS). LYCOMING SB 512 RECENTLY REPLACED WITH SB 521. BOLT	 PN LW25150.			1	L	7	1 	3O			RT	A25SO 					 
1995033100421	19950331	00421	SO 	1995	3	31	95ZZZX1454 	1	19950218	G	7810	40B19842	EXHAUST STACK 			PIPER 	PA46 	PA46350P 		SO 										NR 4 CYL	DISTORTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	1818W	238 				4622151				ON INSPECTION, NR 4 CYLINDER EXHAUST PIPE FLANGE DISTORTED AT LEFT TRANSITION. LEFT TURBOCHARGER HAD BECOME LOOSE AT EN	GINE, SHIFTING DOWN SLIGHTLY CAUSING MISALIGNMENT WITH NR 4 PIPE. FORWARD TRANSITION SUPPORT BOLT (PN LW31-1.69) WAS MI	SSING. LYCOMING SB 512 PERTAINS TO THIS SUBJECT WHICH HAS RECENTLY BEEN REPLACED WITH SB 521.				1	L	7	1 	3O			RT	A25SO 					 
1995033100422	19950331	00422		1995	3	31	95ZZZX1455 	1	19950227	G	2432	106481	BATTERY PACK 	GLOBAL 	106001 															POSITIVE POST	OVERHEATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09					943					BATTERY PACK POSITIVE POST-TO-CELL TAP CONNECTION OVERHEATED AND MELTED PLASTIC COVER OF PACK. THIS CONNECTION IS SECUR	ED ONLY BY A SMASH-TYPE RIVET (HOLLOW SHOP END) AND IS SUBJECT TO WORKING LOOSE IN SERVICE. WHEN CONNECTION LOOSENS, A 	HIGH RESISTANCE CURRENT PATH IS CREATED WHICH WILL AFFECT BATTERY OUTPUT. RECOMMEND MFG GO BACK TO ORIGINAL DESIGN WHIC	H INCLUDES A PHENOLIC TYPE COVER AND SCREW/JAM NUT CONFIGURATION.																 
1995033100423	19950331	00423	SO 	1995	3	31	95ZZZX1456 	2	19950210	G	8540		STARTER ADAPTER 			CESSNA	421 	421A 	2076012	CE 	CONT 	O520 	GTSIO520C 	17032	SO 					ENGINE	FAILED 	D				E				ENGINE SHUTDOWN 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			GL	09	44SC					421A0101				AIRCRAFT LANDED AFTER DARK 2-9-95, WITH THE LEFT ENGINE SHUT DOWN. FOUND STARTER ADAPTER HAD TWO BROKEN TEETH AND METAL	 THROUGHOUT THE ENGINE. VERY ROUGH AIRCRAFT.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995033100424	19950331	00424	CE 	1995	3	31	95ZZZX1457 	1	19950223	G	2752	3536415157	FLAP MOTOR 			BEECH 	55 	95C55 	1152708	CE 										MOUNT	THREADS STRIPPED	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	07	482SJ					TE417				A BEECHCRAFT FACTORY OVERHAULED FLAP MOTOR ASSY WAS ORDERED. UPON INSTALLATION, DISCOVERED 4 MOUNTING HOLES HAD A MAJOR	TIY OF ITS THREADS MISSING. SUBMITTER SUGGESTS MECHANICS SHOULD COMPLETELY INSPECT EVEN FRESHLY OVERHAULED PARTS.					1	L	7	2 	3O				3A16 					 
1995033100426	19950331	00426	SO 	1995	3	31	95ZZZX1459 	1	19950301	G	2750		CONTROL CABLE 			PIPER 	PA36 	PA36285 	7103610	SO 										RUDDER	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	9942P	4610 				367560053				RUDDER CABLE HAD WORN THROUGH THE OUTER BATTERY CABLE INSULATION. WEAR POINT WAS ADJACENT TO THE BATTERY BOX. SUGGEST 	CLOSE MAINTENANCE ATTENTION AND BETTER SUPPORT OF THE BATTERY CABLE IN THIS AIRCRAFT.					1	L	7	1 	3O			 	A10SO 					 
1995033100592	19950331	00592	SO 	1995	3	31	95ZZZX1460 	2	19950222	G	8530	538288	CYLINDER 			BEECH 	33 	F33A 	1151425	CE 	CONT 	O520 	IO520BA 	17032	SO 					NR 1	GUIDE LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	1096W		70 			CE436	569112			DURING A ROUTE INPSECTION, NR 1 CYLINDER DISPLAYED LOW COMPRESSION. FURTHER INVESTIGATION, AFTER REMOVAL OF CYLINDER, R	EVEALED A LOOSE VALVE GUIDE IN THE CYLINDER HEAD. THIS ENGINE HAD BEEN OVERHAULED 70.0 HOURS PREVIOUS TO THE INSPECTION	. CAUSE: INCORRECT TOLERANCES ON INSTALLATION. PREVENTION: INSPECTION OF GUIDES AFTER 100 HOURS OF OPERATION.				1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995033100593	19950331	00593	CE 	1995	3	31	95ZZZX1461 	1	19950220	G	3244	60800257	TIRE 	MCCREARY 		BEECH 	58 	58P 	1152744	CE 										LT MLG	HOLE 	B			HBKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	6012S				CY8AA1L6388	TJ15				HOLE IN TIRE. POSSIBLY, HARD BRAKING MADE HOLE IN TIRE.						1	L	7	2 	3O				A23CE 					 
1995033100594	19950331	00594	EA 	1995	3	31	95ZZZX1463 	2	19950221	G	7322	30766	FLOAT 	FACET 	MA3A 	CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					CARBURETOR	FILLED 	B			EBVR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	09	6449M	2888 			CR27388	15284733				NOTED FUEL DRIPPING FROM COWL. UNCOWLED AND FOUND FUEL LEAKING FROM CARBURETOR ENGINE RAN ROUGH AT LOW SPEEDS. PULLED	 CARBURETOR AND FOUND FLOAT FULL OF FUEL. REPLACED WITH NEW. HAD METAL FLOAT REPLACED 10-12-89 UNDER PRECISION SERVICE	 BULLETIN MSA-1.				1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995033100595	19950331	00595		1995	3	31	95ZZZX1464 	4	19950308	G	3422	55C113002	BACK PLATE 	SIGMATEK 																DG GYRO	PORTS CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09					723146E					EDO-AIRE OR SIGMA-TEK DIRECTIONAL GYRO BACK PLATE -- FITTING PORTS CRACKING FROM MECHANIC OVERTIGHTENING FITTINGS. TORQ	UE SHOULD NOT BE MORE THAN 20 INCH/POUNDS, ALSO, SCREW HOLES CAN CRACK FROM INSTRUMENT REPAIRMAN TIGHTENING THESE 5 SCRE	WS TOO TIGHT. SOLUTION TO THIS WOULD BE TO PUT A WARNING STICKER ON THIS BACK PLATE SO IT CAN BE SEEN WHEN INSTALLING F	ITTINGS OR SCREWS IN PLATE. THIS PLATE IS MADE OF A PLASTIC MATERIAL. INSTALL NEW BACK PLATE.																 
1995033100596	19950331	00596	SO 	1995	3	31	95ZZZX1465 	2	19950321	G	8530	646255	PISTON 			CESSNA	172 	172F 	2072414	CE 	CONT 	O300 	O300D 	17022	SO 					NR 3 CYLINDER	CRACKED 	C	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	8677U					17252580	29549D4D			PISTON CRACKED ON NR 3 CYL. TOTAL TIME SINCE O/H MAJOR, 48 HOURS. CRACK WAS FROM LOWER OIL RING GROOVE UPWARD APPROX 1	.5 INCHES. CYLINDER AND ALL COMPONENTS CHECK OUT GOOD. ALL SPECS CHECK GOOD. TELEDYNE CONTINENTAL INSPECTED AND STATE	D THE FAILED PISTON WAS DUE TO BEING ASSEMBLED INCORRECTLY NOT MANUFACTURING. THIS DIAGNOSIS IS IN DISAGREEMENT BY THE 	A & P TECH., THE SAFETY OFFICER AND OWNER.			1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995033100597	19950331	00597	SO 	1995	3	31	95ZZZX1466 	1	19950210	G	8120		TURBOCHARGER 			PIPER 	PA46 	PA46310P 	7104605	SO 	CONT 	O520 	TSIO520BE 	17040	SO 					LT TURBO MOUNT	BOLTS MISSING 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	4378S	1561 				468508009	273622R			DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: LT TURBO MOUNT BOLTS MISSING.						1	L	7	1 	3O	3	O		A25SO 	E8CE				 
1995033100598	19950331	00598	SO 	1995	3	31	95ZZZX1467 	1	19950210	G	8120		TURBOCHARGER 			PIPER 	PA46 	PA46310P 	7104605	SO 	CONT 	O520 	TSIO520BE 	17040	SO 					RT TURBO MOUNT	INCORRECT BOLTS 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	4378S	1561 				468508009	273622R			DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: INCORRECT MOUNT BOLTS IN RT TURBO.						1	L	7	1 	3O	3	O		A25SO 	E8CE				 
1995033100599	19950331	00599	SO 	1995	3	31	95ZZZX1468 	1	19950210	G	7160		CONTROL 			PIPER 	PA46 	PA46310P 	7104605	SO 										LT ALT AIR DOOR	LOOSE 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	4378S	1561 				468508009				DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: LT ALT. AIR DOOR CONTROL NOT SECURE.						1	L	7	1 	3O				A25SO 					 
1995033100600	19950331	00600	SO 	1995	3	31	95ZZZX1469 	1	19950210	G	3060		LEADS 			PIPER 	PA46 	PA46310P 	7104605	SO 										LT PROP DE-ICE	LOOSE 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	4378S	1561 				468508009				DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: LT PROP DE-ICE LEADS LOOSE.						1	L	7	1 	3O				A25SO 					 
1995033100601	19950331	00601	SO 	1995	3	31	95ZZZX1470 	1	19950210	G	8120		FITTING 			PIPER 	PA46 	PA46310P 	7104605	SO 	CONT 	O520 	TSIO520BE 	17040	SO 					LT TURBO WG	MISSING 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	4378S	1561 				468508009	273622R			DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: LT TURBO WASTEGATE DRAIN LINE AND FITTING MISSING.						1	L	7	1 	3O	3	O		A25SO 	E8CE				 
1995033100602	19950331	00602	SO 	1995	3	31	95ZZZX1471 	1	19950210	G	7120		HEAT SHIELD 			PIPER 	PA46 	PA46310P 	7104605	SO 										LT ENG RT MOUNT	MISSING 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	4378S	1561 				468508009				DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: LT ENG RT REAR ENG MOUNT HEAT SHIELD MISSING.						1	L	7	1 	3O				A25SO 					 
1995033100603	19950331	00603	SO 	1995	3	31	95ZZZX1472 	1	19950210	G	7120		MOUNT 			PIPER 	PA46 	PA46310P 	7104605	SO 										LT ENG AFT	BURNED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	4378S	1561 				468508009				DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: LT ENG RT REAR LOWER ENG MOUNT BURNED.						1	L	7	1 	3O				A25SO 					 
1995033100604	19950331	00604	NM 	1995	3	31	95ZZZX1473 	1	19950308	G	5330		SKIN LAP 			BOEING	737 	737247 	138448D	NM 										FS 1006 STR 10	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				CORROSION AT LAP SEAM STRINGER 10 STA 1006 LEFT. OPENED LAP AND CLEANED CORROSION PER SRM 51-10-6.						2	L	7	2 	4F				A16WE 					 
1995033100605	19950331	00605	NM 	1995	3	31	95ZZZX1474 	1	19950313	G	5347		SEAT TRACK 			BOEING	737 	737247 	138448D	NM 										FS 328-360 RBL54	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				SEAT TRACK CORRODED, STA 328 - STA 360 RBL 54. REMOVED AND REPLACED SEAT TRACK PER SRM 51-10-1.						2	L	7	2 	4F				A16WE 					 
1995033100606	19950331	00606	NM 	1995	3	31	95ZZZX1475 	1	19950313	G	5313		STRINGER 			BOEING	737 	737247 	138448D	NM 										FS 907 4L	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				CRACK IN STR 4L, STA 907. REPLACED STRINGER IAW SRM 51-30-1.						2	L	7	2 	4F				A16WE 					 
1995033100607	19950331	00607	NM 	1995	3	31	95ZZZX1476 	1	19950308	G	5311		FRAME 			BOEING	737 	737247 	138448D	NM 										FS 500B STR 25L	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				STA 500B FRAME BETWEEN STR 25L AND STR 26L CORRODED. INSTALLED NEW FRAME SPLICE IAW SRM 51-10-6.						2	L	7	2 	4F				A16WE 					 
1995033100608	19950331	00608	NM 	1995	3	31	95ZZZX1477 	1	19950308	G	5320	18500MAE1	INTERCOSTAL 			BOEING	737 	737247 	138448D	NM 										FS 520 S26L	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				INTERCOSTAL CORRODED ALONG UPPER EDGE BETWEEN FS 500B AND FS 520, S26L. INSTALLED NEW INTERCOSTAL IAW SRM 51-10-01.						2	L	7	2 	4F				A16WE 					 
1995033100609	19950331	00609	NM 	1995	3	31	95ZZZX1478 	1	19950308	G	5753		SUPPORT FITTING 			BOEING	737 	737247 	138448D	NM 										RT OTBD MID-FLAP	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				RT OTBD MID-FLAP INBD THRUST BEARING SUPPORT FITTING HAS CORROSION ON INNER BORE. REMOVED CORROSION PER BOEING DRW 65C2	1592.					2	L	7	2 	4F				A16WE 					 
1995033100610	19950331	00610	NM 	1995	3	31	95ZZZX1479 	1	19950308	G	5313	6545800MAE647	STRINGER 			BOEING	737 	737247 	138448D	NM 										FS 332.1 S10R	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				STRINGER CRACKED STA 332.1, RT IOR. REPLACED STRINGER PER SRM 51-10-2.						2	L	7	2 	4F				A16WE 					 
1995033100611	19950331	00611	NM 	1995	3	31	95ZZZX1480 	1	19950308	G	5320	18511MAE1	ANGLE 			BOEING	737 	737247 	138448D	NM 										FS 312 WL 206.1	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				FLOOR SUPPORT ANGLE CORRODED STA 312, WL 206.1, LBL 20. INSTALLED SUPPORT ANGLE IAW SRM 51-10-1.						2	L	7	2 	4F				A16WE 					 
1995033100612	19950331	00612	NM 	1995	3	31	95ZZZX1481 	1	19950308	G	5347		SEAT TRACK 			BOEING	737 	737247 	138448D	NM 										FS 277-291 RBL40	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	302VA					20126				SEAT TRACK CORROSION, STA 277 - STA 291, 40 INCHES RBL. REMOVED AND REPLACED SEAT TRACK PER SRM 51-10-01.						2	L	7	2 	4F				A16WE 					 
1995033100613	19950331	00613	EU 	1995	3	31	95ZZZX1482 	1	19950223	G	2410		MOUNT ADAPTER 	AUXILEC 	8012F 	SOCATA	TBM 	TBM700 	8682000	EU 										NR 1 ENG GEN	FAILED 	B		A	JAVR	O				OTHER 				H	E		ELECT. POWER LOSS-50 PC 	VIBRATION/BUFFET 		NR	NOT REPORTED 	1			NE	01	700KL	483 			89	88				PILOT REPORTED ENGINE VIBRATION WITH NR 1 GENERATOR FAILURE. INSPECTED ENGINE FOUND GENERATOR MOUNTING ADAPTER COMPLETE	LY FAILED. GENERATOR HANGING FROM WIRES AND RUBBING ON STANDBY GENERATOR DRIVE PULLEY AND BELT. SUBMITTER STATED EXACT	 CAUSE UNKNOWN AT THIS TIME, APPEARS ADAPTER DEFECTIVE, MAY HAVE BECOME PORUS. RECOMMEND SHIELD TO PROTECT STANDBY GENE	RATOR DRIVE. MFG PART NR Z00N6000707222TBM.			1	L	7	1 	3T			RT	A60EU 					 
1995033100614	19950331	00614	WP 	1995	3	31	95ZZZX1483 	2	19950307	G	7250	31038391	SEAL 	GARRTT 	31033152 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					HOT SECTION	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		6117 			0233151180		P70058			DURING HOT SECTION INSPECTION, FOUND PART CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF EITHER PN 3103315-05 OR PN 310	70825-2 TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST FIRST ROTOR ASSY. THIS PARTICULAR PART WAS MODIFIED TO PN 31070	85-2 BY INCORPORATING A SHIM BETWEEN THE ROTATION AIR SEAL AND THE CURVIC COUPLING, BUT WAS NOT RE-IDENTIFIED. SUBMITTE	R BELIEVES THIS INCREASED TENSION IS CAUSING THIS PART TO CRACK. SUGGEST ALLIED SIGNAL ENGINEERING REVIEW THIS PROBLEM.	 SUBMITTER NOTE: THIS IS SECOND ASSY FOUND CRACKED.							4	T			E4WE				 
1995033100615	19950331	00615	WP 	1995	3	31	95ZZZX1484 	2	19950307	G	7250	31038393	SEAL 								GARRTT	TPE331	TPE33112UAR 	01514	WP 					HOT SECTION	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		3581 			1233151972		P70104			DURING HOT SECTION INSPECTION, FOUND PART CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED	 SEAL PLATE TENSION AGAINST FIRST ROTOR ASSY. SUBMITTER BELIEVES THIS INCREASED TENSION IS CAUSING THIS PART TO CRACK. 	 SUGGEST ALLIED SIGNAL ENGINEERING REVIEW PROBLEM.									4	T			E4WE				 
1995033100616	19950331	00616	SO 	1995	3	31	95ZZZX1485 	1	19950308	G	3520	FR141A2	SHUT-OFF VALVE 	BENDIX 		GULSTM	G1159 	G1159 	3953505	SO 										OXYGEN SYSTEM	WRONG PART 	B			JZBR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25	711RL		1772 		912155	025				CREW REPORTED PASSENGER OXYGEN SYSTEM LEAKING. INSPECTED SYSTEM AND FOUND OXYGEN PRESSURE REDUCER/SHUT-OFF VALVE LEAKIN	G. REMOVED VALVE, PN FR-142-A2, SN 91255. ORDERED SAME UNIT AND WAS INFORMED THE PART WAS REALLY A PN FR-141-A2 AND WA	S MIS-LABLED AS A FR-142-A2. AN FR-142-A2 VALVE IS USED WITH CO2 AND IN AN APPLICATION TO INFLATE LIFE RAFTS, IT IS, AL	SO, NOT SIMILAR TO AN FR-141-A2 VALVE IN APPEARANCE. THE CORRECT PART WAS THEN ORDERED AND RECEIVED WITH NO DISCREPANCI	ES. LANDINGS, 116.		2	L	7	2 	4F			RT	A12EA 					 
1995033100618	19950331	00618	CE 	1995	3	31	95ZZZX1487 	1	19950306	G	7830	23220258511	INNER ARM 		23420000 	RKWELL	NA265 	NA26580 	7630108	CE 										THRUST REVERSER	MISMANUFACTURED 	B		A	IY2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15	80LX					38051				ARMS ARE MANUFACTURED BY LEARJET UNDER PMA. BIZJET RECEIVED AND PUT IN STOCK 1 EACH DASH 511 ARM AND 6 EACH DASH 512 AR	MS. ONE EACH DASH 511 ARM AND 2 EACH DASH 512 ARMS WERE INSTALLED ON A CUSTOMER'S AIRCRAFT. BIZJET'S PURCHASING AGENT 	WAS NOTIFIED BY A LEAR SALES REP THAT THE ARMS WERE SHIPPED BEFORE THEY WERE HEAT-TREATED AND NEEDED TO BE SHIPPED BACK 	TO LEAR. CUSTOMER WITH THE ARMS ON T/R HAS BEEN NOTIFIED. THESE ARMS ARE IN HIGH DEMAND AND THE AMOUNT OF SUPPLIERS IS	 LIMITED, SO A HIGH QUANTITY COULD HAVE BEEN SHIPPED IN THIS CONDITION.		2	L	7	2 	4F				A2WE 					 
1995033100619	19950331	00619	CE 	1995	3	31	95ZZZX1488 	1	19950306	G	7830	23220258512	INNER ARM 		23420000 	RKWELL	NA265 	NA26580 	7630108	CE 										THRUST REVERSER	MISMANUFACTURED 	B		A	IY2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15	80LX					38051				ARMS ARE MANUFACTURED BY LEARJET UNDER PMA. BIZJET RECEIVED AND PUT IN STOCK 1 EACH DASH 511 ARM AND 6 EACH DASH 512 AR	MS. ONE EACH DASH 511 ARM AND 2 EACH DASH 512 ARMS WERE INSTALLED ON A CUSTOMER'S AIRCRAFT. BIZJET'S PURCHASING AGENT 	WAS NOTIFIED BY A LEAR SALES REP THAT THE ARMS WERE SHIPPED BEFORE THEY WERE HEAT-TREATED AND NEEDED TO BE SHIPPED BACK 	TO LEAR. CUSTOMER WITH THE ARMS ON T/R HAS BEEN NOTIFIED. THESE ARMS ARE IN HIGH DEMAND AND THE AMOUNT OF SUPPLIERS IS	 LIMITED, SO A HIGH QUANTITY COULD HAVE BEEN SHIPPED IN THIS CONDITION.		2	L	7	2 	4F				A2WE 					 
1995033100620	19950331	00620	EU 	1995	3	31	95ZZZX1489 	1	19950228	G	2740		LEVER ARM 			SOCATA	TB9 	TB9 	8680694	EU 										STABILATOR	RIVET BROKEN 	B	S	A	DYTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	15	141ER	1949 				1335				DURING 100-HOUR INSPECTION, FOUND TOP RIVET CONNECTING THE STABILATOR LEVER ARM TO THE CONTROL PYLON BROKEN. LOOKED UP 	THE PROPER PART NUMBER TO REPLACE THE RIVET, FOUND THE PARTS BOOK CALLED FOR TWO BOLTS, NOT RIVETS. ALSO, INSPECTED ACF	T N243ER, SN 1336, MODEL TB-9, AND FOUND SAME IMPROPER HARDWARE. THERE ARE 26 SOCATA TB-9'S IN THE FLEET THAT ARE MAINT	AINED.			1	L	7	1 	3O			NT	AS1EU 					 
1995033100621	19950331	00621	NM 	1995	3	31	95ZZZX1490 	1	19950208	G	5320	65564417	CHORD 			BOEING	727 	7272J7 	138400E	NM 										FS 970	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	905PG	44145	44145			20571				DURING BELLY SKIN REPLACEMENT, CHORD, PN 65-56441-7, WAS FOUND CORRODED. FROM EXAMINATION, IT APPEARS THERE WAS NOT ENO	UGH CORROSION PREVENTION AND, ALSO, MOISTURE BUILD-UP. CHECKING DRAIN HOLES IN LOWER SKIN AND MORE EFFORT USED DURING I	NSPECTION.				2	L	7	3 	4F				A3WE 					 
1995033100623	19950331	00623	CE 	1995	3	31	95ZZZX1492 	1	19950315	G	5414	45A3442033	SKIN 			BEECH 	MU300 	400BEECH 		CE 										LT PYLON	CRACKS 	B		A	JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	1564B	2506 				RJ64				NUMEROUS LOOSE RIVETS IN LEFT AND RIGHT WING LOWER PYLON SKINS (AFT). ORIGINAL SKIN THICKNESS .025 INCH 2024T3. SKIN T	OO THIN FOR RIVET REPLACEMENT EFFECTIVELY. REPLACED LEFT AND RIGHT LOWER PANEL SKINS WITH .032 INCH 2024T3 PANELS FABRI	CATED. (SEE 337 DATED 3/95).				2	H	7	2 	4F			RT	A16SW 					 
1995033100624	19950331	00624	CE 	1995	3	31	95ZZZX1493 	1	19950315	G	5414	45A3442034	SKIN 			BEECH 	MU300 	400BEECH 		CE 										RT PYLON	CRACKS 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	1564B	2506 				RJ64				NUMEROUS LOOSE RIVETS IN LEFT AND RIGHT WING LOWER PYLON SKINS (AFT). ORIGINAL SKIN THICKNESS .025 INCH 2024T3. SKIN T	OO THIN FOR RIVET REPLACEMENT EFFECTIVELY. REPLACED LEFT AND RIGHT LOWER PANEL SKINS WITH .032 INCH 2024T3 PANELS FABRI	CATED. (SEE 337 DATED 3/95).				2	H	7	2 	4F			RT	A16SW 					 
1995033100625	19950331	00625	SO 	1995	3	31	95ZZZX1494 	1	19950303	G	5320	1159B2131741	DOUBLER 			GULSTM	G1159 	G1159 	3953505	SO 										FS 580	MISMANUFACTURED 	B		A	OS5R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	187PH					218				WHILE REPAIRING CORROSION FOUND DURING INSPECTION OF THE FS 580 BULKHEAD, ALL 3 SKIN DOUBLERS AT FS 580 HAD TO BE REPLAC	ED DUE TO CORROSION DAMAGE. ALL 3 DOUBLERS WERE ORDERED FROM THE MANUFACTURER. THE OUTBOARD AND INBOARD DOUBLERS WERE 	RECEIVED AND DETERMINED TO BE SATISFACTORY. THE MIDDLE DOUBLER WAS FOUND TO BE .125 INCH SMALLER AROUND THE ENTIRE LENG	TH OF THE OLD PART. THE MANUFACTURER WAS NOTIFIED AND A SECOND REPLACEMENT DOUBLER WAS SENT. THE SECOND DOUBLER WAS FO	UND TO BE IDENTICAL TO THE FIRST REPLACEMENT. MFG STATES DOUBLERS WERE THE CORRECT SIZE AND WERE BEING USED ON G1159, G	1159A, G1159B, AND GIV'S.	2	L	7	2 	4F			RT	A12EA 					 
1995033100626	19950331	00626	SO 	1995	3	31	95ZZZX1495 	1	19950303	G	5312		BULKHEAD 			GULSTM	G1159 	G1159 	3953505	SO 										FS 580	CORRODED 	B			OS5R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	187PH					218				WHILE REPAIRING CORROSION FOUND DURING INSPECTION OF THE FS 580 BULKHEAD, ALL 3 SKIN DOUBLERS AT FS 580 HAD TO BE REPLAC	ED DUE TO CORROSION DAMAGE. ALL 3 DOUBLERS WERE ORDERED FROM THE MANUFACTURER. THE OUTBOARD AND INBOARD DOUBLERS WERE 	RECEIVED AND DETERMINED TO BE SATISFACTORY. THE MIDDLE DOUBLER WAS FOUND TO BE .125 INCH SMALLER AROUND THE ENTIRE LENG	TH OF THE OLD PART. THE MANUFACTURER WAS NOTIFIED AND A SECOND REPLACEMENT DOUBLER WAS SENT. THE SECOND DOUBLER WAS FO	UND TO BE IDENTICAL TO THE FIRST REPLACEMENT. MFG STATES DOUBLERS WERE THE CORRECT SIZE AND WERE BEING USED ON G1159, G	1159A, G1159B, AND GIV'S.	2	L	7	2 	4F			RT	A12EA 					 
1995033100627	19950331	00627	CE 	1995	3	31	95ZZZX1496 	1	19950220	G	3230	0842102	BELLCRANK 			CESSNA	310 	310Q 	2074242	CE 										NLG	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	7666Q					310Q0445				TWO SPACERS BETWEEN ROD END AND BELLCRANK WERE MISSING. THIS COULD HAVE CAUSED STRESS IN BROKEN AREA.						1	L	7	2 	3O				3A10 					 
1995033100630	19950331	00630	WP 	1995	3	31	95ZZZX1499 	1	19950309	G	6210	269A505071	BEARING 			HUGHES	269 	269C 	4470504	WP 										FLAPPING HINGE	FAILED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	103WP	4001 				S1573				WHILE PERFORMING A 400-HOUR INSPECTION OF THIS AIRCAFT, THE INNER RACE OF THE FLAPPING HINGE BEARING WAS FOUND BRINNELLE	D IN TWO AREAS BEYOND THE ACCEPTABLE LIMITS. THIS BEARING WAS NEW AT THE LAST 400-HOUR INSPECTION. SUSPECT CONTAMINATI	ON INTRODUCED DURING MANUFACTURING OF BEARING OR DURING SERVICE. MAIN ROTOR BLADE WAS REMOVED FROM SERVICE AND RENDERED	 UNAIRWORTHY PER MM.			1	G	7	1 	3O				4H12 					 
1995033100631	19950331	00631	EU 	1995	3	31	95ZZZX1500 	1	19950222	G	6210	117150051	BLADE 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R	BULGED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	118LL	4055 				7097				MAIN ROTOR BLADE BALANCE WEIGHT IS COMPRESSING DUE TO CENTRIFUGAL FORCE CAUSING THE LEAD TO BULGE THE BLADE BEYOND MANUF	ACTURER'S LIMITS, THUS, RENDERING THE BLADE UNSERVICEABLE.					1	G	7	2 	3U				H13EU 					 
1995033100632	19950331	00632	WP 	1995	3	31	95ZZZX1501 	1	19950227	G	6310	269A5480	SPRING 		269A5482 	HUGHES	269 	269A 	4470402	WP 										M/R DR CLUTCH	COIL BROKEN 	B			DRRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	8724F	44 				120039				TENSION SPRING FOR MAIN ROTOR DRIVE CLUTCH ACTUATOR FAILED. RECEIVED AND INSTALLED NEW SPRING ON 27 JAN 95. AIRCRAFT F	LEW ON 19 FEB 95 AND BROKEN SPRING WAS DISCOVERED ON DAILY INSPECTION ON THE MORNING OF 20 FEB 95.					1	G	7	1 	3O				4H12 					 
1995033100633	19950331	00633	WP 	1995	3	31	95ZZZX1502 	1	19950310	G	6320	369D2512711	GEAR TOOTH 		369D25100505	HUGHES	369 	369D 	4470706	WP 										M/R XMSN	FAILED 	B			EOOR	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			AL	03	5074R	472 			0055700950	1151D				PILOT REPORTED A M/R TRANS CHIP LIGHT. INITIAL INSPECTION FOUND A DOT SIZED CHIP. THE AIRCRAFT WAS RUN UP AND AT 108 P	ERCENT FLIGHT IDLE A LOUD KNOCKING NOISE WAS HEARD FROM THE TRANSMISSION. REMOVAL AND SUBSEQUENT DISASSEMBLY FOUND A 1 	INCH SECTION OF A TOOTH MISSING FROM THE RING GEAR. THIS TOOTH DAMAGED THE REST OF THE GEARS IN THE TRANSMISSION.				1	G	7	1 	3U				H3WE 					 
1995033100634	19950331	00634	SW 	1995	3	31	95ZZZX1503 	1	19950208	G	5302	206031329003	FITTING 			BELL 	206 	206L3 	1182108	SW 										TAILBOOM ATTACH	CRACKED 	B	S		PN5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	937S	2811 				51258				TAILBOOM ATTACH FITTING FOUND CRACKED ON ROUTINE INSPECTION. FITTING AND LONGERON WERE REPLACED IAW BELL 206 SRM.						1	G	7	1 	3U				H2SW 					 
1995033100636	19950331	00636	EU 	1995	3	31	95ZZZX1505 	1	19950223	G	6310	350A32106046	BOLTS 		350A54020638	AEROSP	AS355 	AS355F1 	8680810	EU 										GEARBOX FLANGE	SHEARED 	H		A		A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			SW	03	5796T	135 				5166				IN-FLIGHT AT CRUISE, ACFT N5796T EXPERIENCED A SHATTERING OF THE NR 2 ENGINE TO C-BOX DISC COUPLING. THE 3 BOLTS ATTACH	ING THE DISC COUPLING TO THE C-BOX FLANGE WERE SEVERED AT THE COTTER PIN HOLES. CONTROL NR 95-005-6310.					1	G	7	2 	3U				H11EU 					 
1995040700191	19950407	00191	CE 	1995	4	7	95ZZZX1584 	1	19950321	G	7430	CH31876	IGNITER 	CHAMPION 		CESSNA	525 	525 	2076601	CE 	WILINT	FJ44 	FJ44 	66000	GL 					RT ENGINE	BROKEN 	B			NVIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	12PA	455 				5250012	1048			WHILE PERFORMING A CHECK-1 IAW WILLIAMS INTERNATIONAL FJ44-1A INSPECTION GUIDE, DISCOVERED THE ELECTRODE INSULATOR ON TH	E RT ENGINE INBOARD IGNITER HAD BROKEN OFF. A BORESCOPE INSPECTION WAS PERFORMED WHICH REVEALED DAMAGE TO THE TURBINE S	ECTION. THE ENGINE WAS REMOVED AND RETURNED TO THE MANUFACTURER FOR REPAIR.				1	L	7	2 	4F	4	F	RT	A1WI 	E3GL				 
1995040700193	19950407	00193	SO 	1995	4	7	95ZZZX1586 	1	19950308	G	5610	1159SCB31024	WINDSHIELD 			GULSTM	G1159 	G1159A 	3970109	SO 										COCKPIT	CRACKED 	H				A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			SW	99	300M	2786 			417	417				COPILOT'S WINDSHIELD, OUTER PANEL SHATTERED AT FL 450. NO EMERGENCY ACTION WAS REQUIRED. DIVERTED TO DALLAS LOVE FIELD	, AVIALL, FOR WINDSHIELD CHANGE. PART 91 OPERATION C/W FLIGHT MANUAL REQUIREMENTS ADDRESSING OUTER PANEL CRACKING.					2	L	7	2 	4F				A12EA 					 
1995040700194	19950407	00194	CE 	1995	4	7	95ZZZX1587 	1	19950207	G	3240	2307003328	LINE 			LEAR 	35 	35A 	5170602	CE 										BRAKE PRESS	CHAFED 	B		A	L4JR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	969MC	5106 				590				LINES WERE CHAFING ON CLAMP ATTACHED TO GEAR DOOR ACTUATOR. LINE NEEDS SMALL BEND AT THIS AREA FOR PROPER CLEARANCE. (L	INES WERE .50 INCH TO .75 INCH CHAFED THROUGH WALL THICKNESS). LINES LOCATED IN AT WHEELWELL.					2	L	7	2 	4F				A10CE 					 
1995040700195	19950407	00195	CE 	1995	4	7	95ZZZX1588 	1	19950207	G	3240	2307003328	LINE 			LEAR 	35 	35A 	5170602	CE 										BRAKE PRESS	CHAFED 	B		A	L4JR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	81MR	2697 				622				LINES WERE CHAFING ON CLAMP ATTACHED TO GEAR DOOR ACTUATOR. LINE NEEDS SMALL BEND AT THIS AREA FOR PROPER CLEARANCE. (	LINES WERE .50 INCH TO .75 INCH CHAFED THROUGH WALL THICKNESS.) LINES LOCATED IN AT WHEELWELL.					2	L	7	2 	4F				A10CE 					 
1995040700196	19950407	00196	EU 	1995	4	7	95ZZZX1589 	1	19950306	G	2910	257EK173	ADAPTER 			BRAERO	DH125 	HS125700A 	4230170	EU 										HYD PUMP	CRACKED 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	15	540B	6890 				NA0255				RIPPLE SUPPRESSOR TO HYDRAULIC PUMP ADAPTER WAS FOUND CRACKED ON POST-FLIGHT. CREW NOTED POOL OF HYDRAULIC FLUID UNDER 	LEFT ENGINE. THIS PART APPEARS TO HAVE DEFECTIVE METAL CASTING.					2	L	7	2 	4F				A3EU 					 
1995040700197	19950407	00197	CE 	1995	4	7	95ZZZX1590 	1	19950306	G	2720	3363000069	TORQUE TUBE 			BEECH 	36 	B36TC 	1151609	CE 										RUDDER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05	65031	1548 				EA334				WHILE C/W AD 93-24-03, THE RUDDER TORQUE TUBE ASSY WAS FOUND CRACKED AT THE UPPER ATTACH POINT WELDS ON BOTH SIDES OF TH	E TUBE. THE UPPER ATTACH POINT OF THE TORQUE TUBE IS RIVETED TO THE RUDDER SKIN AND THESE RIVETS SHOWED SIGNS OF WORKIN	G. SUGGEST TECHNICIANS INSPECT THIS AREA EXTERNALLY FOR WORKING RIVETS WHICH MAY BE A SIGN THAT THE TORQUE TUBE WELDS A	RE CRACKED.			1	L	7	1 	3O				3A15 					 
1995040700198	19950407	00198	SO 	1995	4	7	95ZZZX1591 	1	19950218	G	7160	8972102	AIRBOX 			PIPER 	PA46 	PA46350P 		SO 										INDUCT SYSTEM	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	1818W	238 				4622151				ON INSPECTION, FOUND FOUR HOLES CHAFED INTO INDUCTION AIRBOX AFT OF AIR FILTER. SUSPECT CAUSED BY STAPLES SECURING BAFF	LE SEAL OF CENTER BAFFLE. SUGGEST CLEARANCE BETWEEN CENTER BAFFLE AND AIRBOX BE INCREASED TO AVOID DAMAGE.					1	L	7	1 	3O			RT	A25SO 					 
1995040700199	19950407	00199	SO 	1995	4	7	95ZZZX1592 	1	19950320	G	7922	53E19600	VALVE 			PIPER 	PA32 	PA32R301 	7103218	SO 										THERMO BYPASS	NUT CRACKED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15	9087V					32R8613005				REMOVED THERMOSTATIC BYPASS VALVE TO C/W SB 518A, FOUND NOT TO PASS DIMENSIONAL CHECK. ORDERED NEW VALVE WITH HIGHER SE	RIAL NUMBER TO EXTEND SB COMPLIANCE TIME TO ANNUAL. UPON INSPECTION OF NEW VALVE, FOUND CRIMPED NUT TO HAVE CRACK THAT 	APPEARS TO BE CAUSED BY STRESS IN PROCESS OF CRIMPING TO LYCOMING SPECS. SUBMITTER REQUESTS ENG AD TO INSPECT/RECALL AL	L VALVES (NEW) FOR CRACKED CRIMPED NUT. IN THIS CASE, THE CURE IS WORSE THAN THE ILLNESS.			1	L	7	1 	3O				A3SO 					 
1995040700200	19950407	00200	SO 	1995	4	7	95ZZZX1593 	1	19950126	G	7922	53E19600	VALVE 			PIPER 	PA44 	PA44180 	7104402	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	854ND					4495008				INSPECTED VALVES IN BOTH ENGINES. NUT SWAGE DIMENSIONS ARE APPROXIMATELY .200 INCH. BOTH BYPASS VALVES CRIMP NUTS LOOS	E.					1	L	7	2 	3O				A19S0 					 
1995040700201	19950407	00201	SO 	1995	4	7	95ZZZX1594 	1	19950316	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	4093W				38158	318152176				WHILE PERFORMING LYCOMING MANDATORY SB NR 518A, FOUND THERMOSTATIC BYPASS VALVE CRIMP NUT VERY LOOSE. SUBMITTER STATES 	3 OF 4 VALVES CHECKED WERE BAD.					1	L	7	2 	3O				A20SO 					 
1995040700202	19950407	00202	SO 	1995	4	7	95ZZZX1595 	1	19950317	G	5751		GAP SEAL 			PIPER 	PA28 	PA28181 	7102807	SO 										LT-RT AILERON	RIVET CHAFE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	47971	555 				287890163				KNOTS 2U AILERON AND FLAP SEALS INSTALLED (5-20-86 TACH 948.94) UNDER STC SA 640GL. DURING AILERON DOWN-TRAVEL, THE UND	ERSIDE AILERON RIVETS (SKIN TO AILERON SPAR) RUB ON THE GAP SEAL WEARING THE RIVET HEADS APPROXIMATELY 50 PERCENT IN SOM	E AREAS AS RIVETS ARE REPLACED AND LARGER HEADED RIVETS ACT AS RUB BUTTONS AND WEAR DOWN. SUGGEST NYLON RUB STRIPS BE A	TTACHED TO THE AILERON (AND BALANCE).			1	L	7	1 	3O				2A13 					 
1995040700203	19950407	00203	GL 	1995	4	7	95ZZZX1596 	1	19950128	G	2750	19559840	CONTROL CABLE 			BLANCA	17 	1731A 	1220435	GL 										RT OTBD FLAP	RUSTED 	D				O				OTHER 				F			FLT CONT AFFECTED 			CR	CRUISE 	1			SW	17	4205B	1914 				7532146				THE PILOT REPORTED FLAP CABLE BROKE DURING FLIGHT. PILOT STATED WHEN ON FULL FLAP POSITION, HE HEARD A LOUD THUMP AND A	IRCRAFT STARTED TO ROLL ON RIGHT WING. PILOT NOTED RIGHT FLAP WAS ON THE 'UP' POSITION, SO HE RAISED LEFT FLAP AND LAND	ED SAFELY. AN INVESTIGATION REVEALED THE RIGHT OUTBOARD FLAP CABLE BROKE AT THE SWAGED END FITTING DUE TO RUST WHICH MA	DE IT HARD TO INSPECT. MORE ATTENTION SHOULD BE TAKEN DURING A PREFLIGHT TO CATCH THIS PROBLEM WHEN IT STARTS.			1	L	7	1 	3O			 	A18CE 					 
1995040700204	19950407	00204	CE 	1995	4	7	95ZZZX1597 	1	19950319	G	3250	0760135106	CONTROL CABLE 			CESSNA	185 	A185F 	2072821	CE 										TAIL WHEEL	FAILED 	D				O				OTHER 				E			VIBRATION/BUFFET 			LD	LANDING 	1			SW	17	714HE	890 				18504396				DURING A LANDING, PILOT NOTICED TAIL WHEEL HAD A VIBRATION. INSPECTION REVEALED THE TAIL WHEEL RT CONTROL CABLE HAD BRO	KEN AT THE AFT SWAGED END.					1	H	7	1 	3O			 	3A24 					 
1995040700205	19950407	00205	CE 	1995	4	7	95ZZZX1598 	1	19950208	G	2510	0514181	SEAT 			CESSNA	172 	172P 	2072436	CE 										LT SIDE RAIL	FAILED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	50934	8458 				17274237				SEAT FAILED AFT OF SEAT BACK RECLINE PISTON ATTACH POINT, ALLOWING BACK TO MOVE AFT. SUBMITTER SUSPECTS HIGH TIME AND P	ILOTS USING LEFT FRONT CORNER OF SEAT TO HELP GET IN ACFT CAUSE OF FAILURE.					1	H	7	1 	3O			NT	3A12 					 
1995040700206	19950407	00206	CE 	1995	4	7	95ZZZX1599 	1	19950113	G	3260		SOCKET ASSY 			BEECH 	58 	58 	1152740	CE 										DOWNLOCK LIGHT	FAILED 	D				O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			GL	07	1012W					TH305				DURING APPROACH HAD NO GEAR DOWN INDICATION. FOUND DOWN AND LOCK LIGHT SOCKET FAILED. REMOVED AND REPLACED SOCKET ASSY	. CHECKS GOOD.					1	L	7	2 	3O				3A16 					 
1995040700208	19950407	00208	SO 	1995	4	7	95ZZZX1601 	2	19950321	G	8520		CONNECT ROD 			PIPER 	PA28 	PA28R201T 	7102813	SO 	CONT 	O360 	TSIO360FB 	17025	SO 					NR 3-4	FAILED 	G				K				NONE 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			WP	23	2443M	1328 				28R7803128				THIS ENGINE, CONVERTED FROM A TSIO-360-GB, HAD NR 3 AND NR 4 CONNECTING RODS FAIL AT THE SAME TIME KNOCKING A HOLE IN TH	E UPPER CASE AREA OF ABOUT 8 INCHES DIAMETER. TELEDYNE-CONTINENTAL SB M86-11 R1 PERTAINS TO THIS SUB JECT.					1	L	7	1 	3O	3	O		2A13 	E9CE				 
1995040700209	19950407	00209	EA 	1995	4	7	95ZZZX1603 	2	19950321	G	8520		CRANKCASE 			PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	O540B1B5 	41532	EA 					LT ENGINE	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	4529P				2500	2733	L110440			CRANKCASES FOUND CRACKED AND FRETTING AROUND MAIN BEARING SUPPORT STRUCTURE IN THE AREA OF THE CRACKED CRANKSHAFTS.						1	L	7	2 	3O	3	O		1A10 	E295				 
1995040700210	19950407	00210	EA 	1995	4	7	95ZZZX1604 	2	19950321	G	8520		CRANKCASE 			PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	O540B1B5 	41532	EA 					RT ENGINE	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	4529P				2500	2733	L128540			CRANKCASES FOUND CRACKED AND FRETTING AROUND MAIN BEARING SUPPORT STRUCTURE IN THE AREA OF THE CRACKED CRANKSHAFTS.						1	L	7	2 	3O	3	O		1A10 	E295				 
1995040700211	19950407	00211	CE 	1995	4	7	95ZZZX1607 	1	19950313	G	5711	04111086	SPAR 			CESSNA	150 	150M 	2071830	CE 										AFT DOOR POST	CORRODED 	D		a		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	66786	3492 				15076279				AFTER REMOVING HEADLINER TO REPLACE SPEAKER, FOUND REAR CARRY-THROUGH SPAR WITH CORROSION. CORROSION NOT VISIBLE WITH H	EADLINER IN PLACE. SUSPECT LINER IS HOLDING MOISTURE THAT GETS IN AROUND WING TO FUSELAGE FAIRING ASSY.					1	H	7	1 	3O				3A19 					 
1995040700212	19950407	00212	CE 	1995	4	7	95ZZZX1608 	1	19950313	G	3246	C301631	FLANGE 	MCAULY 	C1630370101 	CESSNA	150 	150M 	2071830	CE 										INBOARD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	6678L	3492 				15076279				WHILE REMOVING WHEEL TO ROTATE TIRE, FOUND BOTH INBD FLANGES NEXT TO BRAKE DISK CRACKED. TAB FLANGE FOR COVER DELAMINAT	ED BOTH SIDES OF TAB. CRACKS IN RELIEVED AREA .1250 INCH TO .50 INCH LONG. THE 1 INCH REPLACEMENT FLANGE ALSO CRACKED.	 HEAT FROM BRAKE DISK SUSPECT CAUSE OF STRESS. SUBMITTER SUGGESTS TO INSPECT EACH 100 HOURS.				1	H	7	1 	3O				3A19 					 
1995040700213	19950407	00213	CE 	1995	4	7	95ZZZX1609 	1	19950302	G	3340	112205101	BREAKER 			CESSNA	310 	310R 	2074245	CE 										NAV LIGHTS	FAILED 	B			EWGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	05	133CW	5861 				310R1260				NAVIGATION LIGHTS CIRCUIT BREAKER DID NOT TRIP OFF AS A RESULT OF A SHORTED WIRE. THIS OVERHEATED THE WIRE ALLOWING IT 	TO MELT THE INSULATION OFF OF TWO OTHER CIRCUITS WHICH SHORTED OUT THESE CIRCUITS AND THEIR RESPECTIVE CIRCUIT BREAKERS 	TRIPPED.				1	L	7	2 	3O				3A10 					 
1995040700214	19950407	00214	CE 	1995	4	7	95ZZZX1610 	1	19950127	G	6123	A3496	SPRING 			BEECH 	300 	300BEECH 	1152930	CE 						HARTZL	HCB4M	HCB4M 	GL 	PROP FEATHER	BROKEN 	B			FR6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03								FW271		PROPELLER WAS IN FOR CALENDER TIME OVERHAUL. AFTER DISASSEMBLY, FEATHER ASSIST SPRING WAS FOUND BROKEN IN FOUR PIECES. 	 THIS PROBLEM WOULD CAUSE THE PROP TO NOT FULLY FEATHER AND/OR SURGING OF RPM DUE TO NOT HAVING ENOUGH SPRING PRESSURE.					2	L	7	2 	4T				A24CE 		6	C	P56GL	 
1995040700215	19950407	00215	GL 	1995	4	7	95ZZZX1611 	3	19950127	G	6111	82NC	BLADE 			CESSNA	188 	188CESSNA 	2073002	CE 						MCAULY	3A32C	D3A32C90 	GL 	30 INCH STA	FAILED 	B			FR6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03		600 						890477		PROPELLER HAD BLADE FAILURE AT THE 30 INCH STATION. DURING DISASSEMBLY, ALSO NOTICED THAT AT LAST ASSY, THE A4140 LOCKI	NG PLUGS FOR THE BLADE RETENTION NUTS HAD NOT BEEN INSTALLED. AFTER FURTHER DISASSEMBLY, THE BLADE THAT HAD FAILED ALSO	 HAD A CRACKED BLADE RETENTION FERRULE.				1	L	7	1 	3O				A9CE 		5	C	P21EA	 
1995040700216	19950407	00216		1995	4	7	95ZZZX1612 	4	19950207	G	2562		ELT1104 	ARTEX 		BEECH 	58 	58 	1152740	CE 										FUSELAGE	ACTIVATED 	B			EHHR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	1556J	1200 			41585	TH1629				ELT FOUND ACTIVATED (SENDING SIGNAL). RESET UNIT, SIGNAL STOPPED 15 MINUTES.						1	L	7	2 	3O				3A16 					 
1995040700217	19950407	00217	SW 	1995	4	7	95ZZZX1613 	1	19950112	G	2434	ALX9425B	ALTERNATOR 	PRESTOLITE 		MOONEY	M20 	M20K 	5870220	SW 										DC SYSTEM	FAILED 	B			CCAR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	331DF	33 			4013156	25003				SUBMITTER STATES TO HAVE HAD NUMEROUS FAILURES OF THIS MODEL ALTERNATOR ON AIRCRAFT. IT IS UNUSUAL TO GET MORE THAN 100	 HOURS OUT OF AN ALTERNATOR.					1	L	7	1 	3O				2A3 					 
1995040700218	19950407	00218	SO 	1995	4	7	95ZZZX1614 	1	19950315	G	2810	63913193	HOSE 			PIPER 	PA28 	PA28180 	7102808	SO 										TANK VENT LINE	CRACKED 	B		A	IGXR	O				OTHER 				K			FLUID LOSS 			CL	CLIMB 	1			NE	05	66AS	2448 				284939				FUEL SMELL ON CLIMB OUT ONLY WITH TANKS TOPPED. FOUND RUBBER COUPLINGS SPLIT ON VENT LINE ON LEFT TANK. THIS AREA IS N	OT INSPECTABLE UNLESS THE FUEL TANK IS REMOVED FROM THE WING. THE TANK IS A REMOVABLE 'WET WING' DESIGN. THERE ARE 2 C	OUPLINGS PER TANK. THIS IS A 1968 AND THESE ARE BELIEVED TO BE ORIGINAL.				1	L	7	1 	3O				2A13 					 
1995040700219	19950407	00219	SO 	1995	4	7	95ZZZX1615 	1	19950315	G	2810	63913194	HOSE 			PIPER 	PA28 	PA28180 	7102808	SO 										TANK VENT LINE	CRACKED 	B			IGXR	O				OTHER 				K			FLUID LOSS 			CL	CLIMB 	1			NE	05	66AS	2448 				284939				FUEL SMELL ON CLIMB OUT ONLY WITH TANKS TOPPED. FOUND RUBBER COUPLINGS SPLIT ON VENT LINE ON LEFT TANK. THIS AREA IS N	OT INSPECTABLE UNLESS THE FUEL TANK IS REMOVED FROM THE WING. THE TANK IS A REMOVABLE 'WET WING' DESIGN. THERE ARE 2 C	OUPLINGS PER TANK. THIS IS A 1968 AND THESE ARE BELIEVED TO BE ORIGINAL.				1	L	7	1 	3O				2A13 					 
1995040700220	19950407	00220	SO 	1995	4	7	95ZZZX1616 	2	19950220	G	8530	SA629690	WRIST PIN 			CESSNA	172 	R172K 	2072431	CE 	CONT 	O360 	IO360K 	17025	SO 					NR 3 CYLINDER	FAILED 	D	P			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CE	01	736DN	60 				R1722446	3535454			PISTON WRIST PIN BROKE IN NR 3 CYLINDER CAUSED PISTON SKIRT TO BREAK. POLLUTED THE ENGINE WITH ALUMINUM. DAMAGED NR 3 	CYLINDER, ROD, AND NR 4 PISTON WAS MARRED. THE ONLY INDICATION OF A PROBLEM WAS THE OIL PRESSURE DROPPED OFF TO HALF OF	 NORMAL DUE TO METAL PARTICLES GETTING INTO PRESSURE SEAT.				1	H	7	1 	3O	3	O		3A17 	E1CE				 
1995040700221	19950407	00221	SW 	1995	4	7	95ZZZX1617 	1	19950314	G	5347		SEAT TRACK 			MOONEY	M20 	M20C 	5870208	SW 										CABIN FLOOR	HOLES WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	9682M	3289 				670018				SEAT ADJUSTMENT TRACKS (BOTH LT & RT SEATS) HAVE BECOME IMPACTED WITH DUST & CABIN DEBRIS COMBINED WITH TRACK LUBRICANT 	FILLING THE BLIND HOLES SO THAT THE SEAT LOCKING PINS HAD LITTLE PENETRATION IN SEAT TRACK. THIS POTENTIAL PROBLEM IS C	OMPOUNDED BY SEAT TRACK HOLES BEGINNING TO SHOW SIGNS OF RAMP & FUNNEL WEAR AT THE TOP. OWNER/PILOT OF THIS ACFT DID NO	T EXPERIENCE A SEAT LOCKING FAILURE, BUT IT WAS APPARENT THAT ONE-HALF OF THE HOLES WERE CLOSE TO MALFUNCTIONING. RECOM	MEND THE HOLES BE CHECKED & CLEANED EVERY ANNUAL INSPECTION IF NECESSARY. TOTAL AIRFRAME TIME 3,289 HOURS.		1	L	7	1 	3O				2A3 					 
1995040700222	19950407	00222	SO 	1995	4	7	95ZZZX1618 	1	19950316	G	3411		LINE 			PIPER 	PA44 	PA44180T 	7104404	SO 										LT PITOT/STATIC	CHAFED 	D	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	8244Q					448107011				LEFT WING PITOT AND STATIC LINES CHAFING AT 2 BULKHEADS IN NACELLE JUST AFT OF FIREWALL. BOTH LINES ARE AL. .1875 INCH 	AND BOTH WERE CHAFED ALMOST THROUGH. SUBMITTER SUGGESTS THERE NEEDS TO BE RUBBER GROMMETS INSTALLED IN THOSE .5625 INCH	 HOLES. INSTALLED GROMMETS AND INSTALLED NEW TUBING WITH AN 'AN' FITTING SPLICE ON INBOARD SIDE AND RECONNECTED TO BULK	HEAD FITTING ALREADY THERE.			1	L	7	2 	3O				A19SO 					 
1995040700223	19950407	00223	SO 	1995	4	7	95ZZZX1619 	1	19950216	G	3250	35192000	STEERING HORN 			PIPER 	PA28 	PA28161 	7102803	SO 										NLG	CRACKED 	B	S	A	AD4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	2480Q	6300 				288516067				SUBMITTER STATES THIS IS THE FOURTH STEERING ARM FOUND CRACKED. THIS ARM CHANGED ON PA28-161 AND DASH 181 WITH A TALLER	 MOUNT FOR THE STEERING RODS TO ATTACH. SUBMITTER THINKS THE ADDED FORCE, WITH TIME, IS CRACKING THE HORN AT THE FLAT P	LATE.				1	L	7	1 	3O				2A13 					 
1995040700224	19950407	00224	GL 	1995	4	7	95ZZZX1620 	2	19950307	G	7200		ENGINE 			BELL 	206 	206L 	1181522	SW 	ALLSN 	250C 	250C20B 	03013	GL 					POWER SECTION	FAILED 	B			KUVR	A				UNSCHED LANDING 				F	R		FLT CONT AFFECTED 	PARTIAL RPM/PWR LOSS 		HO	HOVERING 	1			SO	19	164BH					46602	CAE821029			PILOT REPORTED ENGINE LOST POWER IN MODERATE LEVEL HOVER. AFTER HEARING 3 DULL THUMPS, THE NOSE YAWED AND ACFT BEGAN TO	 SETTLE. PERFORMED CONTROLLED LANDING INTO 20 FEET OF WATER. ACFT ROLLED INVERTED AND SANK. CAUSE CURRENTLY UNKNOWN. 	 NTSB IS INVESTIGATING AT THIS TIME.				1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995040700225	19950407	00225	WP 	1995	4	7	95ZZZX1621 	1	19950126	G	7922	53E19600	VALVE 			HUGHES	269 	269C 	4470504	WP 										THERMO BYPASS	NUT LOOSE 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	557DC	666 				S1630				INSPECTED VALVE PER LYCOMING SB 518 AND FOUND NUT TO BE LOOSE. NUT SWAGE DIMENSION IS .215 INCH. (ORDERED NEW VALVE.) 	 SB DATED 11-4-94. RECEIVED SB 1-24-95.					1	G	7	1 	3O				4H12 					 
1995040700546	19950407	00546	CE 	1995	4	7	95ZZZX1634 	1	19950222	G	2821	07560106	STRAINER 			CESSNA	172 	172L 	2072432	CE 										FUEL SYSTEM	PLUNGER FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	7721G	2064 				17259421				PRIOR TO A FLIGHT, PILOT ATTEMPTED TO DRAIN FUEL STRAINER. IT WOULD NOT DRAIN. UPON DISASSEMBLY, FOUND RUBBER TIP OF P	LUNGER HAD DISBONDED FROM ASSY AND WAS PREVENTING FUEL FROM DRAINING.					1	H	7	1 	3O			NT	3A12 					 
1995040700547	19950407	00547	CE 	1995	4	7	95ZZZX1635 	1	19950314	G	3210	AN17520	BOLT 			CESSNA	402 	402C 	207590R	CE 										LT MLG SCISSORS	FAILED 	D				K				NONE 				O			OTHER 			LD	LANDING 	1			NE	01	403BK					402C0330				THE LEFT GEAR SCISSOR BOLT CAME OUT ON LANDING. THE LEFT WHEEL TURNED SIDEWAYS. REPLACED WHEEL, BOLT, NUT. INSPECTED 	STRUT AND WHEELWELLS AND ACTUATORS. SUBMITTER STATED A PERIODIC CHANGE OF SCISSOR BOLTS WILL BE IMPLEMENTED. BOLT PN A	N175-20. NUT PN AN310-5.				1	L	7	2 	3O				A7CE 					 
1995040700548	19950407	00548	SO 	1995	4	7	95ZZZX1636 	1	19950304	G	2750	62701101	CONTROL CABLE 			PIPER 	PA28 	PA28161 	7102803	SO 										FLAP	FRAYED 	B		A	DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	162ER	7658 				2841152				DURING PHASE INSPECTION, FLAP CABLE ASSY FOUND FRAYED IN AREA OF MAIN SPAR CENTER SECTION IN CABIN. SUSPECT FRAYING CAU	SED BY CABLE BEING TOO SOFT, AND BY FAIR LEAD PN62768-00, PN 62769-00 (2 PARTS MAKE ONE FAIR LEAD) CONTACTING FLAP CABLE	 LONG TERM FLAPS UP. NOTE: FAIR LEAD LOCATED AFT LOWER POSITION OF MAIN SPAR BOX CARRY-THROUGH. AS FLAPS ARE EXTENDED	, POINT OF WEAR (FRAY) MOVES FORWARD INTO CENTER SECTION BOX (SPAR CARRY-THROUGH) AND IS VERY DIFFICULT TO VISUALLY INSP	ECT. PLEASE NOTE IF THIS CABLE FAILS, AN UNEXPECTED, UNCOMMANDED, RAPID RETRACTION OF WING FLAPS WOULD OCCUR.		1	L	7	1 	3O			 	2A13 					 
1995040700549	19950407	00549	SO 	1995	4	7	95ZZZX1637 	1	19950304	G	2710	62701122	CONTROL CABLE 			PIPER 	PA28 	PA28161 	7102803	SO 										AIL BOTH WINGS	FRAYED 	B		A	DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	162ER	7658 				2841152				DURING PHASE INSPECTION, PRIMARY AILERON CABLE IN EACH WING WAS FOUND FRAYED AT PULLEY. PULLEY LOCATION IN EACH WING IS	 LOCATED JUST INBOARD OF MLG, AND CAN EASILY BE SEEN THROUGH EXISTING INSPECTION HOLE. BOTH CABLES HAD TO BE REPLACED. 	 IT APPEARS CABLE IS TOO SOFT AND IS BEING WORN BY PULLEY AT THE AILERONS' NEUTRAL POSITION. PLEASE NOTE THAT A FLEET O	F 17 PA28-161'S ARE MAINTAINED BY THIS REPAIR STATION, AND THAT AT APPROX 7,000 HOURS, ENTIRE FLEET IS ENCOUNTERING THIS	 PROBLEM. SIMILAR PROBLEMS SHOW UP ON STABILATOR AND FLAP CABLES, SOME SEVERE.		1	L	7	1 	3O			 	2A13 					 
1995040700550	19950407	00550	SO 	1995	4	7	95ZZZX1638 	1	19950321	G	2410	9907200	PULLEY 			PIPER 	PA32 	PA32RT300 	7103215	SO 										ALTERNATOR IDLER	BEARING SEIZED 	B			CSNR	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			CE	01	600CJ					32R7885050				FOUND IDLER PULLEY BEARING FOR ALTERNATOR BELT USED ON AIR CONDITIONED PA32RT ONLY. BEARING SEIZED AND CAUSED ALTERNATO	R BELT TO BREAK IN-FLIGHT. FLIGHT WAS VFR AT THIS TIME, BUT IS COMMONLY IFR FOR THIS AIRCRAFT.					1	L	7	1 	3O				A3SO 					 
1995040700552	19950407	00552	CE 	1995	4	7	95ZZZX1640 	1	19950317	G	2752		JACKSCREW 			CESSNA	310 	T310R 	2074246	CE 										RT FLAP SYSTEM	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	97216	1800 				310R0930				DURING AN ANNUAL INSPECTION, FOUND AN ALUMINUM SHEAR RIVET HAD BEEN REPLACED WITH A STEEL CLEVIS PIN. WHEN THE PROPER S	HEAR RIVET WAS INSTALLED, IT SHEARED. FURTHER INVESTIGATION FOUND RT JACKSCREW HAD WORN AND BALLBEARINGS WERE JAMMING T	HE SCREW CAUSING THE RIVET TO SHEAR AS IT WAS DESIGNED TO. OVERHAUL OF THE JACKSCREW AND INSTALLATION OF THE CORRECT PA	RTS FIXED ALL PROBLEMS.			1	L	7	2 	3O				3A10 					 
1995040700553	19950407	00553	CE 	1995	4	7	95ZZZX1641 	1	19950316	G	3221	05430131	FITTING 			CESSNA	172 	172P 	2072436	CE 										NLG ATTACH	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	5336K	6300 				172740069				UPPER NOSE GEAR FITTING FOUND LOOSE. A SHIMMY PROBLEM WAS REPORTED WHEN THE MECHANIC WAS REMOVING THE NOSE GEAR FOR STE	ERING COLLAR SHIMMING. INVESTIGATION FOUND THE AIRCRAFT HAD A SHIMMY PROBLEM FOR SEVERAL HUNDRED HOURS AND WAS NOT REPO	RTED.				1	H	7	1 	3O			NT	3A12 					 
1995040700554	19950407	00554	EA 	1995	4	7	95ZZZX1642 	2	19950317	G	7314	LW15472	PUMP 			AMTR 	PITTS 	PITTSSPECS1C		GL 	LYC 	O320 	O320* 	41508	EA 					ENGINE FUEL	DIAPHRAGM FAIL 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			EA	07	4T	400 				01	A			INVESTIGATION OF IN-FLIGHT ENGINE SHUT DOWN REVEALED THE DIAPHRAGM IN THE FUEL PUMP HAD RUPTURED. ENGINE HAD APROX 400 	HOURS OF OPERATION OVER 16 YEARS. SUBMITTER RECOMMENDS A CALENDER LIFE BE PLACED ON THESE DIAPHRAGMS.					1	Q	7	1 	3O	3	O		EXPA1Q71	E274				 
1995040700555	19950407	00555	SO 	1995	4	7	95ZZZX1643 	1	19950304	G	3242	164120	DISK 	PARKERHANFIN		PIPER 	PA28 	PA28140 	7102802	SO 										RT MLG BRAKE	PITTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8792N	600 				2825633				DURING NORMAL ANNUAL INSPECTION, RT MAIN WHEEL BRAKE ASSEMBLY, DISK, AND BOTH MAIN WHEEL HALVES FOUND CORRODED AND PITTE	D. DISK REQUIRED REPLACEMENT. DISK HAD BEEN REPLACED 10 YEARS PRIOR. SUBMITTER SUGGESTS REMOVING WHEEL FAIRING AND IN	SPECTING ASSEMBLY PROPERLY AT ANNUAL INSPECTION.				1	L	7	1 	3O				2A13 					 
1995040700556	19950407	00556	SO 	1995	4	7	95ZZZX1644 	1	19950305	G	3243	6140	CYLINDER 	PARKERHANFIN		PIPER 	PA28 	PA28140 	7102802	SO 										BRAKE ASSY	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8792N	3100 			3055	2825633				AT NORMAL ANNUAL INSPECTION, PART WAS REMOVED TO BE CLEANED AND INSPECTED. FOUND TO BE INITIALLY ONLY DIRTY AND CORRODE	D, HOWEVER, CLOSER INSPECTION REVEALED ANCHOR BOLT LUGS TO BE CRACKED. SUBMITTER SUGGESTS REMOVE, CLEAN, INSPECT, AND S	ERVICE AT REGULAR INTERVALS. WHEEL FAIRING MUST BE REMOVED TO PROPERLY INSPECT THIS AREA/PART.				1	L	7	1 	3O				2A13 					 
1995040700557	19950407	00557		1995	4	7	95ZZZX1645 	1	19950306	G	7830	23220258511	INNER ARM 	LEAR 	23420000 															THRUST REV	MISMANUFACTURED 	B			IY2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15										ARMS ARE MANUFACTURED BY LEARJET UNDER PMA. BIZJET RECEIVED AND PUT IN STOCK, 1 EACH DASH 511 ARM AND 6 EACH DASH 512 A	RMS. ONE EACH DASH 511 ARM AND 2 EACH DASH 512 ARMS WERE INSTALLED ON A CUSTOMER'S AIRCRAFT. BIZJETS PURCHASING AGENT 	NOTICIED BY LEAR SALES REP THAT THE ARMS WERE SHIPPED BEFORE THEY WERE HEAT-TREATED & NEEDED TO BE SHIPPED BACK TO LEAR.	 CUSTOMER WITH ARMS ON T/R HAS BEEN NOFIFIED. ARMS ARE IN HIGH DEMAND AND THE AMOUNT OF SUPPLIERS IS LIMITED, SO A HIG	H QUANTITY COULD HAVE BEEN SHIPPED IN THIS CONDITION.															 
1995040700558	19950407	00558		1995	4	7	95ZZZX1646 	1	19950306	G	7830	23220258512	INNER ARM 	LEAR 	23420000 															THRUST REV	MISMANUFACTURED 	B			IY2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15										ARMS ARE MANUFACTURED BY LEARJET UNDER PMA. BIZJET RECEIVED AND PUT IN STOCK, 1 EACH DASH 511 ARM AND 6 EACH DASH 512 A	RMS. ONE EACH DASH 511 ARM AND 2 EACH DASH 512 ARMS WERE INSTALLED ON A CUSTOMER'S AIRCRAFT. BIZJETS PURCHASING AGENT 	NOTICIED BY LEAR SALES REP THAT THE ARMS WERE SHIPPED BEFORE THEY WERE HEAT-TREATED & NEEDED TO BE SHIPPED BACK TO LEAR.	 CUSTOMER WITH ARMS ON T/R HAS BEEN NOFIFIED. ARMS ARE IN HIGH DEMAND AND THE AMOUNT OF SUPPLIERS IS LIMITED, SO A HIG	H QUANTITY COULD HAVE BEEN SHIPPED IN THIS CONDITION.															 
1995040700561	19950407	00561	CE 	1995	4	7	95ZZZX1650 	1	19950201	G	7603		CONTROL CABLE 			CESSNA	210 	P210N 	2073454	CE 										VERNIER THROTTLE	BROKEN 	G	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	6489W					P21000875				DESCENT RATE CONTROL (DRC) DEFECTIVE DUE TO VERNIER CONTROL GETS TWISTED WHEN THE CONTROL FOR WING SPOILERS IS TURNED. T	HIS CAUSES CABLE TO VERNIER CONTROL TO TWIST AND BREAK. PRECISE FLIGHT INC., STC SA1456NM.					1	H	7	1 	3O			 	3A21 					 
1995040700562	19950407	00562		1995	4	7	95ZZZX1651 	1	19950202	G	2432	503284	CELL 	MARATHON 	7883480011J 															BATTERY CAN	WRONG PART 	B		A	RD4D	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					316					INBOUND INSPECTION REVEALED THE FOLLOWING ON 2-2-95. CELLS STAMPED 'FURUKAWA' FOUND INSTALLED IN A MARATHON MANUFACTURE	D CAN. THE CIRCUIT BREAKER, NORMALLY FOUND IN FRONT OF THE CAN, HAS BEEN INSTALLED IN THE AFT CAVITY OF THE CAN, WITH S	CREWS AND A METAL BRACKET. THE DATA PLATE ON THE OUTSIDE OF THE BATTERY (FRONT) READS: NICKEL CADMIUM BATTERY, PN 7883	480-011J, 24 VOLTS, 6.0 AH AT 2 HR RATE, DATE OF REBUILT 754.30, SN 316, MODIFIED BY JAPAN AIRLINES. SIDE MARKINGS ARE:	 JAL 316 B-419-96200. BATTERY RETURNED TO SOUTHERN AIR TRANSPORT DUE TO LACK OF TECHNICAL DATA.															 
1995040700563	19950407	00563		1995	4	7	95ZZZX1652 	1	19950220	G	2432	503284	CELL 	MARATHON 	7883480011J 															BATTERY CAN	WRONG PART 	B		A	RD4D	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					301					INBOUND INSPECTION REVEALED THE FOLLOWING ON 2-20-95. CELLS STAMPED 'FURUKAWA', FOUND INSTALLED IN A MARATHON MANUFACTU	RED CAN. THE CIRCUIT BREAKER, NORMALLY FOUND IN FRONT OF THE CAN, HAS BEEN INSTALLED IN THE AFT CAVITY OF THE CAN, WITH	 SCREWS AND A METAL BRACKET. THE DATA PLATE ON THE OUTSIDE OF THE BATTERY (FRONT) READS: NICKEL CADMIUM BATTERY, PN 78	83480-011J, 24 VOLTS, 6.0 AH AT 2 HR RATE, DATE OF REBUILT 742.22, SN 301, MODIFIED BY JAPAN AIRLINES. SIDE OF CAN MAR	KINGS ARE: JAL 301 B-419-96200. BATTERY RETURNED TO SOUTHERN AIR TRANSPORT IN MIAMI, FL, DUE TO LACK OF TECHNICAL DATA	.														 
1995040700564	19950407	00564		1995	4	7	95ZZZX1653 	1	19950220	G	2432	503284	CELL 	MARATHON 	7883480011J 															BATTERY CAN	WRONG PART 	B		A	RD4D	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					221					INBOUND INSPECTION REVEALED THE FOLLOWING ON 2-20-95. CELLS STAMPED 'FURUKAWA', FOUND INSTALLED IN A MARATHON MANUFACTU	RED CAN. THE CIRCUIT BREAKER, NORMALLY FOUND IN FRONT OF THE CAN, HAS BEEN INSTALLED IN THE AFT CAVITY OF THE CAN, WITH	 SCREWS AND A METAL BRACKET. THE DATA PLATE ON THE OUTSIDE OF THE BATTERY (FRONT) READS: NICKEL CADMIUM BATTERY, PN 78	83480-011J, 24 VOLTS, 6.0 AH AT 2 HR RATE, DATE OF REBUILT 73.11.10, SN 221, MODIFIED BY JAPAN AIRLINES. SIDE OF CAN M	ARKINGS: JAL 221 B-417-96200. BATTERY RETURNED TO SOUTHERN AIR TRANSPORT IN MIAMI, FL, DUE TO LACK OF TECHNICAL DATA.															 
1995040700565	19950407	00565		1995	4	7	95ZZZX1654 	1	19950301	G	2432	10H120B	CELL 	MARATHON 	CA101N 															BATTERY	WRONG PART 	B		A	RD4D	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					9346051R					INBOUND INSPECTION OF BATTERY, PN CA101N, SN 9346051R, REVEALED SEVERAL DEFECTS. THE IMPROPER CELL TYPE IS INSTALLED FO	R THE CA101N BATTERY APPLICATION CELL, PN 10H 120S, IS THE PROPER TYPE CELL, BUT CELL, PN 10H120B'S, ARE CURRENTLY INSTA	LLED. FURTHER INSPECTION AND DISASSEMBLY REVEALED LETTERS 'NCAB' STAMPED ON TOP OF 18 (OUT OF 19) CELLS, WHERE THE MARA	THON LOGO CAN NORMALLY BE FOUND. THESE CELLS ARE CLEARLY REBUILT.																 
1995040700611	19950407	00611	WP 	1995	4	7	95ZZZX1680 	1	19950314	G	2720	4649526	STATOR ASSY 		5765017501 	DOUG 	DC9 	DC9* 		WP 										RUDDER DAMPER	MISINSTALLED 	B		A	B5SR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	23					W023805					UNIT DISASSEMBLED FOR REPLACEMENT OF SEAL AND INSPECT FOR BURRS. UPON INSPECTION, STATOR ASSY HAD ONE-HALF INSTALLED WI	TH ETCHED SIDE AWAY FROM PLATE. THIS IS IN DIRECT VIOLATION OF PAGE 6, STEP 4 CAUTION NOTE OF DOUGLAS OVERHAUL MANUAL 2	7-20-5.				2	L	7	2 	4F				A6WE 					 
1995040700613	19950407	00613	NE 	1995	4	7	95ZZZX1682 	2	19950303	G	7210	7895922	BOWED TAB WASHER		7758001 	SAAB 	SF340 	SF340A 	7850100	EU 	GE 	CT7TP 	CT75A2 	30030	NE 					GC 49 GEARCASE	BROKEN 	B			SI3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03		16437			UDAC0185		GEE367286			GEARBOX WAS RETURNED FOR 'METAL CONTAMINATION'. AFTER TEAR DOWN OF GEARBOX, NOTICED TABS WERE BROKEN OFF TAB WASHER (IT	EM 20A OF SEI 663) AND RETAINING NUT (ITEM 25 OF SEI 663) WAS BACKED OFF THREAD ON PROP SHAFT (ITEM 80 OF SEI 663). NOT	E: NO OTHER DAMAGE SEEN. REF: CMM 72-11-02.				2	L	7	2 	4T	4	T	RT	A52EU 	E8NE6				 
1995040700614	19950407	00614	EA 	1995	4	7	95ZZZX1683 	2	19950323	G	7230		COMPRESSOR 			BEECH 	90 	B90 	1152912	CE 	PWA 	PT6 	PT6A20 	52043	EA 					FIRST STAGE	FOD DAMAGE 	G				A				UNSCHED LANDING 				A	J		FLAME/FIRE 	WARNING INDICATION 		CR	CRUISE 	1			GL	05	939K	5092 	1603 			LJ349	PCE21635			MGY - EN ROUTE, RT ENGINE FUEL FLOW FLUCTUATED AND FLAMES WERE OBSERVED OUT OF EXHAUST. FLIGHT DIVERTED TO DAY WHERE IN	SPECTION SHOWED FOD TO FIRST STAGE COMPRESSOR. ENGINE REMOVED FOR INSPECTION AND REPAIR FOLLOW-UP.					1	L	7	2 	3T	3	T		3A20 	E4EA				 
1995040700616	19950407	00616	NM 	1995	4	7	95ZZZX1685 	1	19950216	G	5280	65267632	HINGE ASSY 			BOEING	727 	72717 	1384008	NM 										RT MLG DOOR	FAILED 	B		A	AMCR	O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			GL	09	529AC					20327				TIST - DURING CLIMB-OUT, AIRCRAFT HAD A VIBRATION. ALL SYSTEMS CHECKED OKAY. ABOUT 2.50 HOURS INTO THE FLIGHT, CREW HE	ARD A DULL BANG, AND VIBRATION WAS GONE. AFTER LANDING IN GRR, FOUND RIGHT GEAR DOOR WAS MISSING. FORWARD HINGE POINT,	 BOEING PN 65-26763-2, CRACKED ALLOWING DOOR TO DROP DOWN INTO THE AIRFLOW. THE DOOR FINALLY TORE THE REMAINING ATTACH 	POINTS LOOSE AND ALLOWED THE DOOR TO DEPART AIRCRAFT. SUBMITTER RECOMMENDS INSPECTION REQUIREMENTS BE UPDATED FOR N.D.T	. TO THE HINGE BRACKET AREA EVERY 24 MONTHS OR 1,400 HOURS AT THE 2-C INSPECTION.		2	L	7	3 	4F				A3WE 					 
1995040700617	19950407	00617	WP 	1995	4	7	95ZZZX1686 	1	19950330	G	2820	369A8113	HOSE 			HUGHES	369 	369E 	4470707	WP 										START PUMP	LOOSE 	B			XAZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	471SD	5225 				0179E				DURING COMPLIANCE OF EN AND CHECKING INTERIOR OF FUEL CELL FOR CLEANLINESS, THE FUEL LINE FROM THE START PUMP TO THE FUE	L SHUT OFF VALVE WAS FOUND LOOSE AT THE PUMP. THE UNION WAS LOOSE ALSO. AN ARTICLE IN THE FAA AC 43-16, ALERT NR 201, 	PAGE 12, PROPAGATED THIS INSPECTION. NO ABNORMAL VIBRATIONS OR DISCREPANT TOT TEMPS WERE REPORTED BY THE PILOT.				1	G	7	1 	3U				H3WE 					 
1995040700619	19950407	00619		1995	4	7	95ZZZX1688 	2	19950126	G	7414		BEARING 	SLICK 	4273 	CHRIS 	HUSKY 	A1 	221020X	NM 										MAGNETO	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	2941W	535 			88010007	1040				ROTATING MAGNET FOUND GRINDING AGAINST STATIONARY MAGNET DUE TO MAIN BALLBEARING COMING LOOSE. MAG TOTAL TIME 535.2 HRS	. DESIGN OF MAG PROMOTES NON-INSPECTION AT REQUIRED 500-HOUR INTERVALS. SUBMITTER SUGGESTS THE INSPECTIONS SHOULD BE M	ANDATORY AS THESE MAGNETOS ARE WELL KNOWN FOR PROBLEMS.				1	H	7	1 	3O			NC	A22NM 					 
1995040700725	19950407	00725	SW 	1995	4	7	95ZZZX1689 	1	19950317	G	6300	206040106001	SPRING 		20604001510 	BELL 	206 	206A 	1181508	SW 										FWD D/S COUPLING	BROKEN 	B		A	RT2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	90SP				A1210	583				DURING 100-HOUR INSPECTION, MECHANIC FOUND GREASE LEAKAGE FROM THE FORWARD COUPLING OF MAIN DRIVE SHAFT. AT DISASSEMBLY	 FOR REPAIR, THE COUPLING SPRING WAS FOUND IN 16 PIECES AND HAD WORN THROUGH THE END CAP (CAUSING GREASE LEAKAGE). THE 	BROKEN SPRING HAD WORN INTO THE INNER COUPLING AND ATTACHING HARDWARE RENDERING THESE PARTS UNSERVICEABLE. THERE WAS NO	 OVERTEMP INDICATION AND NO UNUSUAL REPORTS FROM THE PILOT. THIS SPRING HAS NO LIFE LIMIT AND MAY HAVE FAILED DUE TO FA	TIGUE. THE DRIVE SHAFT IS INSPECTED AT 12 MO/600-HOUR INTERVALS. THE SUBJECT SPRING IS UTILIZED ON A VARIETY OF BELL H	ELICOPTER 206 AIRCRAFT.	1	G	7	1 	3U				H2SW 					 
1995040700727	19950407	00727		1995	4	7	95ZZZX1691 	1	19950228	G	2434	6468481	BRUSH 	TELEDYNECRIT	646843 															ALTERNATOR	WORN 	B			KC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03		145 			A0494210R					ON ORIGINAL FACTORY UNIT, FOUND BRUSH HOLDER NOT CORRECTLY ALIGNED WITH SLIP RINGS CAUSING BRUSH TO RIDE OFF OF EDGE ONT	O PHENOLIC INSULATOR. THIS CAUSES 'ALT. OUT' CONDITION. SUBMITTER SUGGESTS FACTORY CHECK SLIP RING POSITION ON ROTOR S	HAFT TO ASSURE CORRECT ALIGNMENT. (HAVE SEEN THIS SAME PROBLEM MANY TIMES).																	 
1995040700728	19950407	00728	SO 	1995	4	7	95ZZZX1692 	1	19950315	G	5700		LIFT STRUT 			PIPER 	PA18 	PA18150 	7101828	SO 										LT REAR	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	4362Z					188681				LEFT REAR LIFT STRUT HAS SEVERE CORROSION AT LOWER 2 INCHES OF STRUT. STRUT DENSITY 4.9 HD. COMPARITOR SHIM DENSITY 4.	75 HD.					1	H	7	1 	3O				1A2 					 
1995040700729	19950407	00729	SO 	1995	4	7	95ZZZX1693 	1	19950315	G	5700		LIFT STRUT 			PIPER 	PA18 	PA18150 	7101828	SO 										LT FRONT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	4362Z					188681				LEFT FRONT LIFT STRUT HAS SEVERE CORROSION AT LOWER 6 INCHES OF STRUT. STRUT DENSITY 5.04 HD. COMPARITOR SHIM DENSITY 	4.87 HD. AD NOTE 93-10-06.					1	H	7	1 	3O				1A2 					 
1995040700730	19950407	00730	SO 	1995	4	7	95ZZZX1694 	1	19950220	G	2140	G474942	IGNITER 		940DA 	PIPER 	PA23 	PA23250 	7102308	SO 										HEATER	SHORTED 	B			KC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03		1 								IGNITER WAS INSTALLED NEW AND FAILED AFTER 5 MINUTES OF OPERATION. SHORTED TO GROUND DRAWING EXCESSIVE CURRENT. SUPPLI	ER INDICATED THAT SOUTHWIND HAS HAD MORE PROBLEMS THAN USUAL WITH THIS IGNITER.					1	L	7	2 	3O				1A10 					 
1995040700731	19950407	00731	EA 	1995	4	7	95ZZZX1695 	2	19950322	G	8520	72877	TAPPET 			CESSNA	172 	172N 	2072434	CE 	LYC 	O360 	O360A4M 	41514	EA 					VALVE	FAILED 	D				A	E			UNSCHED LANDING 	ENGINE SHUTDOWN 			E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			WP	07	3216E	2003 				17271471	L3173036A			AFTER TAKEOFF, TURN OUT OF TRAFFIC, UNDER FULL POWER, RPM ROLLED BACK TO 1900. SEVERE VIBRATION. CONTINUED TURN TO DOW	NWIND; BASE FOR EMERGENCY LANDING. ENGINE SHUT DOWN.					1	H	7	1 	3O	3	O	NT	3A12 	E286				 
1995040700732	19950407	00732	CE 	1995	4	7	95ZZZX1696 	1	19950118	G	3233	1693800601	ACTUATOR 	GERDES 		BEECH 	23 	C24R 	1151254	CE 										LT MLG	CAP LEAKING 	B	S	A	EHHR	O				OTHER 				K			FLUID LOSS 			NR	NOT REPORTED 	1			EA	17	6021P	3307 				MC657				LANDING GEAR WOULD NOT RETRACT. FOUND HYDRAULIC RESERVOIR EMPTY OF FLUID. FURTHER INVESTIGATION FOUND FLUID COMING OUT	 OF LEFT LANDING GEAR ACCESS PANEL. FOUND LEFT HYD ACTUATOR LEAKING AT RADIUS OF CAP FLATS WHERE THE CAP CAN BE PUT INT	O A VISE AND TWISTED OFF. FOUND THIS SAME CONDITION IN A SERVICEABLE SPARE UNIT.				1	L	7	1 	3O				A1CE 					 
1995040700733	19950407	00733	SW 	1995	4	7	95ZZZX1697 	1	19950323	G	7922	75944	VALVE 			MOONEY	M20 	M20F 	5870214	SW 										THERMO BYPASS	CRIMP NUT LOOSE 	B			CR1D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	642DG	1789 			10965	670158				WHILE COMPLYING WITH LYCOMING SB518A INSPECTION OF THE THERMOSTATIC BYPASS VALVE, THE NUT WAS FOUND LOOSE. A NEW VALVE,	 PN 53E19600, SN 61088, WAS OBTAINED AS A REPLACEMENT. WHEN THE NEW VALVE WAS INSPECTED, NUT WAS ALSO FOUND LOOSE. THIS	 VALVE, ACCORDING TO THE SB, DOES NOT APPLY TO THE INITIAL INSPECTION REQUIREMENTS. ANOTHER VALVE WAS ORDERED AND IT CH	ECKED OKAY. RECOMMEND A SMALL SPOT WELD INSTEAD OF A CRIMP ON THE NUT TO SECURE THE NUT TO THE SHAFT.			1	L	7	1 	3O				2A3 					 
1995040700734	19950407	00734	NE 	1995	4	7	95ZZZX1698 	3	19950301	G	6111	AG1002	BLADE 			AYRES 	S2 	S2RNORMAL 	7630202	SO 						HAMSTD	12D	12D40 	NE 	NR 1 FILLET	CRACKED 	B			XX4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	984UA		468 		779460	21642		74900		PROPELLER WAS REMOVED FROM AIRCRAFT FOR VIBRATION. AFTER DISASSEMBLY, NR 1 BLADE WAS CRACKED IN HALF IN FILLET AREA, ON	LY BLADE BUSHING PREVENTED SEPARATION FROM THE HUB.					1	L	7	1 	3R			NC	A3SW 		5	C	P257	 
1995040700735	19950407	00735	CE 	1995	4	7	95ZZZX1699 	1	19950302	G	3230	12802091	PIN 			CESSNA	182 	TR182 	2072735	CE 										NLG ACTUATOR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	2268S	393 				R18201317				NOSE GEAR DOWNLOCK PIN, LT SIDE, CRACKED AT ROLL PIN GROOVE ALLOWING PIN TO VIBRATE TOWARD NOSE GEAR ACTUATOR SHAFT STOP	PING NOSE GEAR FROM LOCKING DOWN.					1	H	7	1 	3O				3A13 					 
1995040700736	19950407	00736	CE 	1995	4	7	95ZZZX1700 	1	19950306	G	3230	12434262	LINK ASSY 			CESSNA	210 	210L 	2073448	CE 										NLG SCISSOR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	777BK	5850 				21060560				TOP SCISSOR LINK FOUND CRACKED ON BOTTOM SIDE. SUSPECT REPEATED NOSE STRUT EXTENSIONS EXERTING PULL-DOWN PRESSURE ON UP	PER LINK, WHICH INCORPORATES A STOP BLOCK, PREVENTING OVER EXTENSION.					1	H	7	1 	3O				3A21 					 
1995040700737	19950407	00737	CE 	1995	4	7	95ZZZX1701 	1	19950306	G	3230	12434262	LINK ASSY 			CESSNA	210 	210L 	2073448	CE 										NLG SCISSOR	BENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5171V	4800 				21060846				TOP SCISSOR LINK FOUND BOWED DOWNWARD. SUSPECT CAUSE AS REPEATED NOSE STRUT EXTENSIONS EXERTING PULL-DOWN PRESSURE ON U	PPER LINK, WHICH HAS A STOP BLOCK PN 1243038-1, ATTACHED TO IT, PREVENTING OVER EXTENSION.					1	H	7	1 	3O				3A21 					 
1995040700738	19950407	00738	EA 	1995	4	7	95ZZZX1702 	2	19950310	G	8530	SL74230	GUIDE 		LW12419 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					LOWER PORTION	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	140ER					1529				DURING CYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION.						1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995040700739	19950407	00739	EA 	1995	4	7	95ZZZX1703 	2	19950310	G	8530	74230	GUIDE 		LW12416 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					LOWER PORTION	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	140ER	1757 				1529				DURING CYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION.						1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995040700740	19950407	00740	EA 	1995	4	7	95ZZZX1704 	2	19950310	G	8530	74230	GUIDE 		LW12419 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					LOWER PORTION	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	117ER	1763 				1509				DURING CYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION.						1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995040700741	19950407	00741	EA 	1995	4	7	95ZZZX1705 	2	19950308	G	8530	74230	GUIDE 		LW12416 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					LOWER PORTION	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	137ER	1665 				1527				DURING CYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION.						1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995040700742	19950407	00742	EA 	1995	4	7	95ZZZX1706 	2	19950310	G	8530	74230	GUIDE 		LW12416 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					LOWER PART	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	130ER	1568 				1511				DURING CYLINDER OVERHAUL, EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION.						1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995040700743	19950407	00743	EA 	1995	4	7	95ZZZX1707 	2	19950310	G	8530	SL74230	GUIDE 		LW12419 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					LOWER PORTION	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	144ER		228 			1339				DURING CYLINDER PRE-OVERHAUL INSPECTION, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION.						1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995040700744	19950407	00744	EA 	1995	4	7	95ZZZX1708 	2	19950310	G	8530		GUIDE 		LW12416 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					LOWER PORTION	PART MISSING 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	130ER	1568 				1511				DURING CYLINDER OVERHAUL, FOUND LOWER PORTION OF THE EXHAUST GUIDE WAS MISSING APPROXIMATELY ONE-HALF OF ITS MATERIAL. T	HE UPPER PORTION OF THE GUIDE THAT PROJECTS IN THE ROCKER BOX AREA WAS FOUND BROKEN OFF LEVEL WITH THE CYLINDER HEAD.					1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995040700745	19950407	00745	EA 	1995	4	7	95ZZZX1709 	2	19950308	G	8530	S74230	GUIDE 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					LOWER PORTION	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	167ER		398 			2841183				DURING CLYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED ON THE LOWER PORTION.						1	L	7	1 	3O	3	O		2A13 	E274				 
1995040700746	19950407	00746	EA 	1995	4	7	95ZZZX1710 	2	19950308	G	7414	10400006	IDENT PLATE 		D4LN3000 	MOONEY	M20 	M20J 	5870219	SW 	LYC 	O360 	IO360A3B6 	41514	EA 					MAGNETO	DAMAGED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	194ER		1500 		J049108G	243255				ALUMINUM FOIL IDENTIFICATION PLATE FOUND TORN WHEN MAGNETO WAS RECEIVED FOR REPAIR. CORRECTIVE ACTION WAS TO INSTALL A 	NEW, PN 10-400006, IDENTIFICATION PLATE. IT IS EXPECTED THE NEW IDENTIFICATION PLATE WILL EXPERIENCE THE SAME CONDITION	 THAT LED TO DAMAGE OF THE PREVIOUSLY INSTALLED IDENTIFICATION PLATE. RECOMMEND A METAL DATA PLATE BE PERMANENTLY ATTAC	HED TO MAGNETO.			1	L	7	1 	3O	3	O		2A3 	1E10				 
1995040700747	19950407	00747	GL 	1995	4	7	95ZZZX1711 	2	19950313	G	7261	23006661	BODY 								ALLSN 	501D 	501D13 	03004	GL 					PUMP GEAR POCKET	DEBONDED 	B			WS2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01										OIL PUMP REPAIR MATERIAL DEBONDING. APPROXIMATELY .50 SQUARE INCH OF MATERIAL HAS LIFTED AWAY FROM GEAR POCKET WALL. S	URROUNDING MATERIAL SHOWS EVIDENCE OF GENERAL DEBONDING. BODY IDENTIFIED WITH 'IAR 7148'.										4	T			E282				 
1995040700748	19950407	00748	NE 	1995	4	7	95ZZZX1712 	2	19950310	G	7314	2113045	HOUSING 								PWA 	JT9 	JT9* 	52054	NE 					PUMP GEAR POCKET	DEBONDED 	B			WS2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01										FUEL PUMP DEBONDING OF GEAR POCKET REPAIR MATERIAL APPROXIMATELY 50 PERCENT OF REPAIR MATERIAL IS MISSING FROM GEAR POCK	ET WALLS. REMAINDER IS FLAKING OFF. HOUSING IDENTIFIED WITH 'IAR 9931D'.										4	F			E20EA				 
1995040700749	19950407	00749		1995	4	7	95ZZZX1713 	1	19950310	G	4990	379617	BODY 																	APU OIL PUMP	DEBONDED 	B			WS2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01										APU OIL PUMP, 100 PERCENT DEBONDING OF GEAR POCKET REPAIR MATERIAL. APPROXIMATELY 30 PERCENT OF REPAIR MATERIAL IS MISS	ING FROM GEAR POCKET WALLS. REMAINDER REMOVED FROM GEAR POCKETS IN TWO PIECES. APU GTCP85 HOUSING (BODY) IDENTIFIED WI	TH 'GASD 0616 09347 6945 I'.																	 
1995040700750	19950407	00750		1995	4	7	95ZZZX1714 	1	19950310	G	4990	372839	COVER 																	APU OIL PUMP	DEBONDED 	B			WS2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01										APU OIL PUMP, 100 PERCENT DEBONDING OF GEAR POCKET REPAIR MATERIAL. APPROXIMATELY 20 PERCENT OF REPAIR MATERIAL IS MISS	ING FROM GEAR POCKET WALLS. REMAINDER REMOVED FROM GEAR POCKETS IN 2 PIECES. APU GTCP85 COVER IDENTIFIED WITH 'GASD 06	16 09347 6945I'.																	 
1995040700751	19950407	00751	EU 	1995	4	7	95ZZZX1715 	1	19950223	G	3230	TB1041035000	TORQUE LINK 			SOCATA	TB9 	TB9 	8680694	EU 										LT MLG BOLT	SPLIT 	B	S	A	DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	244ER	2464 				1371				UPON 500-HOUR TORQUE LINK INSPECTION WHEREAS TORQUE LINKS ARE TAKEN APART, CLEANED, INSPECTED AND LUBED, THEN ARE REINST	ALLED. MECHANIC FOUND LMG LWR TORQUE LINK AT HEAD OF BOLT CRACKED AND SPLIT APART. PART TT 2463.7. RMG FOUND TO BE OK	AY. NG TORQUE LINKS BOTTOM BOLT HAD TO BE DRIVEN OUT WITH BRASS DRIFT AND HAMMER. ALSO, FOUND SAME CONDITION AT THE SA	ME LOCATION WHERE BOLT GOES THROUGH BOTTOM TORQUE LINK. THIS WAS FOUND CRACKED, NOT YET SPLIT APART. RECOMMEND FORGE N	OT CASE PART.		1	L	7	1 	3O			NT	AS1EU 					 
1995040700752	19950407	00752	EU 	1995	4	7	95ZZZX1716 	1	19950223	G	3230	TB1041035000	TORQUE LINK 			SOCATA	TB9 	TB9 	8680694	EU 										NLG BOLT	CRACKED 	B			DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	244ER	2464 				1371				UPON 500-HOUR TORQUE LINK INSPECTION WHEREAS TORQUE LINKS ARE TAKEN APART, CLEANED, INSPECTED AND LUBED, THEN ARE REINST	ALLED. MECHANIC FOUND LMG LWR TORQUE LINK AT HEAD OF BOLT CRACKED AND SPLIT APART. PART TT 2463.7. RMG FOUND TO BE OK	AY. NG TORQUE LINKS BOTTOM BOLT HAD TO BE DRIVEN OUT WITH BRASS DRIFT AND HAMMER. ALSO, FOUND SAME CONDITION AT THE SA	ME LOCATION WHERE BOLT GOES THROUGH BOTTOM TORQUE LINK. THIS WAS FOUND CRACKED, NOT YET SPLIT APART. RECOMMEND FORGE N	OT CASE PART.		1	L	7	1 	3O			NT	AS1EU 					 
1995040700753	19950407	00753	SO 	1995	4	7	95ZZZX1717 	1	19950316	G	2910	159H1016517P8	LINE 		66WAY3002 	GULSTM	G159 	G159 	3952202	SO 										RT HYD PUMP	HOLE CHAFED 	B			BTVR	L	A	O		ABORTED APPROACH 	UNSCHED LANDING 	OTHER 		F	K		FLT CONT AFFECTED 	FLUID LOSS 		AP	APPROACH 	1			GL	23	659PC				NA1	196				AIRCRAFT WAS IN LEVEL FLIGHT ON APPROACH TO DESTINATION AIRPORT WHEN CREW NOTICED FLAPS WOULD NOT RESPOND TO SELECTED IN	PUTS. IT WAS THEN THAT THEY NOTICED HYDRAULIC PRESSURE FLUCTUATING AND DROPPING OFF. THE CREW DIVERTED TO AN ALTERNATE	 AIRFIELD, USED EMERGENCY FLAPS, AND EMERGENCY GEAR (BLOW DOWN). A NORMAL LANDING WAS MADE. ON SITE INSPECTION REVEALE	D THE RT MAIN HYDRAULIC PRESSURE LINE HAD CHAFED ON THE FIREWALL STRUCTURE CAUSING A HOLE IN THE LINE. BETTER ISOLATION	 AND SECURING OF THE NEW LINE SHOULD PREVENT ANOTHER FAILURE. OPER CONTROL NR BTVR31695.		2	L	7	2 	4T				1A17 					 
1995040700754	19950407	00754	NM 	1995	4	7	95ZZZX1718 	1	19950301	G	2410		BELT 			PIPER 	PA60 	PA60601P 	7106012	NM 										ALTERNATOR	LOOSE 	B			CGHR	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	03	6074E					61P070479633				PILOT REPORTS A LOW VOLTAGE INDICATOR WARNING CAME ON WHEN HE WAS IFR IN IMC CONDITIONS WITH A HEAVY ELECTRICAL LOAD. F	OUND BOTH ALTERNATOR BELTS WERE SLIPPING AT HIGH ENGINE RPM AND HIGH LOADS. TIGHTENED BOTH ALT BELTS. RECOMMEND ALTERN	ATOR BELTS BE SERVICED PER MM. NOTE: BOTH BELTS HAD APPROXIMATELY 150 HOURS IN SERVICE SINCE NEW.				1	M	7	2 	3O			RT	A17WE 					 
1995040700755	19950407	00755	CE 	1995	4	7	95ZZZX1719 	1	19950217	G	2741	S2800223	POTENTIOMETER 			CESSNA	500 	560CESSNA 	2076750	CE 										ELEV POSITION	SHAFT SHEARED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	502T	1133 				560153				ELEVATOR POSITION POTENTIOMETER FOR FDR FOUND SHEARED. THIS IS SECOND FAILURE OF THIS TYPE ON SECOND AIRCRAFT. CESSNA 	ENGINEERING FOUND BRACKET MISALIGNED. THEY READJUSTED TO PREVENT FUTURE FAILURE.					2	L	7	2 	4F			RT	A22CE 					 
1995040700756	19950407	00756	CE 	1995	4	7	95ZZZX1720 	1	19950309	G	2121	99123232	BLOWER ASSY 			CESSNA	500 	550 	2076604	CE 										AIR DIST J BOX	MOTOR FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	101AF	216 				5500732				PILOT REPORTED NO AIR FLOWING FROM OVERHEAD VENTS. WITH ENGINES RUNNING, LOW AIR FLOW THROUGH VENTS. TROUBLESHOT SYSTE	M, FOUND BLOWER MOTOR INOP. REPLACED MOTOR AND VENTS WORE NORMAL. CAUSE OF MOTOR FAILURE UNKNOWN. MOTOR PN ME38A-1.					1	L	7	2 	4F				A22CE 					 
1995040700757	19950407	00757	CE 	1995	4	7	95ZZZX1721 	1	19950309	G	2915	4614	VALVE 			CESSNA	500 	550 	2076604	CE 										HYD PANEL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	11	101AF	216 				5500732				NOTED HYD FLUID ON HYD PANEL. TROUBLESHOT SYSTEM, FOUND HYD PRESSURE RELIEF VALVE LEAKING AT AREA WHERE THE TWO HALVES 	OF THE VALVE CONNECT. THERE IS NO PROCEDURE IN THE MM TO RESEAL UNIT. HAD TO REPLACE UNIT WITH EXCHANGE PART.					1	L	7	2 	4F				A22CE 					 
1995041400385	19950414	00385	CE 	1995	4	14	95ZZZX1731 	1	19950301	G	2520		HARNESS 			BEECH 	200 	B200 	1152922	CE 										SEAT BELT	MISRIGGED 	D	S			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	11	44SR					BB853				UPON RE-FURBUSHING INTERIOR, THE SEAT BELT SHOULDER HARNESS WAS FOUND TO BE MADE WRONG. WHEN SEAT BELT WAS RELEASED, OC	CUPANT WAS STILL TRAPPED IN THE SEAT BY HARNESS THE WAY IT WAS MADE.					1	L	7	2 	4T				A24CE 					 
1995041400386	19950414	00386	CE 	1995	4	14	95ZZZX1732 	1	19950301	G	2740	12602382	ACTUATOR 			CESSNA	210 	T210N 	2073456	CE 										ELEVATOR TRIM	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	6986N	2061 				21063195				ELEVATOR TRIM HAD EXCESSIVE PLAY DUE TO WORN TRIM ACTUATOR, DUE TO HIGH REPLACEMENT COST, ACTUATORS ARE NOT BEING REPLAC	ED. CESSNA HAS NO REPAIRS ON THE ACTUATOR OTHER THAN REPLACEMENT. HAVE FOUND SEVERAL ACTUATORS WITH EXCESSIVE PLAY IN 	THE LAST 5 YEARS. AIRCRAFT TOTAL TIME 2061.4.				1	H	7	1 	3O				3A21 					 
1995041400387	19950414	00387	EA 	1995	4	14	95ZZZX1733 	2	19950303	G	7414	104001678	IMPULSE COUPLING	BENDIX 	S6LN1227 	PIPER 	PA25 	PA25260 	7102508	SO 	LYC 	O540 	O540G1A5 	41532	EA 					LT MAG	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	9785P	401 			0127691	257556096				MAG INSPECTION FOUND FLYWEIGHT TO AXLE CLEARANCE BEYOND LIMITS.						1	L	7	1 	3O	3	O		2A10 	E295				 
1995041400388	19950414	00388	SO 	1995	4	14	95ZZZX1734 	1	19950217	G	5741	6862101	SUPPORT 			PIPER 	PA32 	PA32R300 	7103213	SO 										REAR WING ATTACH	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	43797	4285 				32R7780526				WHILE PERFORMING PIPER SB 977, THE REAR WING ATTACH BRACKETS ON BOTH THE RIGHT AND LEFT WERE FOUND BADLY CORRODED. WHEN	 PART WAS REMOVED, MORE RUST WAS FOUND THAT WAS VERY DIFFICULT TO SEE UNTIL PART WAS REMOVED. SUBMITTER STRONGLY RECOMM	ENDS SB BE FOLLOWED AND IF ANY CORROSION OR RUST FOUND, THAT PART BE REPLACED OR VERY CLOSELY EXAMINED.				1	L	7	1 	3O				A3SO 					 
1995041400389	19950414	00389	SO 	1995	4	14	95ZZZX1735 	1	19950217	G	5741	6862100	SUPPORT 			PIPER 	PA32 	PA32R300 	7103213	SO 										REAR WING ATTACH	CORRODED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	43797	4285 				32R7780526				WHILE PERFORMING PIPER SB 977, THE REAR WING ATTACH BRACKETS ON BOTH THE RIGHT AND LEFT WERE FOUND BADLY CORRODED. WHEN	 PART WAS REMOVED, MORE RUST WAS FOUND THAT WAS VERY DIFFICULT TO SEE UNTIL PART WAS REMOVED. SUBMITTER STRONGLY RECOMM	ENDS SB BE FOLLOWED AND IF ANY CORROSION OR RUST FOUND, THAT PART BE REPLACED OR VERY CLOSELY EXAMINED.				1	L	7	1 	3O				A3SO 					 
1995041400390	19950414	00390	SO 	1995	4	14	95ZZZX1736 	2	19950213	G	8530	SA632932	PISTON 			CESSNA	182 	182C 	2072708	CE 	CONT 	O470 	O470L 	17026	SO 					NR 3 CYLINDER	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CE	07	856ST	868 				52465	80505964			PISTON WAS COMPLETELY DISINTEGRATING. ALL VALVES AND OTHER ENGINE PARTS COMPLETE AND ACCOUNTED FOR. SUSPECT CAUSE WAS 	METAL WAS TOO BRITTLE. PISTON PIN WAS IN ROD AND MOVING AROUND IN CYLINDER.					1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995041400391	19950414	00391	CE 	1995	4	14	95ZZZX1737 	1	19950330	G	2810	BTC54A	CELL 			CESSNA	182 	182P 	2075816	CE 										WING ROOT	DETERIORATED 	B			FC6R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	58684	1642 				18262234				FUEL BLADDERS DETERIORATED AND LEAKING, CAUSING SEVERE LEAKAGE, RT WING ROOT.						1	H	7	1 	3O			NT	TA13 					 
1995041400392	19950414	00392	EA 	1995	4	14	95ZZZX1738 	3	19950322	G	6111		BLADE 			PIPER 	PA28 	PA28140 	7102802	SO 						SNSNCH	74D	74DM 	EA 	CAMBER SURFACE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8792N	3100 				2825633		K28105		ANNUAL INSPECTION REVEALED DEEP PITS ON CAMBERED SURFACE OF PROPELLER. FACE OF PROP PROTECTED BY FLAT BLACK PAINT, CAMB	ER UNPROTECTED, UNPAINTED EXCEPT FOR WHITE TIPS. DEEP LINES OF CORROSION AT INTERSECTION OF PAINTED TIPS AND UNPAINTED 	CAMBER. ONE PROPELLER SHOP TURNED IT DOWN AS UNSERVICEABLE. OWNER TOOK IT TO OTHER PROP SHOP FOR REPAIR (AWAITING RESU	LTS). SUBMITTER RECOMMENDS WAX OR OIL PROP MONTHLY (MINIMUM) TO PROTECT FROM CORROSION.			1	L	7	1 	3O				2A13 		5	N	P88614	 
1995041400396	19950414	00396	EU 	1995	4	14	95ZZZX1742 	1	19950224	G	5320	MY20020103017B1	SUPPORT BRACKET 			AMD 	FALC20	FALCON200 	2730150	EU 										LT BAG COMPT	BENT 	B			JZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	843MG					491				WHILE PERFORMING A SCHEDULED INSPECTION, 2 REAR BAGGAGE COMPARTMENT FLOOR SUPPORT BRACKETS FOUND BENT. SUSPECT CAUSE IS	 DUE TO BALLAST BEING INSTALLED AT OUTFITTING & ITS CONSTANT REMOVAL/REPLACEMENT TO PERFORM SCHEDULED & UNSCHEDULED MAIN	TENANCE. SHOULD A FAILURE OF A BRACKET OCCUR, BALLAST AND/OR FLOORBOAD MAY DROP & REST ON ELEVATOR BELLCRANKS WHICH ARE	 DIRECTLY UNDERNEATH. PROBLEM COULD BE CONSIDERED AS A SAFETY OF FLIGHT HAZARD DUE TO CIRCUMSTANCES. SUBMITTER RECOMME	NDED ALL FALCON 200 ACFT BE INSPECTED FOR THIS CONDITION & A HEAVIER BRACKET BE INSTALLED ALONG WITH A CHECK FOR CLEARAN	CE BETWEEN BELLCRANKS & STRUCTURE ABOVE. REF: OPER CNTRL NR JZBR959576.	2	L	7	2 	4F			RT	A7EU 					 
1995041400397	19950414	00397	EU 	1995	4	14	95ZZZX1743 	1	19950224	G	5320	MY20251030016B1	SUPPORT BRACKET 			AMD 	FALC20	FALCON200 	2730150	EU 										REAR BAG COMPT	BENT 	B			JZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	843MG					491				WHILE PERFORMING A SCHEDULED INSPECTION, 2 REAR BAGGAGE COMPARTMENT FLOOR SUPPORT BRACKETS FOUND BENT. SUSPECT CAUSE IS	 DUE TO BALLAST BEING INSTALLED AT OUTFITTING & ITS CONSTANT REMOVAL/REPLACEMENT TO PERFORM SCHEDULED & UNSCHEDULED MAIN	TENANCE. SHOULD A FAILURE OF A BRACKET OCCUR, BALLAST AND/OR FLOORBOAD MAY DROP & REST ON ELEVATOR BELLCRANKS WHICH ARE	 DIRECTLY UNDERNEATH. PROBLEM COULD BE CONSIDERED AS A SAFETY OF FLIGHT HAZARD DUE TO CIRCUMSTANCES. SUBMITTER RECOMME	NDED ALL FALCON 200 ACFT BE INSPECTED FOR THIS CONDITION & A HEAVIER BRACKET BE INSTALLED ALONG WITH A CHECK FOR CLEARAN	CE BETWEEN BELLCRANKS & STRUCTURE ABOVE. REF: OPER CNTRL NR JZBR959576.	2	L	7	2 	4F			RT	A7EU 					 
1995041400398	19950414	00398	EU 	1995	4	14	95ZZZX1744 	1	19950216	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B		A	XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		309 			1249					THIS UNIT'S BRUSHES WERE WORN OUT IN 309 FLIGHT HOURS. FAA INSPECTOR WITNESSED BRUSH INSPECTION. RECOMMEND REDESIGNING	 DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995041400399	19950414	00399	CE 	1995	4	14	95ZZZX1745 	1	19950316	G	2910		LINE 			LEAR 	35 	31A 	5170531	CE 										GEAR RETRACT	B-NUT LOOSE 	B			BHKR	O				OTHER 				J	K		WARNING INDICATION 	FLUID LOSS 		CR	CRUISE 	1			EA	21	92EC	725 				024				ON A FLIGHT FROM RIC TO RDU WITH RDU IN SIGHT, HYDRAULIC PRESSURE WENT TO ZERO. GEAR WAS BLOWN DOWN. CHECK LIST FOLLOW	ED FOR A NO-HYDRAULIC PRESSURE LANDING. FLUID WAS EVIDENT IN NOSE WHEELWELL. MAINTENANCE TECHNICIANS DETERMINED ONLY P	ARTIAL LOSS OF FLUID AND PRESSURE ON SYSTEM 10 HOURS LATER. FOUND A B-NUT FOR NOSE GEAR-UP LINE LOOSE. TIGHTENED B-NUT	. CYCLED GEAR, RAN ENGINES TO BLEED HYDRAULIC PUMPS. SYSTEM FUNCTIONED NORMALLY. SUSPECT CAUSE WAS A LOOSE JAM NUT AT	 BULKHEAD CONNECTION FROM WHEELWELL TO AVIONICS BAY ALLOWING FITTING TO VIBRATE LOOSE.		2	L	7	2 	4F			RT	A10CE 					 
1995041400400	19950414	00400	SO 	1995	4	14	95ZZZX1746 	1	19950324	G	7830	192001914	HINGE 	ROHR 	2080023 	LKHEED	1329 	132925 	5263125	SO 										NR 2 THRUST REV	CRACKED 	B			FQQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	901EH	7235 			RC0284	5230				DURING A SCHEDULED INSPECTION OF NR 2 T/R, THE RT AFT HINGE OF THE UPPER DOOR WAS FOUND CRACKED. CAUSE UNKNOWN.						2	L	7	4 	4F				2A1SO 					 
1995041400401	19950414	00401	CE 	1995	4	14	95ZZZX1747 	1	19950221	G	2820	5426002011	FUEL LINE 			LEAR 	60 	60LEAR 	5170707	CE 										BELLY DRY BAY	CHAFED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	637LJ					037				AIRCRAFT WAS IN FOR FIRST SERIES OF INSPECTIONS. THE FUEL CROSSOVER FUEL LINE WAS BEING CHAFED BY THE ELEVATOR MAIN CAB	LES. THE AN833-12D ELBOW LOCATED AT THE RT END OF THE CROSS FLOW TUBE WAS ROTATED IN ITS BRACKET UPWARD. THE TUBE WAS 	THEN FORMED TO FIT. THE TUBE WAS THEN FORMED HIGH ENOUGH TO PROVIDE A TANGENCY TO THE CABLES. HAVE ALERTED THE PRODUCT	ION AREA. AIRFRAME TIME 293.3.			2	L	7	2 	4F			RT	A10CE 					 
1995041400402	19950414	00402	NM 	1995	4	14	95ZZZX1748 	1	19950126	G	3520	27034812	LANYARD 		417T4205142 	BOEING	767 	76727G 	7102502	NM 										OXYGEN SYSTEM	FAILED 	H				K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	15	2FOR	10 	10 			25537				LANYARD FOR ACTIVATING PASSENGER CHEMICAL OXYGEN SYSTEM FAILED DURING ACTIVATION TEST. INSPECTION OR OTHER LANYARDS ON 	THE ACFT RESULTED IN APPROXIMATELY 50 PERCENT FAILURE RATE. ALL LANYARDS REPLACED WITH NEW SERVICEABLE LANYARDS. OXYGE	N ASSEMBLY MANUFACTURER PURITAN BENNETT WAS NOTIFIED AND IS PERFORMING FAILURE ANALYSIS ON REMOVED LANYARDS. BOEING AIR	CRAFT HAS BEEN NOTIFIED AND IS INVESTIGATING THE PROBLEM.			2	L	7	2 	4F			RT	A1NM 					 
1995041400403	19950414	00403	CE 	1995	4	14	95ZZZX1749 	1	19950330	G	5720	5520130	FITTING 			CESSNA	500 	500CESSNA 	2076602	CE 										LT JACK PAD	RIVET MISSING 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	21	360DA	10027				5000056				DURING AIRCRAFT INSPECTION FOR 10,000-HOUR X-RAY OF WING, FOUND 4 HUCK RIVETS ON LEFT WING JACK PAD WS 96 ON PN 5520130 	JACK PAD FITTING WERE IMPROPERLY SWAGED AND COLLARS WERE MISSING. NO RECORD OF ANY WORK DONE IN THIS AREA. AREA NOT IN	SPECTED ON PHASE INSPECTIONS. ENGINEERING APPROVAL OBTAINED TO INSTALL HI-LOK AS REPLACEMENTS GRIP LENGTH ON ORIGINAL F	ASTENERS WAS TOO LONG CAUSING IMPROPER SEATING OF RIVET COLLARS. SUGGEST VISUAL INSPECTION ON ALL AIRCRAFT.			1	L	7	2 	4F				A22CE 					 
1995041400404	19950414	00404	CE 	1995	4	14	95ZZZX1750 	1	19950330	G	5551	553100729	ATTACHMENT 			CESSNA	500 	500CESSNA 	2076602	CE 										HORIZ STAB	CRACKED 	H		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	360DA	10027				5000056				DURING 10,000-HOUR INSPECTION, CRACK FOUND AT HORIZONTAL STABILIER ATTACH BRACKET USING EDDY CURRENT INSPECTION. ZYGLO 	AND VISUAL INSPECTIONS SHOWED NO DEFECT. DEFECT TOO CLOSED UP FOR DETECTION. NEW PART OBTAINED FROM MANUFACTURER AND I	NSTALLED. REFER TO ATTACHMENT FROM CESSNA NDT MANUAL FOR DETAILS.				1	L	7	2 	4F				A22CE 					 
1995041400405	19950414	00405	EA 	1995	4	14	95ZZZX1751 	2	19950301	G	7200		ENGINE 								PWA 	PT6 	PT6* 	52043	EA 					MAINT PART	HARD O-RING 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	07										DURING MAINTENANCE ON A PT6 ENGINE, FOUND A NEW O-RING PN MS9388115 CAME OUT OF PACKAGING UNUSEABLE DUE TO VERY HARD CON	DITION. O-RING PURCHASED FROM AVIALL ABOUT JUNE, 1994.										3	T			E2NE				 
1995041400406	19950414	00406	NE 	1995	4	14	95ZZZX1752 	2	19950327	G	7321	72807722	PILOT VALVE 	HAMSTD 	JFC60 						PWA 	JT8 	JT8* 	52044	NE 					SPEED GOV	SEIZED 	B	S		SI3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03					11CN					RECEIVED PILOT VALVES AND HOUSING GROUP WITH SPEED GOVERNING PILOT VALVE SEIZED IN HOUSING BORE. (REF. FIG. 13 OF CMM 7	3-21-05, ITEM 260. SEIZED IN BORE OF ITEM 275). NOTE: THIS 'PILOT VALVES AND HOUSING GROUP' CAN BE INSTALLED IN A NUMB	ER OF JFC 60 MODELS: CMM 73-21-1, CMM 73-21-04, CMM 73-21-05.									4	F			E2EA				 
1995041400462	19950414	00462	WP 	1995	4	14	95ZZZX1753 	1	19950324	G	3350	602094001	EEL SIGN 			DOUG 	DC9 	DC931 	3022065	WP 										PASSENGER DOOR	FAILED TEST 	B			EF2R	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	07	650UG					47418				FORWARD SERVICE DOOR SELF-ILLUMINATING EMERGENCY EXIT SIGN FAILED LUMINOSITY CHECK. REPLACED SIGN PER SRM 51-30-1. AIR	CRAFT TT, 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400464	19950414	00464	WP 	1995	4	14	95ZZZX1755 	1	19950324	G	5753	59121251	SPAR CAP 			DOUG 	DC9 	DC931 	3022065	WP 										LT TE FLAP	CORROSION 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				LEFT WING FLAP, STA XFLS 168.5, AFT LOWER SPAR CAP HAS CORROSION BULGE. REPAIRED CAP PER DALFORD AVIATION XEA NR X9-57-	17, REVISION 2. AIRCRAFT TT, 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400465	19950414	00465	WP 	1995	4	14	95ZZZX1756 	1	19950324	G	5755	5910052	SKIN 			DOUG 	DC9 	DC931 	3022065	WP 										RT SPOILER	DELAMINATION 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				RIGHT WING OUTBOARD SPOILER DELAMINATED ON UPPER SURFACE. REPAIRED SPOILER PER SRM 51-70-2. AIRCRAFT TT, 54,495 HRS.						2	L	7	2 	4F				A6WE 					 
1995041400466	19950414	00466	WP 	1995	4	14	95ZZZX1757 	1	19950310	G	5320		DOUBLER 			DOUG 	DC9 	DC931 	3022065	WP 										FS 1121-1132	CORROSION 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				HEAVY CORROSION AND CRACK ON INNER SKIN DOUBLER FS 1121 - FS 1132, BETWEEN LONGERONS 17L-18L. REPAIRED DOUBLER PER SRM 	53-01, FIGURE 2. AIRCRAFT TT, 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400467	19950414	00467	WP 	1995	4	14	95ZZZX1758 	1	19950310	G	5330	591142551	SKIN 			DOUG 	DC9 	DC931 	3022065	WP 										FS 950 29R	CORROSION 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				HEAVY CORROSION ON INNER SKIN FS 950 AT LONGERON 29R. REPAIRED SKIN PER DALFORT AVIATION XEA NR X9-53-80. AIRCRAFT TT,	 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400468	19950414	00468	WP 	1995	4	14	95ZZZX1759 	1	19950310	G	5400	5913262	ANGLE 			DOUG 	DC9 	DC931 	3022065	WP 										RT PYLON	CRACK 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				RIGHT PYLON ANGLE RIB HAS A .75 INCH CRACK UNDER PANEL NR 8204. REPAIRED ANGLE PER SRM 54-01, FIGURE 2. AIRCRAFT TT, 5	4,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400469	19950414	00469	WP 	1995	4	14	95ZZZX1760 	1	19950310	G	5320		DOUBLER 			DOUG 	DC9 	DC931 	3022065	WP 										FS 1132-1143	CORROSION 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				HEAVY CORROSION ON INNER DOUBLER FS 1132 - FS 1143, BETWEEN LONGERONS 18L-20L. REPLACED DOUBLER PER SRM 51-30-02. AIRC	RAFT TT, 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400470	19950414	00470	WP 	1995	4	14	95ZZZX1761 	1	19950310	G	5320	3917624	FITTING 			DOUG 	DC9 	DC931 	3022065	WP 										FS 986-996	CRACK 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				FS 986 - FS 996, RBL 15, 54 INCHES AND 18 INCHES ABOVE FLOOR, 2 EACH FITTINGS CRACKED AROUND FASTENERS. REPLACED FITTIN	GS PER SRM 51-3-5, AND SRM 51-30-2. AIRCRAFT TT, 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400471	19950414	00471	WP 	1995	4	14	95ZZZX1762 	1	19950310	G	5400	5913262	ANGLE 			DOUG 	DC9 	DC931 	3022065	WP 										RT PYLON RIB	CRACK 	B			KF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	650UG					47418				RIGHT PYLON ANGLE RIB HAS 1 INCH LONG CRACK UNDER PANEL NR 8206. REPLACED ANGLE RIB PER SRM 51-30-02. AIRCRAFT TT. 54,	495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400472	19950414	00472	WP 	1995	4	14	95ZZZX1763 	1	19950314	G	5313	5951685	FITTING 			DOUG 	DC9 	DC931 	3022065	WP 										FS 760	CORROSION 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				MODERATE CORROSION DAMAGE AT LONGERON 36 END FITTING, FS 760. REPLACED FITTING PER SRM 53-02, FIGURE 12. AIRCRAFT TT, 	54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400473	19950414	00473	WP 	1995	4	14	95ZZZX1764 	1	19950314	G	5320		SHEAR TIE 			DOUG 	DC9 	DC931 	3022065	WP 										FS 1089	CRACK 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				SHEAR TIE HAS CORROSION AND .5 INCH CRACK, FS 1089 BETWEEN LONGERONS 16L-17L. REPLACED SHEAR TIE PER SRM 53-30-5. AIRC	RAFT TT, 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400474	19950414	00474	WP 	1995	4	14	95ZZZX1765 	1	19950314	G	5330		SKIN 			DOUG 	DC9 	DC931 	3022065	WP 										FS 1132	CRACK 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				FUSELAGE SKIN HAS A 5 EACH 1 INCH CRACK ON CANT FRAME, STA 1132 AT LONGERON 20R. REPAIRED SKIN PER SRM 53-01, FIGURE 2.	 AIRCRAFT TT, 4,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400475	19950414	00475	WP 	1995	4	14	95ZZZX1766 	1	19950314	G	5320	9911509	ANGLE 			DOUG 	DC9 	DC931 	3022065	WP 										FS 110	CORROSION 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				HEAVY CORROSION ON ANGLE FRAME TEE CAP, FS 110 BETWEEN LONGERONS 26R-27R. REPAIRED ANGLE PER DALFORT AVIATON XEA NR X9-	53-74. AIRCRAFT TT, 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400476	19950414	00476	WP 	1995	4	14	95ZZZX1767 	1	19950314	G	5320		DOUBLER 			DOUG 	DC9 	DC931 	3022065	WP 										FS 990	CRACK 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				FS 990, BETWEEN LONGERONS 15R-16R, INNER SKIN DOUBLER HAS A 1 INCH LONG CRACK INSIDE RT LAV. REPAIRED INNER DOUBLER PER	 SRM 53-04, FIGURE 41. AIRCRAFT TT, 54,495 HRS.					2	L	7	2 	4F				A6WE 					 
1995041400477	19950414	00477	WP 	1995	4	14	95ZZZX1768 	1	19950314	G	5311		FRAME 			DOUG 	DC9 	DC931 	3022065	WP 										FS 1074	CRACK 	B			EF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	650UG					47418				ONE INCH LONG CRACK ON CANT FRAME FS 074, LONGERON 4L. REPAIRED FRAME PER SRM 53-01, FIGURE 2. AIRCRAFT TT, 54,495 HRS	.					2	L	7	2 	4F				A6WE 					 
1995041400510	19950414	00510	SO 	1995	4	14	95ZZZX1771 	1	19950209	G	5551	MS21069L4	NUTPLATE 			GULSTM	AA5 	AA5B 	3960105	SO 										HORZ STAB ATTACH	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	4540L	4122 				AA5B1307				ALL EIGHT NUTPLATES FOUND CRACKED ON FORWARD HORIZONTAL SPAR ATTACH. SUSPECT CAUSE SITTING ON TAIL TO PARK AIRCRAFT. N	UTPLATES WERE FOUND AFTER REMOVING STABILIZER FOR REPAIR AND CANNOT BE SEEN ON NORMAL INSPECTION. SUBMITTER WOULD RECOM	MEND REMOVING STABILIZER EVERY 500 HOURS FOR VISUAL INSPECTION.				1	L	7	1 	3O				A16EA 					 
1995041400511	19950414	00511		1995	4	14	95ZZZX1772 	1	19950322	G	2434	902014	BEARING 	PRESTOLITE 	ALT9422 															SLIP RING END	FAILED 	B			CYKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07					62273					ALTERNATOR FAILED DUE TO REAR BEARING FAILURE. SUBMITTER SUGGESTS A NEED FOR DIFFERENT DESIGN ON REAR BEARING.																			 
1995041400512	19950414	00512		1995	4	14	95ZZZX1773 	1	19950316	G	2434	902014	BEARING 	ELECTROSYS 	ALU8421R 															SLIP RING END	FAILED 	B			CYKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07					3082612					BEARING ROLLERS FAILED. SUBMITTER STATES THIS BEARING HAS ALWAYS BEEN THE WEAK SPOT IN THESE ALTERNATORS. IT IS GETTIN	G WORSE. REAR HOUSING SHOULD BE DESIGNED TO ACCEPT A BETTER, MORE STABLE BEARING.																		 
1995041400513	19950414	00513		1995	4	14	95ZZZX1774 	1	19950320	G	2434	902014	BEARING 	PRESTOLITE 	ALT9422 															SLIP RING END	GALLED 	B			CYKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07					894100013					INSPECTION FOUND ALTERNATOR WITH INNER RACE OF BEARING GALLED. SUBMITTER STATES A NEED FOR A NEW DESIGN BEARING.																			 
1995041400514	19950414	00514	EA 	1995	4	14	95ZZZX1775 	2	19950321	G	8530	SL134441	PIN 								LYC 	O540 	IO540K1F5 	41532	EA 					PISTON	FAILED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07		178 					L1572548A			FOUND PISTON PIN BROKEN DURING ROUTINE TEAR DOWN FOR OVERHAUL.											3	O			1E4				 
1995041400515	19950414	00515		1995	4	14	95ZZZX1776 	1	19950412	G	3510	474133	MASK 	SCOTT 	80289602 															FLOW CHECK VALVE	MISMANUFACTURED 	B		A	GW1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	03										RECEIVED 6 EACH OXYGEN MASKS FROM PIPER AIRCRAFT. THE UNITS WERE RECEIVED NEW IN SEALED BAGS. THE 'FLOW INDICATOR/CHEC	K VALVES' WERE INSTALLED BACKWARDS. ALL MASKS HAD ASSEMBLY DATE OF 4Q94. PIPER AIRCRAFT AND SCOTT AVIATION HAVE BEEN N	OTIFIED.																	 
1995041400517	19950414	00517		1995	4	14	95ZZZX1778 	4	19950313	G	3416	10143501211	ALTIMETER 	AEROSONIC 		SUD 	CM170 	CM170R 	3650101	EU 										COCKPIT	MISWIRED 	B			MGOR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	09	332DM					209				TRANSPONDER MODE-C WAS REPORTED INOPERATIVE. FOUND AIRCRAFT WAS WIRED FOR WRONG ALTIMETER DURING RECENT INSTALLATION. F	OUND INSTALLATION HAD BEEN INSPECTED IAW 'FAR 91.171 AND 91.172' WHICH ARE OBSOLETE. RE-WIRED AIRCRAFT.					1	M	7	2 	3J			RT	EXPA1M72					 
1995041400518	19950414	00518		1995	4	14	95ZZZX1779 	4	19950313	G	2312	CI139	ANTENNA 			SUD 	CM170 	CM170R 	3650101	EU 										VHF COMM	DEFECTIVE 	B			MGOR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	09	332DM					209				FOUND USED COMM ANTENNA HAD RECENTLY BEEN INSTALLED. PART WAS AN UN-AIRWORTHY PART AND WAS NOT IN SERVICEABLE CONDITION	.					1	M	7	2 	3J			RT	EXPA1M72					 
1995041400519	19950414	00519	EU 	1995	4	14	95ZZZX1780 	1	19950313	G	2720		PEDAL 			SUD 	CM170 	CM170R 	3650101	EU 										RUDDER	INTERFERENCE 	B			MGOR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	09	332DM					209				RUDDER DOES NOT HAVE FULL TRAVEL. FOUND RUDDER PEDAL TO HIT RADIO STACK THAT WAS RECENTLY INSTALLED. NO ACTION TAKEN P	ER CUSTOMER REQUEST.					1	M	7	2 	3J			RT	EXPA1M72					 
1995041400520	19950414	00520	EA 	1995	4	14	95ZZZX1781 	2	19950329	G	8530	LW13870	CYLINDER 								LYC 	O540 	O540F1B5 	41532	EA 					NR 6 CYLINDER	MISMANUFACTURED 	B			YV3R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	05							L2485640A			CYLINDER NR 6 ON A NEW PRODUCTION ENGINE HAS THE CYLINDER HEAD ORIENTED 2 DEGREES CCW RELATIVE TO THE BASE AND THE OTHER	 CYLINDERS. THIS PUTS THE EXHAUST FLANGE SURFACE OUT OF ALIGNMENT WITH THE OTHER CYLINDERS AND THE PUSH ROD HOUSINGS AR	E ASKEWED ACCORDINGLY.									3	O			E295				 
1995041400525	19950414	00525		1995	4	14	95ZZZX1786 	1	19950327	G	3710	212CW	PUMP 	AIRBORNE 																VACUUM SYSTEM	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01		2 			033587					PUMP FAILED AFTER OVERHAUL. FAILED LESS THAN 2 HOURS AFTER INSTALLATION.																			 
1995041400529	19950414	00529	SO 	1995	4	14	95ZZZX1790 	2	19950224	G	7322	63255531	LEVER 		632840A1 	CESSNA	210 	T210N 	2073456	CE 	CONT 	O520 	TSIO520R 	17040	SO 					THROTTLE BODY	BROKEN 	D	P	A		O				OTHER 				R			PARTIAL RPM/PWR LOSS 			DE	DESCENT 	1			CE	07	5313U		913 			21064862	522546			THROTTLE CONTROL FAILED AFTER POWER REDUCTION FOR DESCENT INTO MEM. ENGINE POWER REMAINED AT APPROXIMATELY 24 INCHES M.	 P. AIRCRAFT SUCCESSFULLY LANDED WITH MIXTURE CONTROL. FOUND THROTTLE LEVER BROKEN AT BASE OF ARM AND REAR ALTERNATOR 	BELT BROKEN. CAUSE OF BREAKAGE UNDETERMINED, THROTTLE CONTROL ATTACHMENT AND ALTERNATOR BELT CONDITION WERE KNOWN TO BE	 CHECKED AT 50-HOUR INSPECTION JUST PRIOR TO INCIDENT AND FOUND SATISFACTORY. FORWARDED INFORMATION ON INCIDENT TO CESS	NA AN TCM PRODUCT SAFETY.		1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995041400530	19950414	00530	CE 	1995	4	14	95ZZZX1791 	1	19950313	G	3246	201302561	HUB 	MCAULY 	D302916 	CESSNA	172 	172M 	2072418	CE 										BOLT HOLE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	1252U	1404 			760205	17266947				SMALL CRACKS WERE FOUND AT BOLT HOLES WHERE WHEEL FLANGE ATTACHES TO HUB. SUBMITTER SUGGESTS IF UNDETECTED, THESE CRACK	S COULD LEAD TO WHEEL FAILURE.					1	H	7	1 	3O			NT	3A12 					 
1995041400531	19950414	00531	CE 	1995	4	14	95ZZZX1792 	1	19950304	G	3244		TIRE 	GOODYEARAERO		BEECH 	200 	B200 	1152922	CE 										OUTSIDE EDGE	BULGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	2748X	243 			41010901	BB1258				THE TIRE HAS 16 BULGES AROUND THE OUTSIDE EDGES ON THE OUTSIDE TREAD.						1	L	7	2 	4T				A24CE 					 
1995041400532	19950414	00532	SO 	1995	4	14	95ZZZX1793 	1	19950324	G	5620	JF7647	WINDOW 			LKHEED	1329 	132925 	5263125	SO 										CABIN	CRACKED 	B			FGQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	901EH					5230				DURING SCHEDULED INSPECTION, PRISM CHECK OF CABIN WINDOWS WAS CONDUCTED AND 5 OF THE 10 WINDOWS WERE FOUND CRACKED. AFT	ER REMOVAL, CURED SEALANT WAS FOUND IN THE CRACKS INDICATING CRACKS BEGAN DURING INSTALLATION. THE 5-YEAR X-RAY INSPECT	ION WAS CONDUCTED ON 5-11-94 AND A PRISM INSPECTION WAS CONDUCTED DURING PRE-PURCHASE IN AUGUST, 1994. THESE WINDOWS WE	RE ALL PREVIOUSLY INSTALLED AND SHOULD HAVE BEEN DETECTED DURING ONE OF THE PREVIOUS INSPECTIONS.			2	L	7	4 	4F				2A1SO 					 
1995041400535	19950414	00535	SO 	1995	4	14	95ZZZX1796 	1	19950403	G	7603	67639008	CONTROL CABLE 			PIPER 	PA28 	PA28140 	7102802	SO 										THROTTLE	SEPARATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	98301					2826157				THROTTLE CABLE SEPARATED WHILE ACFT ON RAMP AT TIME OF START-UP.						1	L	7	1 	3O			 	2A13 					 
1995041400536	19950414	00536		1995	4	14	95ZZZX1797 	1	19950331	G	2435	N207533	INSULATORS 	LUCAS 	BC09101 															BRUSH HOLDER	MISSING 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	03		1212 			1797					STARTER/GENERATOR WAS PURCHASED FROM DEHAVILLAND ZERO TIME NEW. AFTER 1211.5 FLIGHT HOURS OF OPERATION, STARTER/GENERAT	OR FAILED. TEAR DOWN REVEALED INSULATORS WERE MISSING FROM THE BRUSH HOLDERS. THIS CAUSED THE ARMATURE AND STATOR TO S	HORT CIRCUIT RESULTING IN STARTER/GENERATOR FAILURE.																	 
1995041400537	19950414	00537	SO 	1995	4	14	95ZZZX1798 	2	19950325	G	8530	630626	BALANCE TUBE 			CESSNA	182 	182 	2072702	CE 	CONT 	O470 	O470R 	17026	SO 					CYL INTAKE	DISCONNECTED 	B			SH5R	O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			NE	03	92680					18260308	238098H			PILOT REPORTED ROUGH ENGINE IN-FLIGHT AND WOULD NOT IDLE ON GROUND. FOUND BALANCE TUBE ASSY DISCONNECTED FROM RT SIDE A	ND BOTH ENDS BROKEN OFF. TACH TIME 8418.1.					1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995041400538	19950414	00538	EA 	1995	4	14	95ZZZX1799 	2	19950325	G	8520		CYLINDER 			PIPER 	PA60 	PA60602P 	7106015	NM 	LYC 	O540 	IO540S1A5 	41532	EA 					RT ENG NR 4	BASE NUT FAILED 	D				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			J	R		WARNING INDICATION 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			WP	23	6902T	1893 	350 			608265046				ON TAKEOFF, RT ENGINE FIRE LIGHT, LOSS OF POWER. PILOT SHUT DOWN, RETURNED TO AIRPORT. FOUND NR 4 CYLINDER HELD ON BY 	ONE BASE NUT. EXAMINED CYLINDER/PISTON, FOUND NO DISCREPANCIES. SUSPECT NUTS OVER/UNDERTORQUED.					1	M	7	2 	3O	3	O	RT	A17WE 	1E4				 
1995041400539	19950414	00539	SO 	1995	4	14	95ZZZX1800 	1	19950331	G	2731	4322100	HORN 		4248004 	PIPER 	PA31 	PA31350 	7103110	SO 										ELEV TRIM TAB	LOOSE 	B			IGXR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	771A	4600 				317852027				ON ELEVATOR TRIM TAB ASSEMBLY, FOUND HORN LOOSE WHERE IT IS RIVETED TO THE RIBS OF THE TAB. THIS CONDITION ATTRIBUTED T	O FREE-PLAY IN THE TAB.					1	L	7	2 	3O				A20SO 					 
1995041400540	19950414	00540	EA 	1995	4	14	95ZZZX1801 	2	19950330	G	8530	74230	GUIDE 			SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					EXH VALVE	PART MISSING 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	130ER		1568 		LW12419	1511				DURING CYLINDER OVERHAUL, EXHAUST VALVE GUIDE FOUND MISSING APPROXIMATELY ONE-HALF OF THE LOWER PORTION OF THE GUIDE. T	HE WHOLE UPPER PORTION OF THE GUIDE THAT NORMALLY PROTRUDES INTO THE ROCKER BOX AREA WAS ALSO MISSING.					1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995041400541	19950414	00541	EA 	1995	4	14	95ZZZX1802 	2	19950330	G	8530	74230	GUIDE 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D2A 	41508	EA 					EXH VALVE	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	167ER		398 		LW12419	2841183				DURING CYLINDER OVERHAUL, EXHAUST VALVE GUIDE FOUND CRACKED AT THE LOWER END OF THE GUIDE. THE CRACK WAS ORIENTED IN TH	E SAME PLACE AS THE ROCKER ARM.					1	L	7	1 	3O	3	O		2A13 	E274				 
1995041400542	19950414	00542		1995	4	14	95ZZZX1803 	1	19950216	G	7600	310047503	CONTROL ASSY 								PWA 	PT6 	PT6A65B 	52043	EA 					ENGINE	DEFECTIVE 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01										CONTROL ASSY DEFECTIVE.											4	T			E4EA				 
1995041400543	19950414	00543	EA 	1995	4	14	95ZZZX1804 	2	19950216	G	7250	3029885	NUT 								PWA 	PT6 	PT6A65B 	52043	EA 					POWER SECT	DAMAGED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										NEWLY OVERHAULED PART RECEIVED FROM TURBINE PARTS THAT HAS THREAD DAMAGE AND HEAVY CORROSION. RECEIVED UNDER P.O. NR 95	0207023.										4	T			E4EA				 
1995041400548	19950414	00548	EA 	1995	4	14	95ZZZX1809 	2	19950111	G	7210	3032649	BEARING 			BEECH 	1900 	1900D 	1154162	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					NR 6	SPALLED 	B		A	MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	11ZV	3873 			84C559	UE11	114051			THE METAL OBSERVED IN THE ENGINE WAS BEING GENERATED BY THE NR 6 BEARING. SUBMITTER SUGGESTS FOCUSING INVESTIGATION ON 	THE PROPELLER ASSY AND ITS KNOWN STATIC PROBLEMS.					2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995042100097	19950421	00097	EA 	1995	4	21	95ZZZX1811 	2	19950119	G	7210	310164701	BEARING 			BEECH 	1900 	1900D 	1154162	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					NR 6	SPALLED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	35YV	5412 			64D513	UE35	114073			THE NR 6 BEARING WAS FOUND WITH SPALLING ON ONE INNER RACE HALF AND SEVERAL OF THE BEARING BALLS. SUBMITTER BELIEVES TH	E SPALLING TO BE INTRODUCED BY THE STATIC PROBLEMS THAT ARE KNOWN TO BE ASSOCIATED WITH THE PROPELLER SYSTEM.					2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995042100100	19950421	00100	EA 	1995	4	21	95ZZZX1814 	2	19950102	G	7532	311271401	VALVE ASSY 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					GAS GEN	FRETTED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	76YV				5R106	UC76	32488			SUSPECT CAUSE OF FAILURE IS A FAULTY BLEED VALVE. THE DEFINITE CAUSE IS STILL UNDER INVESTIGATION.						2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995042100101	19950421	00101	EA 	1995	4	21	95ZZZX1815 	2	19950112	G	7230	310920901	BEARING 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					GAS GEN COMP	FRACTURED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	118YV	2353 			FC12409	UC118	32027			THE PRELIMINARY INVESTIGATION IS INDICATING THE NR 1 BEARING FAILED.						2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995042100102	19950421	00102	EA 	1995	4	21	95ZZZX1816 	2	19950214	G	7210	310063201	BEARING 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					PROP REDUCTION	SPALLED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	144YV	11548			72B809	UC144	32394			PRELIMINARY FINDINGS ARE FOCUSING ON THE ARCING AND MAGNETISM FOUND THROUGHOUT THE ENTIRE GEAR TRAIN.						2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995042100104	19950421	00104	EA 	1995	4	21	95ZZZX1818 	2	19950125	G	7230	311211701	BEARING 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					GAS GENERATOR	FRACTURED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	158YV	147 			FC15201	UC158	97316			THERE ARE 4 AREAS THAT SUBMITTER IS INVESTIGATING. A. A MATERIAL FAILURE OF THE NR 1 BEARING. B. ELECTRICAL DISCHARG	E DUE TO THE MAGNETISM ON THE STARTER DRIVE GEAR. C. PLASTIC BEAD MATERIAL. D. THE FIT OF THE NR 1 BEARING ONTO THE 	REAR STUB SHAFT. FOUND NR 1 BEARING FRACTURED.				2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995042100105	19950421	00105	NM 	1995	4	21	95ZZZX1819 	1	19950322	G	2782	69358861	ACTUATOR 		65446517 	BOEING	737 	737* 		NM 										LE SLAT	PLUGGED 	B			IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01					184					ORIFICE HOLE OF THE ORIFICE PLUG WAS PLUGGED WITH DEBRIS. THIS COULD CAUSE ACTUATOR TO WORK INTERMITTENTLY OR NOT AL AL	L. THE DEBRIS WAS DETERMINED TO BE PARTICLES FROM A PACKING AND/OR BACKUP RING. POSSIBLE INCORRECT INSTALLATION OF G. 	T. TYPE SEAL COULD CAUSE PREMATURE CHAFING AND WEAR OF THE T-SEAL WHICH COULD BE THE SOURCE OF THE MATERIAL. CARE SHOUL	D BE TAKEN TO ENSURE BACKUP RINGS ON THE G. T. SEALS ARE INSTALLED CORRECTLY PER THE ILLUSTRATION ON THE PACKAGE.			2	L	7	2 	4F			RT	A16WE 					 
1995042100106	19950421	00106	NM 	1995	4	21	95ZZZX1820 	1	19950322	G	2740	6977851	BRAKE SPRING 		65C347514 	BOEING	737 	737* 		NM 										HORIZ STAB	BROKEN 	B			IU6R	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			NM	01		14307			KE00061					THE HORIZONTAL STABILIZER TRIM GEARBOX FAILED THE AUX BRAKE TEST. UPON DISASSEMBLY, SPRINGS WERE FOUND SHATTERED. THIS	 CONDITION HAS BEEN FOUND AND REPORTED IN PREVOUS MDR'S. PER BOEING TELEX AEO-AUB-94-0195RR, THE (DASH 1) SPRINGS ARE T	O BE REPLACED WITH (DASH 2) SPRINGS AS SUBMITTER SUGGESTS THE (DASH 1) SPRINGS HAD IMPROPER HEAT TREAT OR INCORRECT ALLO	YS IN THE SPRINGS.			2	L	7	2 	4F			RT	A16WE 					 
1995042100107	19950421	00107	NM 	1995	4	21	95ZZZX1821 	1	19950327	G	5754	6534780	FENCE 			BOEING	727 	727 	1384001	NM 										NR 4 LE SLAT	CRACKED 	B	S		IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01					BN224					DURING TEAR-DOWN INSPECTION, A CRACK WAS DETECTED IN THE EXTERIOR SKIN C/T AERODYNAMIC FENCE ATTACHMENT POINT AT SLAT UP	PER SURFACE NR 2 HOLE FROM L/E AT STA 86.5. DYE PENETRANT INSPECTION CONFIRMED CRACK, WAS .80 INCH LONG. SUSPECT TOO S	MALL OF AREA WASHER, PN 66-20913-1, SECURED TO INTERIOR OF SKIN AND POSSIBLY TOO SMALL OF RADIUS AT CHEM MILL AREA ADJAC	ENT TO WASHER ATTACH POINTS.			2	L	7	3 	4F				A3WE 					 
1995042100108	19950421	00108	NM 	1995	4	21	95ZZZX1822 	1	19950327	G	5754	6534780	FENCE 			BOEING	727 	727 	1384001	NM 										NR 4 LE SLAT	CRACKED 	B	S		IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01										DURING TEAR-DOWN INSPECTION FOR CLEANING AND INSPECTION OF SLAT EXTERIOR SKIN C/T AERODYNAMIC FENCH ATTACH HOLES, DYE PE	NETRANT INSPECTION REVEALED CRACK INDICATION, STA 82.5 .35 INCH LONG NR 1 HOLE UPPER SURFACE. SUSPECT TOO SMALL OF AREA	 WASHER, PN 66-20913-1, SECURED TO INTERIOR OF SKIN AND POSSIBLE TOO SMALL OF RADIUS AT CHEM MILL AREA ADJACENT TO WASHE	R ATTACH POINTS.			2	L	7	3 	4F				A3WE 					 
1995042100109	19950421	00109	NM 	1995	4	21	95ZZZX1823 	1	19950327	G	5754	6534780	FENCE 			BOEING	727 	727 	1384001	NM 										NR 5 LE SLAT	CRACKED 	B	S		IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01					BN39					DURING TEAR-DOWN INSPECTION, A CRACK WAS DETECTED IN THE EXTERIOR SKIN C/T AERODYNAMIC FENCE ATTACHMENT POINTS (3 PLACES	) AT SLAT STA 86.5, STA 88.0, AND STA 91.75. DYE PENETRANT INSPECTION CONFIRMED CRACKS ALL APPROXIMATELY 1.25 INCH LONG	 IN LENGTH, IN UPPER SKIN. SUSPECT TOO SMALL OF AREA WASHER PN 66-20913-1 SECURED TO INTERIOR OF SKIN AND POSSIBLY TOO 	SMALL OF RADIUS AT CHEM MILLED AREA ADJACENT TO WASHER ATTACH POINTS.			2	L	7	3 	4F				A3WE 					 
1995042100110	19950421	00110	NM 	1995	4	21	95ZZZX1824 	1	19950327	G	5754	6534780	FENCE 			BOEING	727 	727 	1384001	NM 										NR 5 LE SLAT	CRACKED 	B	S		IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01					BN341					DURING TEAR-DOWN INSPECTION, AERODYNAMIC FENCE WAS REMOVED FOR CLEANING AND INSPECTION. DYE PENETRANT INSPECTION REVEAL	ED TWO CRACK INDICATIONS AT STA 82.5-30.0 C/T LOWER SKIN NR 1 HOLE .2 INCH AND .25 INCH LONG OUT FROM HOLES. AT STA 86.	5, UPPER SURFACE NR 2 HOLES AFT FROM L/E UPPER SURACE .6 INCH LONG CRACK. SUSPECT TOO SMALL OF AREA WASHER PN 66-20913-	1 SECURED TO INTERIOR OF SKIN AND POSSIBLY TOO SMALL OF RADIUS AT CHEM MILL AREA ADJACENT TO WASHER ATTACH POINTS.			2	L	7	3 	4F				A3WE 					 
1995042100111	19950421	00111	NM 	1995	4	21	95ZZZX1825 	1	19950327	G	5754	6534780	FENCE 			BOEING	727 	727 	1384001	NM 										NR 4 LE SLAT	CRACKED 	B	S		IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01					BN472					DURING TEAR-DOWN INSPECTION, AERODYNAMIC FENCE WAS REMOVED FOR CLEANING AND INSPECTION OF SLAT SKIN. DYE PENETRANT INSP	ECTION PERFORMED WHICH REVEALED TWO CRACKS AT SLAT STA 86.75, .5 INCH LONG, STA 91.75, .4 INCH LONG UPPER SKIN SURFACE. 	 SUSPECT TOO SMALL OF AREA WASHER PN 66-20913-1 SECURED TO INTERIOR OF SKIN AND POSSIBLY TOO SMALL OF RADIUS AT CHEM MIL	L AREA ADJACENT TO WASHER ATTACH POINT.			2	L	7	3 	4F				A3WE 					 
1995042100112	19950421	00112	NM 	1995	4	21	95ZZZX1826 	1	19950327	G	5754	69545541	SPRING 		654465114 	BOEING	737 	7372H4 	138448C	NM 										LE SLAT	DAMAGED 	B			IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01			8430 		2103T					SPRING (56) IS COMPRESSED INSIDE STOP (57). GUIDE (55) RELEASED FROM SPRING (56) AND WAS CRUSHED INSIDE LOCK PISTON (47	). GUIDE (55) IS TIGHTLY INSTALLED INSIDE SPRING (56). SUSPECT THAT GUIDE (55) WAS NOT TIGHT INSIDE SPRING (56), CAME 	LOOSE AND CAUSED COLLATERAL DAMAGE.				2	L	7	2 	4F				A16WE 					 
1995042100113	19950421	00113	NM 	1995	4	21	95ZZZX1827 	1	19950327	G	5754	69135141	UPSTOP 			BOEING	727 	727 	1384001	NM 										NR 1 LE FLAP	CORRODED 	B			IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01					64600					PITTING CORROSION AT CONTACT POINT. SUSPECT PROTECTIVE COATING MISSING.						2	L	7	3 	4F				A3WE 					 
1995042100114	19950421	00114	NM 	1995	4	21	95ZZZX1828 	1	19950327	G	5754	69174991	CHANNEL 			BOEING	727 	727 	1384001	NM 										NR 1 LE SLAT	CRACKED 	B			IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01					64600					CRACKED IN BEND RADIUS. SUSPECTED IMPROPER OR LACK OF SHIMMING C/T CHANNEL TO TRACK ATTACH POINT.						2	L	7	3 	4F				A3WE 					 
1995042100115	19950421	00115	NM 	1995	4	21	95ZZZX1829 	1	19950327	G	5754	69179002	CHANNEL 			BOEING	727 	727 	1384001	NM 										NR 1 LE SLAT	CRACKED 	B			IU6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01					BN284					STRESS CRACKS AT RT AFT LOWER RADIUS AND CRACKED AT LT LOWER RADIUS. SUSPECT IMPROPER OR LACK OF SHIMMING C/T CHANNEL T	O TRACK ATTACH POINT.					2	L	7	3 	4F				A3WE 					 
1995042100116	19950421	00116	EA 	1995	4	21	95ZZZX1830 	2	19950330	G	7260	3022872	SLEEVE 		310199201 						PWA 	PT6 	PT6A65B 	52043	EA 					PUMP HOUSING	CORRODED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					41A493075					PART WAS RECEIVED BY THE PARTS DEPARTMENT AND DURING VISUAL INSPECTION, THE SLEEVE WAS FOUND CORRODED.											4	T			E4EA				 
1995042100117	19950421	00117	EA 	1995	4	21	95ZZZX1831 	2	19950323	G	7250	311980701	BEARING 								PWA 	PT6 	PT6A65B 	52043	EA 					PWR SECT NR 4	NOISY 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					FC28003		32069			DURING THE BALANCE PROCEDURE OF THE PT SHAFT, THE NR 4 BEARING WAS MAKING A CHATTERING NOISE. THIS BEARING WAS FROM THE	 PT6 OVERHAUL KIT PURCHASED FROM PWC.										4	T			E4EA				 
1995042100118	19950421	00118	EA 	1995	4	21	95ZZZX1832 	2	19950403	G	7260	3040026	HOUSING 								PWA 	PT6 	PT6A65B 	52043	EA 					ASSORY GEARBOX	MISMANUFACTURED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					044002					PART RECEIVED FROM STOCK WITH BEARING MOUNT OVERSIZE 1.655 INCH PLUS.											4	T			E4EA				 
1995042100119	19950421	00119		1995	4	21	95ZZZX1833 	1	19950315	G	6120	3031844	CASING ASSY 								PWA 	PT6 	PT6A65B 	52043	EA 					PROP CONTROL	DENTED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										PART WAS RECEIVED FROM VENDOR (TURBINE PARTS) AND FOUND DENTED BEYOND SERVICEABLE LIMITS.											4	T			E4EA				 
1995042100120	19950421	00120	EA 	1995	4	21	95ZZZX1834 	2	19950308	G	7260	3012124	HOUSING 								PWA 	PT6 	PT6A65B 	52043	EA 					ASSORY GEARBOX	MISMANUFACTURED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					2390					PART RECEIVED FROM STOCK. WHEN HOUSING ASSEMBLED IN THE AGB, GEARS WOULD NOT ROTATE. FURTHER INVESTIGATION REVEALED TH	E GEARS' PARTS WORKED PROPERLY WHEN INSTALLED IN ANOTHER HOUSING ASSY.										4	T			E4EA				 
1995042100121	19950421	00121	EA 	1995	4	21	95ZZZX1835 	2	19950308	G	7260	3008360	DRIVE GEAR 								PWA 	PT6 	PT6A65B 	52043	EA 					ASSORY GEARBOX	CORRODED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										RECEIVED PART FROM STOCK. PLASTIC BEAD FOUND PACKED INTO GEAR END OF SHAFT. INNER LUG FOUND CORRODED AND PITTED.											4	T			E4EA				 
1995042100122	19950421	00122	EA 	1995	4	21	95ZZZX1836 	2	19950327	G	7532	310687301	PISTON 								PWA 	PT6 	PT6A65B 	52043	EA 					BLEED VALVE	DAMAGED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										THE PISTON RECEIVED FROM PARTS ROOM AND FOUND DAMAGED. UNABLE TO INSTALL PISTON RINGS BECAUSE OF THE BENT RING GROOVE.											4	T			E4EA				 
1995042100123	19950421	00123	EA 	1995	4	21	95ZZZX1837 	2	19950308	G	7210	310236001	RING GEAR 								PWA 	PT6 	PT6A65B 	52043	EA 					POWER SECTION	TEETH NICKED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					44A697					PART RECEIVED FROM VENDOR WITH GEAR TEETH NICKED. RETURNED TO VENDOR AS UNACCEPTABLE.											4	T			E4EA				 
1995042100124	19950421	00124	EA 	1995	4	21	95ZZZX1838 	2	19950308	G	7260	3008785	GEAR 								PWA 	PT6 	PT6A65B 	52043	EA 					ASSORY GEARBOX	PITTED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										PART RECEIVED FROM VENDOR FOUND CORRODED AND PITTED. RETURN TO VENDOR AS UNACCEPTABLE FOR USE.											4	T			E4EA				 
1995042100125	19950421	00125	EA 	1995	4	21	95ZZZX1839 	2	19950308	G	7260	3017609	GEARSHAFT 								PWA 	PT6 	PT6A65B 	52043	EA 					ASSORY GEARBOX	NICKED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										PART RECEIVED FROM VENDOR AND FOUND WITH DAMAGE ON CARBON SEALING SURFACE AND BEARING MOUNTING FLANGES. FLANGES HAVE EV	IDENCE OF ROLLERS SKIDDING.										4	T			E4EA				 
1995042100126	19950421	00126	EA 	1995	4	21	95ZZZX1840 	2	19950301	G	7210	310236001	RING GEAR 								PWA 	PT6 	PT6A65B 	52043	EA 					POWER SECTION	DAMAGED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					36B504					RECEIVED PART FROM VENDOR THAT HAS DAMAGE ON GEAR TEETH.											4	T			E4EA				 
1995042100127	19950421	00127	EA 	1995	4	21	95ZZZX1841 	2	19950222	G	7260	3017609	GEARSHAFT 								PWA 	PT6 	PT6A65B 	52043	EA 					STARTER DRIVE	DAMAGED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										RECEIVING INSPECTION OF PART REVEALED DAMAGE TO SNAP-RING GROOVE, DRIVE AND SEAL END OF SHAFT AND GEAR FACE-PLATE.											4	T			E4EA				 
1995042100128	19950421	00128	EA 	1995	4	21	95ZZZX1842 	2	19950327	G	7250	3043061	VANE RING 								PWA 	PT6 	PT6A65B 	52043	EA 					HOT SECTION	DENTED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					7L779					THE VANE RING RECEIVED FROM THE PARTS ROOM AND FOUND DENTED AT THE OUTBOARD EXIT FLANGE.											4	T			E4EA				 
1995042100129	19950421	00129	EA 	1995	4	21	95ZZZX1843 	2	19950216	G	7210	3029885	NUT 								PWA 	PT6 	PT6A65B 	52043	EA 					POWER SECTION	CORRODED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01										RECEIVED 3 EACH OVERHAULED NUTS, INSPECTED, FROM AVIALL. ALL PARTS HAVE HEAVY CORROSION.											4	T			E4EA				 
1995042100130	19950421	00130	EA 	1995	4	21	95ZZZX1844 	2	19950316	G	7260	310298502	DIAPHRAGM 								PWA 	PT6 	PT6A65B 	52043	EA 					ASSORY GEARBOX	MISMANUFACTURED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					94M180		PWC94M180			PART RECEIVED FROM VENDOR (PWC SERVICE CENTER) AND THE OIL SEAL BORE WAS FOUND OVERSIZED. ACCEPTABLE LIMITS ARE: MINIM	UM 1.399 INCH TO MAXIMUM 1.400 INCH. PRESSURE SEAL BORE IS 1.412 INCH.										4	T			E4EA				 
1995042100131	19950421	00131	EA 	1995	4	21	95ZZZX1845 	2	19950118	G	7210	310076701	SUN GEAR 		3029694 	BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					POWER SECTION	FAILED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	156YV	8851 	8851 		57B849	UC156	32589			INDICATIONS ARE THAT THE FAILURE OCCURRED IN THE 1ST STAGE GEAR REDUCTION AREA. THE INVESTIGATION CENTERS AROUND THE 1S	T STAGE GEAR AND THE 1ST STAGE SUN GEAR AREA.					2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995042100132	19950421	00132	NM 	1995	4	21	95ZZZX1846 	1	19950331	G	3230	410SE1	VALVE BODY 		4105DA 	BOEING	737 	737* 		NM 										ACTUATOR	CORRODED 	B			B5SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23					48					PITTING CORROSION DISCOVERED ON OUTSIDE HOUSING DUE TO BREAK-DOWN OF ANODIZING. MANUFACTURER RECOMMENDED BLENDING AND C	HEM FILM PROTECTION PRIOR TO ANTI-CORROSION PROTECTION. MANUFACTURER BELIEVES OUTSIDE CONTAMINATION AROUND PART TO ATTA	CH SURFACE ON AIRFRAME WAS CAUSE OF ANODIZE BREAK-DOWN. PART IS SERVICEABLE EXCEPT FOR OUTSIDE COSMETIC DAMAGE.				2	L	7	2 	4F			RT	A16WE 					 
1995042100133	19950421	00133	NE 	1995	4	21	95ZZZX1847 	2	19950317	G	7250		BLADE 								GE 	CJ610 	CJ6106 	30006	NE 					TURB 1ST STAGE	BOWED 	B			IY2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15							251562A			STAGE 1 TURBINE BLADES ARE BOWED OUT OF LIMITS. TIME ON THE BLADES IS UNKNOWN. THE BLADES ARE MARKED WITH 'BK' WHICH S	HOULD IDENTIFY THE PART NUMBER. HOWEVER, 'BK' IS NOT RECOGNIZED BY GENERAL ELECTRIC.										4	J			1E16				 
1995042100134	19950421	00134	NE 	1995	4	21	95ZZZX1848 	2	19950317	G	7230	6002T57P05	BLUCKET 		6028T47P01 						GE 	CF700 	CF7002D2 	30010	NE 					FAN ROTOR	CRACKED 	B			IY2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15		2945 			7689FT		304572B			DURING EDDY CURRENT INSPECTION OF THE FAN BLUCKETS REQUIRED AS PART OF THE HOT SECTION INSPECTION, FOUND ONE FAN BLUCKET	 WITH A MINUTE CRACK ON THE LEADING EDGE IN THE HOT SECTION PORTION OF THE BLUCKET.										4	F			E7EA				 
1995042100315	19950421	00315	SW 	1995	4	21	95ZZZX1849 	1	19950327	G	6700	20006B161416	BUSHING 			BELL 	206 	206L1 	1182107	SW 										XMSN DECK	BINDING 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3184P					45774				DISCOVERED DURING MAJOR MAINTENANCE, FOUND BUSHING BINDS WHEN MOVING FLIGHT CONTROLS CAUSING BRACKET (206-063-707-001) T	O BE STRESSED CAUSING INSERTS THAT HOLD BRACKET TO ROOF TO BE PULLED CAUSING SEPARATION AND DAMAGE TO ROOF.					1	G	7	1 	3U				H2SW 					 
1995042100316	19950421	00316	SW 	1995	4	21	95ZZZX1850 	1	19950327	G	6700	20006B161416	BUSHING 			BELL 	206 	206L1 	1182107	SW 										XMSN DECK	BINDING 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1081G					45405				DISCOVERED DURING MAJOR MAINTENANCE, FOUND BUSHING BINDS WHEN MOVING FLIGHT CONTROLS CAUSING BRACKET (206-063-707-001) T	O BE STRESSED CAUSING INSERTS THAT HOLD BRACKET TO ROOF TO BE PULLED CAUSING SEPARATION AND DAMAGE TO ROOF.					1	G	7	1 	3U				H2SW 					 
1995042100319	19950421	00319	GL 	1995	4	21	95ZZZX1853 	2	19950308	G	7310	23033400	PC FILTER 		23004545 	BELL 	206 	206L4 	1182110	SW 	ALLSN 	250C 	250C30 	03013	GL 					ENGINE	UNBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	170AL	1718 				52063	CAE895745			DURING PHASE INSPECTION, FOUND FILTER LOOSE IN FILTER BOWL. FILTER ELEMENT WAS UNBONDED FROM FILTER CAP. CAUSE UNKNOWN	.					1	G	7	1 	3U	3	U	NC	H2SW 	E1GL				 
1995042100473	19950421	00473	NM 	1995	4	21	95ZZZX1865 	1	19950308	G	3240	25W714015003	BRAKE LEVER 			ISRAEL	1125 	1125 		NM 										CENTER PED	WORN 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	60AJ	200 				071				PARK BRAKE LEVER CENTER DETENT WORN OUT. UNDER NORMAL OPERATION, IT WOULD THEN ALLOW LEVER TO BE EASILY SLID INTO EMERG	ENCY POSITION DISABLING ANTI-SKID. CENTER DETENT STOP TOO SOFT OR NOT SUFFICIENT TO HOLD LEVER. SUBMITTER SUGGESTS RED	ESIGN OF LEVER FOR MORE POSITIVE LOCK IN CENTER POSITION.				2	L	7	2 	4F			RT	A16NM 					 
1995042100474	19950421	00474		1995	4	21	95ZZZX1866 	4	19950224	G	3455	G686201	CONTROL HEAD 	GABLES 		AMD 	FALC50	FALCON50MYST	2730106	EU 										ADF	FAILED 	D				O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			TX	TAXI/GRND HDL 	1			WP	23	41TH	85 				201				DATE 2-24-95, ACFT TT 2249, CYC 1057, LOCATION LAX. AFTER LANDING AT LAX, TURNING OFF THE ACTIVE RUNWAY, THE PILOT REPO	RTED SMOKE IN THE COCKPIT. THE MECHANIC FOUND ADF NR 2 CIRCUIT BREAKER TRIPPED AND NR 2 SIDE OF THE ADF INOPERATIVE. A	DF CONTROL HEAD WAS THE SOURCE OF THE SMOKE. THE CONTROL HEAD WAS ONLY 89 HOURS OUT OF FACTORY REPAIR.				2	L	7	3 	4F				A46EU 					 
1995042100475	19950421	00475	EU 	1995	4	21	95ZZZX1867 	1	19950324	G	2435	36A227602P19	BOLT 		2CM504D1D 	AMD 	FALC10	FALCON10 	2730101	EU 										START/GEN	SHEARED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	13BK		295 		795DD125	094				DURING 2A INSPECTION, REMOVED STARTER/GENERATOR SHROUD TO INSPECT BRUSHES, FOUND BOLT HEAD THAT HOLDS PRESSURE PLATE, PN	 36C717455G1, SECURED BY SAFETY WIRE ONLY. SUBMITTER SUSPECTS WRONG BOLT USED UPON ASSEMBLY (A NON-SHANKED BOLT WAS USE	D). INSTALLED PROPER BOLT COATED WITH ZINC CHROMATE TO PREVENT CORROSION.				2	L	7	2 	4F				A33EU 					 
1995042100476	19950421	00476	CE 	1995	4	21	95ZZZX1868 	1	19950224	G	3210	50810025	SIDE BRACE 		908100002 	BEECH 	90 	C90A 	1152911	CE 										RT MLG	CORRODED 	B			PAIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	1552G	1443 				LJ1206				DURING PRIMARY INSPECTION, THE RIGHT MAIN GEAR SIDE BRACE WAS FOUND CORRODED. WHAT APPEARED TO BE A BLACK SPOT .0625 IN	CH IN DIAMETER, AFTER PROBING, BECAME .25 INCH HOLE. THE CORROSION HAD STARTED INTERNALLY AND HAD EATEN THROUGH. THE C	ORROSION WAS ON THE LOWER END. AIRCRAFT IS 6 YEARS OLD.				1	L	7	2 	3T			RT	3A20 					 
1995042100477	19950421	00477	CE 	1995	4	21	95ZZZX1869 	1	19950401	G	7713	52001094	LINE 			CESSNA	402 	402C 	207590R	CE 										MP GAUGE	FAILED 	I				C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			O			OTHER 			TO	TAKEOFF 	1			SO	17	108GP					402C0058				PILOT REPORTED THAT DURING TAKEOFF ROLL, THE RIGHT MANIFOLD INDICATION DECREASED TO STATION PRESSURE, AND ABORTED THE TA	KEOFF WHILE STILL ON THE RUNWAY. NO ACTUAL LOSS OF POWER WAS REPORTED. UPON INSPECTION, IT WAS FOUND THAT STEEL MANIFO	LD PRESSURE LINE FROM THE INDUCTION PIPE TO FIREWALL HAD BROKEN AT THE FLARE ON THE INDUCTION PIPE END. TUBE WAS CUT AN	D REFLARED. GROUND CHECK NORMAL.			1	L	7	2 	3O				A7CE 					 
1995042100478	19950421	00478	CE 	1995	4	21	95ZZZX1870 	1	19950329	G	7810	969500139	BRACKET 			BEECH 	58 	58 	1152740	CE 										RT ENG EXHAUST	BROKEN 	B	S		CGOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	3122R	108 				TH1722				FOUND BOTH EXHAUST TAIL PIPE SUPPORT BRACKETS BROKEN, RT ENGINE. APPEAR TO BE BROKEN AT CREASE MARK FROM DIE DURING MAN	UFACTURE. FOUND DURING C/W WITH TCM CSB 94-15. INSPECTION OF CRANCKCASE STUDS.					1	L	7	2 	3O				3A16 					 
1995042100479	19950421	00479	CE 	1995	4	21	95ZZZX1871 	1	19950329	G	7810	9695001310	BRACKET 			BEECH 	58 	58 	1152740	CE 										RT ENG EXHAUST	BROKEN 	B			CGOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	3122R	108 				TH1722				FOUND BOTH EXHAUST TAIL PIPE SUPPORT BRACKETS BROKEN, RT ENGINE. APPEAR TO BE BROKEN AT CREASE MARK FROM DIE DURING MAN	UFACTURE. FOUND DURING C/W WITH TCM CSB 94-15. INSPECTION OF CRANCKCASE STUDS.					1	L	7	2 	3O				3A16 					 
1995042100480	19950421	00480	CE 	1995	4	21	95ZZZX1872 	1	19950329	G	7810	969500139	BRACKET 			BEECH 	58 	58 	1152740	CE 										RT ENG EXH	BROKEN 	B	S		CGOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	56B	65 				TH1730				FOUND BOTH EXHAUST TAIL PIPE SUPPORT BRACKETS BROKEN, RT ENGINE. APPEAR TO BE BROKEN AT CREASE MARK FROM DIE DURING MAN	UFACTURE. FOUND DURING C/W WITH TCM CSB 94-15. INSPECTION OF CRANKCASE STUDS.					1	L	7	2 	3O				3A16 					 
1995042100481	19950421	00481	CE 	1995	4	21	95ZZZX1873 	1	19950329	G	7810	9695001310	BRACKET 			BEECH 	58 	58 	1152740	CE 										RT ENG EXH	BROKEN 	B			CGOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	56B	65 				TH1730				FOUND BOTH EXHAUST TAIL PIPE SUPPORT BRACKETS BROKEN, RT ENGINE. APPEAR TO BE BROKEN AT CREASE MARK FROM DIE DURING MAN	UFACTURE. FOUND DURING C/W WITH TCM CSB 9415. INSPECTION OF CRANKCASE STUDS.					1	L	7	2 	3O				3A16 					 
1995042100482	19950421	00482	SW 	1995	4	21	95ZZZX1874 	1	19950324	G	7120		MOUNT 			MOONEY	M20 	M20F 	5870214	SW 										ENGINE	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	2FOR					670281				ENGINE MOUNT ASSEMBLY SHOWING A CRACK AND SEPARATION ON THE LOWER PART. THIS WAS FOUND DURING A 100-HOUR INSPECTION. T	HE RUBBER ENGINE MOUNTS THAT WERE INSTALLED ARE NOT THE ORIGINALS, THEY WERE MADE IN BRAZIL. THE PROPELLER SPINNER HAD 	BEEN REPAIRED, BUT WAS NOT DYNAMICALLY BALANCED.				1	L	7	1 	3O				2A3 					 
1995042100483	19950421	00483	SO 	1995	4	21	95ZZZX1875 	1	19950401	G	7922	53E19600	VALVE 			PIPER 	PA28 	PA28180 	7102808	SO 										THERMO BYPASS	NUT FAILED INSP 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	99	9001J	129 			50436	283026				CRIMP NUT INSPECTION DONE AT ANNUAL AND PART FAILED THE FIRST PART OF THE MANDATORY SB NR 518A, DATED 2-3-95. ONE OF TH	REE HAVE ALL FAILED THE FIRST TEST OF BEING OVER THE MINIMUM CRIMP DEPTH. (ALL AT .191 INCH). PARTS ON BACK-ORDER 3 TO	 8 WEEKS.				1	L	7	1 	3O				2A13 					 
1995042100484	19950421	00484		1995	4	21	95ZZZX1876 	4	19950309	G	2215	047340000	TRIM SPRING 		KS270A 	BEECH 	58 	58P 	1152744	CE 										PITCH SERVO	BROKEN 	B			NH2D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	110Z				20654	TJ213				TRIM SPRING TAB WAS BROKEN AND FLOATING INSIDE PITCH SERVO HOUSING.						1	L	7	2 	3O				A23CE 					 
1995042100485	19950421	00485	SO 	1995	4	21	95ZZZX1877 	1	19950324	G	7922	75944	VALVE 			PIPER 	PA28 	PA28R201 	7102816	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	3420Q	1802 				28R7737054				WHILE COMPLYING WITH LYCOMING SB518A, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. CRIMP NUT LOOSE DUE TO POOR	 DESIGN.					1	L	7	1 	3O				2A13 					 
1995042100486	19950421	00486	SO 	1995	4	21	95ZZZX1878 	2	19950328	G	8520		CRANKCASE 								CONT 	O520 	TSIO520WB 	17040	SO 					BEARING BORE	DEFECTIVE 	B			CYKR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	07							518882			IN COMPLYING WITH SB M92-09 DURING ASSEMBLY USING NEW 12-POINT NUT PN 652541 AND TORQUE OF 790-810 INCHES/POUNDS, ENGINE	 FAILED TO TURN WHEN FULL TORQUE WAS REACHED. UPON DISASSEMBLY, MAIN BEARING BORES WERE FOUND OUT OF ROUND. SUSPECT 'S	OFT' CRANKCASE.									3	O			E8CE				 
1995042100487	19950421	00487	CE 	1995	4	21	95ZZZX1879 	1	19950317	G	5320		TUNNEL 			CESSNA	170 	170A 	2072304	CE 										CABIN	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	9210A	3200 				18971				CABIN HEAT DUCT TUBING LEADING FROM THE FIREWALL TO THE REAR SEAT HEAT IS CAUSING SEVERE CORROSION IN THE CABIN TUNNEL I	NTERIOR. THIS TUNNEL SUPPORTS THE YOKE ASSEMBLY, TRIM WHEEL, AND FLAP LEVER. RECOMMEND REPLACING ALL INTERIOR DUCT TUB	ING WITH MODERN SILICONE CAT OR SCAT, INSPECT FOR CORROSION.				1	H	7	1 	3O				A799 					 
1995042100488	19950421	00488	SO 	1995	4	21	95ZZZX1880 	1	19950313	G	7810	47C21952	WYE 			PIPER 	PA46 	PA46350P 		SO 										WASTEGATE CLAMP	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	345MM	911 				4622112				INSPECTION FOUND A 2 INCH CRACK AT EXHAUST WYE. EXHAUST TRANSITION APPEARS TO BE SECURED IN 3 PLACES UNDER STRESS. OLD	 PN 47C19848.					1	L	7	1 	3O			RT	A25SO 					 
1995042100489	19950421	00489	SO 	1995	4	21	95ZZZX1881 	1	19950309	G	5751		HINGE PIN 			PIPER 	PA34 	PA34200 	7103405	SO 										AILERON	DETERIORATED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	5228T					347250226				NEOPRENE HINGE PIN FAILED DUE TO WEATHERING. THE HINGE DID NOT FAIL OR WEAR, ONLY THE PIN. SUBMITTER SUGGESTS A TIME P	ERIOD SHOULD BE REQUIRED FOR MANDATORY REPLACEMENT OF NEOPRENE COVERED PINS. FEEL THIS SHOULD ONLY BE IMPOSED ON THE IN	DIVIDUAL ITEM. THE PLASTIC COATING HARDENED AND CRACKED AWAY. THIS CAUSED ABNORMAL PLAY IN THE HINGE RESULTING IN POSS	IBLE FLUTTER OR DAMAGE TO THE AILERON.			1	L	7	2 	3O				A7SO 					 
1995042100490	19950421	00490	SO 	1995	4	21	95ZZZX1882 	1	19950310	G	5711	4019016	SPAR 			PIPER 	PA31 	PA31310 	7103103	SO 										LT WING	CRACKED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	59984	7267 				317512042				DURING COMPLIANCE WITH PIPER SB 974, LT SPAR FOUND CRACKED IN AREA NORMALLY CONCEALED BEHIND ORIGINAL INBOARD HINGE BRAC	KET. CRACK WAS VISIBLE .50 INCH WITHOUT DYE CHECK.					1	L	7	1 	3O			RT	A20SO 					 
1995042100491	19950421	00491	CE 	1995	4	21	95ZZZX1883 	1	19950315	G	2842	CB7740168	TRANSMITTER 			BEECH 	35 	P35BEECH 	1151530	CE 										INBD LT FUEL	ERRATIC 	B			CGHR	A				UNSCHED LANDING 				E	Y		VIBRATION/BUFFET 	ENGINE STOPPAGE 		CR	CRUISE 	1			GL	03	1567S					D6993				OWNER WAS VFR AT 5,500 FEET WHEN ENGINE RAN ROUGH AND THEN QUIT, HE SWITCHED FUEL SELECTOR VALVE TO RIGHT SIDE AND RAN 	ELECTRIC BOOST PUMP, BUT WAS UNABLE TO RESTART ENGINE. MADE FORCED LANDING INTO A BEAN FIELD WITH NO DAMAGE TO ACFT WIT	H LEFT TANK EMPTY. LEFT FUEL GAUGE INDICATED JUST BELOW THE QUARTER MARK. TROUBLESHOT, FOUND GAUGE STICKING AND INBOAR	D TRANSMITTER VERY ERRATIC. THERE WAS NO RECORD OF FUEL GAUGE OR TRANSMITTER HAVING BEEN CHANGED AND APPEARED ORIGINAL.	 REPLACED FUEL GAUGE AND INBOARD AND OUTBOARD TRANSMITTERS FOR LEFT SIDE. RECOMMEND OPERATORS OF OLDER VINTAGE ACFT PA	Y CLOSE ATTENTION TO FUEL BURN RATE AND A CLOCK. DO NOT DEPEND ENTIRELY ON FUEL GAUGE INDICATIONS.	1	L	7	1 	3O				3A15 					 
1995042100492	19950421	00492	CE 	1995	4	21	95ZZZX1884 	1	19950315	G	2841	5643645	GAUGE 			BEECH 	35 	P35BEECH 	1151530	CE 										INBD LT FUEL	STICKING 	B			CGHR	A				UNSCHED LANDING 				E	Y		VIBRATION/BUFFET 	ENGINE STOPPAGE 		CR	CRUISE 	1			GL	03	1567S					D6993				OWNER WAS VFR AT 5,500 FEET WHEN ENGINE RAN ROUGH AND THEN QUIT, HE SWITCHED FUEL SELECTOR VALVE TO RIGHT SIDE AND RAN 	ELECTRIC BOOST PUMP, BUT WAS UNABLE TO RESTART ENGINE. MADE FORCED LANDING INTO A BEAN FIELD WITH NO DAMAGE TO ACFT WIT	H LEFT TANK EMPTY. LEFT FUEL GAUGE INDICATED JUST BELOW THE QUARTER MARK. TROUBLESHOT, FOUND GAUGE STICKING AND INBOAR	D TRANSMITTER VERY ERRATIC. THERE WAS NO RECORD OF FUEL GAUGE OR TRANSMITTER HAVING BEEN CHANGED AND APPEARED ORIGINAL.	 REPLACED FUEL GAUGE AND INBOARD AND OUTBOARD TRANSMITTERS FOR LEFT SIDE. RECOMMEND OPERATORS OF OLDER VINTAGE ACFT PA	Y CLOSE ATTENTION TO FUEL BURN RATE AND A CLOCK. DO NOT DEPEND ENTIRELY ON FUEL GAUGE INDICATIONS.	1	L	7	1 	3O				3A15 					 
1995042100493	19950421	00493	CE 	1995	4	21	95ZZZX1885 	1	19950321	G	5741		ATTACH 			BEECH 	23 	C23 	1151242	CE 										LT WIND FWD	BOLT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	5226M	4870 				M2014				LEFT FORWARD WING ATTACH BOLT WAS FOUND LOOSE WHICH CAUSED ELONGATION OF THE CABIN BOLT HOLE. REPAIRED BY REPLACING ITE	MS NOTED IN BEECH SI 0042-031RII. FOUND DURING ANNUAL INSPECTION.					1	L	7	1 	3O				A1CE 					 
1995042100494	19950421	00494	GL 	1995	4	21	95ZZZX1886 	3	19950309	G	6110	A251352	BOLT 			CESSNA	150 	150L 	2071826	CE 						MCAULY	1A101	1A101DCM 	GL 	PROP MOUNT	TOO SHORT 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	11	6504G					15072004				INSPECTED TWO 'L' MODEL CESSNA 150'S, AND FOUND THE PROPELLER MOUNT BOLTS TO BE OF INSUFFICIENT LENGTH. REPLACEMENT WIT	H MCCAULEY BOLT KITS REMEDIED THIS PROBLEM.					1	H	7	1 	3O				3A19 		5	N	P918	 
1995042100495	19950421	00495	GL 	1995	4	21	95ZZZX1887 	3	19950309	G	6110	A251352	BOLT 			CESSNA	150 	150L 	2071826	CE 						MCAULY	1A101	1A101DCM 	GL 	PROP MOUNT	TOO SHORT 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	11						15075781				INSPECTED TWO 'L' MODEL CESSNA 150'S, AND FOUND THE PROPELLER MOUNT BOLTS TO BE OF INSUFFICIENT LENGTH. REPLACEMENT WIT	H MCCAULEY BOLT KITS REMEDIED THIS PROBLEM.					1	H	7	1 	3O				3A19 		5	N	P918	 
1995042100496	19950421	00496	EA 	1995	4	21	95ZZZX1888 	2	19950405	G	7414	10400313	IMPULSE COUPLER 	BENDIX 	S4LN21 	PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E2A 	41508	EA 					MAGNETO	SPRING BROKE 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11	7312F	1 			990356	2825231				INSTALLED IMPULSE COUPLER (NEW) ACCORDING TO MANUFACTURER'S INSTRUCTIONS. AFTER LESS THAN ONE HOUR'S TIME IN SERVICE, T	HE INTERNAL SPRING BROKE IN TWO PIECES. AFTER CONTACTING SUPPLIER OF PART, DISCOVERED THAT THEY HAD HAD AN IDENTICAL PA	RT RETURNED THAT DAY WITH SAME PROBLEM AND TIME IN SERVICE.				1	L	7	1 	3O	3	O		2A13 	E274				 
1995042100497	19950421	00497	SO 	1995	4	21	95ZZZX1889 	2	19950329	G	8520	539937	PAN 			CESSNA	182 	182 	2072702	CE 	CONT 	O470 	O470L 	17026	SO 					ENGINE OIL	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	6222A	6566 				33022	690249L4			AIRCRAFT HAD A GROUND STRIKE AND SUDDEN STOPPAGE. ENGINE AND PROP DISASSEMBLED, INSPECTED, AND REASSEMBLED. AFTER 19 H	OURS, OIL LEAK DEVELOPED FROM CRACK IN PAN. CRACK LOCATED 11 INCHES FROM FRONT OF PAN. BELIEVE THIS WAS CAUSED FROM PA	N STRIKING ENGINE MOUNT CROSS BRACE. CRACK EXTENDED IN 4 DIRECTIONS. AIRCRAFT LANDED WITH OUT DAMAGE TO ENGINE. REPLA	CED OIL PAN WITH NEW LIKE ITEM. THIS IS THE SECOND OIL PAN (NOT SAME ACFT) IN 4 MONTHS. THE FIRST WAS NOT DUE TO SUDDE	N STOPPAGE. DIFFERENT ACFT, SAME TYPE.		1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995042100498	19950421	00498	EA 	1995	4	21	95ZZZX1890 	2	19950404	G	8530	AL16740	VALVE 								LYC 	O360 	IO360C1C6 	41514	EA 					ENGINE EXHAUST	WORN 	B			YYBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03		160 					RL1811351A			ONE CYLINDER WAS REMOVED FOR LOW COMPRESSION. INSPECTION REVEALED THE EXHAUST VALVE BADLY WORN IN THE VALVE KEEPER AREA	. STEM DIAMETER WAS WORN FROM .336 INCH TO ,280 INCH. THE OTHER 3 CYLINDERS WERE INSPECTED AND FOUND TO HAVE WORN VALV	ES AS WELL. NO SIGNS OF IMPROPER ASSEMBLY WERE FOUND. THE VALVE HAS BEEN RETURNED TO AIRCRAFT TECHNOLOGY CORP. FOR ANA	LYSIS. SUSPECT THE VALVES MAY NOT HAVE BEEN PROPERLY HARDENED.								3	O			1E10				 
1995042100500	19950421	00500	SO 	1995	4	21	95ZZZX1892 	1	19950327	G	3221		SUPPORT ANGLE 			PIPER 	PA44 	PA44180 	7104402	SO 										NLG TRUNNION	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	2197Z	5328 				447995277				DURING 100-HOUR INSPECTION, FOUND BOTH LOWER NOSE TRUNNION SUPPORT ANGLES SEVERELY CRACKED AT BOLT ATTACH POINTS DUE TO 	CONTINUED FLIGHT SCHOOL USAGE. THE POSSIBILITY OF REPETITIVE HARD LANDINGS HAS CAUSED THIS PROBLEM.					1	L	7	2 	3O				A19S0 					 
1995042100501	19950421	00501	CE 	1995	4	21	95ZZZX1893 	1	19950324	G	7160	22540189	SHROUD ASSY 			CESSNA	182 	TR182 	2072735	CE 										CARBURETOR HEAT	CLIP FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	2625S	2421 	464 			R18201350				THE CARBURETOR HEAT SHROUD HAS 3 ATTACH CLIPS, DOG-LEG IN SHAPE, SPOT WELDED TO THE SHROUD, FOR ATTACHMENT TO THE EXHAUS	T VIA CLAMPS. ONE OF THE CLIPS BROKE OFF AND ENTERED THE DUCT AND THEN TO THE INLET OF THE TURBOCHARGER, AND CAUSED IMP	ELLER FAILURE. IN THE CARBURETOR HEAT MODE, THE TURBOCHARGER RECEIVES UNFILTERED, UNPROTECTED AIR. CESSNA ADVISES THER	E IS NO PROVISION FOR A SCREENED INLET TO CARBURETOR HEAT AS ON OTHER MODELS.			1	H	7	1 	3O				3A13 					 
1995042100502	19950421	00502	CE 	1995	4	21	95ZZZX1894 	1	19950313	G	2752	26111441	BRACKET 			CESSNA	208 	208B 	2073701	CE 										FLAP MOTOR	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	4687B					208B0167				PILOT REPORTED FLAP C/B TRIPPED DURING FLAP RETRACTION. DURING TROUBLESHOOTING, FOUND PN 2611144-1 WING FLAP MOTOR BRAC	KET BROKEN CAUSING THE MOTOR TRANSMISSION ASSY TO BIND. POSSIBLE CAUSES FOR THIS PROBLEM ARE (1) EXCESSIVE USE OF THE S	TBY FLAP SYSTEM, THERE ARE NO LIMIT SWITCHES OR EXTENDING FLAP AT TOO HIGH AIRSPEED.				1	H	7	1 	3T				A37CE 					 
1995042100503	19950421	00503	SO 	1995	4	21	95ZZZX1895 	1	19950329	G	2701	1689100	NEGATOR 			PIPER 	PA23 	PA23250 	7102308	SO 										CONTROL COLUMN	SPRING BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	5157Y	5250 				272196				AT ANNUAL INSPECTION FOUND CONTROL COLUMN NEGATOR SPRING BROKEN 6 INCHES FROM ATTACH BOLT. PART APPEARED TO HAVE BEEN B	ROKEN FOR MANY YEARS. ON THIS AIRCRAFT, IT SHOWED CONTROL COLUMN BINDING WHEN THE COLUMN IS PUSHED FORWARD.					1	L	7	2 	3O				1A10 					 
1995042100507	19950421	00507	CE 	1995	4	21	95ZZZX1896 	1	19950330	G	3242	5010398	LINING 	GOODYEARAERO	9540688 	BEECH 	18 	D18S 	1151004	CE 										RT BRAKE	FAILED 	D				O				OTHER 				K			FLUID LOSS 			LD	LANDING 	1			SO	19	354T				9D250	A91				LOG ENTRY: 'UPON LANDING IN MYEH, LOST RIGHT BRAKE. AFTER SLOWING AIRCRAFT DOWN TO A STOP, LOST LEFT BRAKE. SHUT BOTH	 ENGINES DOWN AND GOT TOWED TO RAMP'. FOUND RIGHT BRAKE LEAKING THROUGH THE CENTER PISTON DUE TO THE LINING CRACKING IN	 PIECES. DUE TO THAT FAILURE, LEFT BRAKE WAS INOPERATIVE BECAUSE THE FLUID WAS LOST. REPLACED RIGHT BRAKE ASSEMBLY. B	LEEDING AND BRAKE TEST PERFORMED. AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	3R				A765 					 
1995042100508	19950421	00508	CE 	1995	4	21	95ZZZX1897 	1	19950203	G	7921	637132	COOLER 			CESSNA	340 	340A 	2076405	CE 										ENGINE OIL	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	03	4121G		153 			340A0293				ENGINE INSTALLED AFTER OVERHAUL. UPON GROUND RUN, FOUND OIL COOLER LEAKING EXCESSIVELY. REMOVED AND INSTALLED SERVICEA	BLE COOLER. ENGINE STILL HAD SMALL OIL LEAK. AFTER EXTENSIVE TROUBLESHOOTING AND SEVERAL ATTEMPTS OF RESEALING OIL PUM	P HOUSING, WHICH APPEARED TO BE THE CAUSE OF LEAK. FOUND SERVICEABLE OIL COOLER PREVIOUSLY INSTALLED TO BE CRACKED AT M	OUNT FLANGE BASE THROUGH AND AROUND MOUNT BOLT HOLE. INSTALLED NEW COOLER AND LEAK CHECK OKAY.			1	L	7	2 	3O				3A25 					 
1995042100509	19950421	00509	SO 	1995	4	21	95ZZZX1898 	2	19950405	G	7414		COIL 	SLICK 	4201 	CESSNA	150 	A150L 	2071828	CE 	CONT 	O200 	O200A 	17020	SO 					MAGNETO	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	6041J				8050405	A1500341	2310001R80			DURING A 100-HOUR INSPECTION, THE IGNITION COILS WERE REMOVED FROM THE MAGS AND WERE FOUND CRACKED. THE TOTAL TIME WAS 	UNDETERMINABLE DUE TO LOST LOG BOOKS, BUT AT LEAST 600 HOURS ARE VERIFIABLE. THIS IS A LONG PERIOD OF SERVICE AND SLICK	 HAS ADDRESSED THIS PROBLEM WITH SERVICE LETTERS, BUT WITH NO AD'S, IT IS NOT MANDATORY TO REMOVE COILS FROM SERVICE AND	 APPARENTLY THIS HAS BEEN THE CASE. TO HELP PREVENT THIS FROM BECOMING A COMPLETE ENGINE FAILURE, RECOMMEND COIL REMOVA	L DURING INSPECTION AND PRE-PURCHASE INSPECTIONS ON ALL AIRCRAFT.		1	H	7	1 	3O	3	O		3A19 	E252				 
1995042100510	19950421	00510	EA 	1995	4	21	95ZZZX1899 	2	19950405	G	7414		COIL 	SLICK 	4271 	CESSNA	177 	177 	2073704	CE 	LYC 	O320 	O320E2D 	41508	EA 					MAGNETO	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	29406	180 			89080358	17700866	L2123927A			THE MAGNETO COIL CRACKED CAUSING MAG TO FAIL. THIS REPORT IS IN CONJUNCTION WITH AN ADDITIONAL REPORT ON THE SAME AIRPL	ANE AT THE SAME TIME A DUAL MAG FAILURE OCCURRED ON LANDING ROLL OUT. INSPECTIONS ON THE NAGNETOS DO NOT REQUIRE REMOVA	L OF COIL TO SATISFY INPSECTION, BUT IT WOULD BE HIGHLY RECOMMENDABLE TO DO SO. SHOP HAS NOW FOUND 4 CRACKED SLICK COIL	S.			1	H	7	1 	3O	3	O	NT	A13CE 	E274				 
1995042100511	19950421	00511	EA 	1995	4	21	95ZZZX1900 	2	19950405	G	7414		COIL 	SLICK 	4250 	CESSNA	177 	177 	2073704	CE 	LYC 	O320 	O320E2D 	41508	EA 					MAGNETO	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	29406	300 			0080373R	1700866	L2123927A			THE MAGNETO COIL CRACKED ITS OUTER CASING. THERE DID NOT SEEM TO BE ANY EVIDENCE OF ABUSE, BUT THE LEFT MAGNETO ON THE 	SAME ENGINE FAILED BY CRACKING ALSO, AND, IT ONLY HAD 180 HOURS TIME IN SERVICE, AN ADDITIONAL MALFUNCTION AND DEFECT RE	PORT WILL BE FILED FOR IT. SUBMITTER RECOMMENDS ACTUALLY REMOVING COILS FROM THE MAGNETOS DURING ANY 100-HOUR OR ANNUAL	 INSPECTION TO DETECT CRACKS ON THE BOTTOM OF THE COILS.			1	H	7	1 	3O	3	O	NT	A13CE 	E274				 
1995042100512	19950421	00512	SO 	1995	4	21	95ZZZX1901 	2	19950405	G	7414		COIL 	SLICK 	4201 	CESSNA	150 	A150L 	2071828	CE 	CONT 	O200 	O200A 	17020	SO 					MAGNETO	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	6041J				8050218	A1500341	2310001R80			DURING A 100-HOUR INSPECTION, COILS FOUND CRACKED IN THE MAGS. SLICK MFG COMPANY HAS ADDRESSED THE PROBLEM WITH SERVICE	 LETTERS, BUT THERE ARE NO AD'S ADDRESSING THESE COILS WHICH ALLOWS OWNERS THE LEEWAY TO RESIST REPLACING THEM. SUBMITT	ER SUGGESTS THE BEST WAY OF PREVENTING THIS PROBLEM IS COIL REMOVAL INSPECTIONS DURING 100-HOUR OR ANNUALS AND DURING PR	E-PURCHASE INSPECTIONS WHEN BUYING OR SELLING AIRCRAFT.			1	H	7	1 	3O	3	O		3A19 	E252				 
1995042100513	19950421	00513	SO 	1995	4	21	95ZZZX1902 	1	19950322	G	2810		VENT HOSE 			PIPER 	PA28 	PA28140 	7102802	SO 										FUEL TANK	DETERIORATED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	07	8792N	3100 				2825633				AT ANNUAL INSPECTION, FUEL STAINS NOTED ON BOTTOM OF WING. INVESTIGATION REVEALED DETERIORATED CONDITION OF FUEL VENT L	INE HOSES. HOSES CRUMBLED AT THE TOUCH. AUTO FUEL NOT A FACTOR. AIRCRAFT STORED OUTSIDE (TIE-DOWN). NO EVIDENCE OF H	AVING BEEN REPLACED, ORIGINAL EQUIPMENT. SUBMITTER RECOMMENDATION: ANY TANK NOT INSPECTED IN THE LAST 10 YEARS SHOULD 	BE REMOVED AND VENT LINE HOSES REPLACED.			1	L	7	1 	3O				2A13 					 
1995042100514	19950421	00514	SO 	1995	4	21	95ZZZX1903 	2	19950301	G	7322		NOZZLE 	FACET 	MA3SPA 	CESSNA	150 	150J 	2071820	CE 	CONT 	O200 	O200A 	17020	SO 					CARB DISCHARGE	NOT COMPATIBLE 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	01	61184				BE2420609	15020869	251274A48			ONE-PIECE VENTURI, NOT COMPATIBLE WITH ORIGINAL DISCHARGE NOZZLE. SHOULD BE MANDATORY TO CHANGE DISCHARGE NOZZLE AT THE	 TIME OF ONE-PIECE VENTURI IS INSTALLED. OLD NOZZLE NOT COMPATIBLE WITH NEW VENTURI.					1	H	7	1 	3O	3	O		3A19 	E252				 
1995042100515	19950421	00515	SO 	1995	4	21	95ZZZX1904 	1	19950306	G	3250	7641105	HORN ASSY 			PIPER 	PA28 	PA28161 	7102803	SO 										NLG STEERING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	8137Q	4912 				288016179				ANNUAL INSPECTION NOTED SMALL CRACKS AT WELD OF NLG STEERING HORN. SUBMITTER STATED CAUSE UNKNOWN, BUT SUSPECT EITHER T	AXI ON ICE AND RUTS OR POSSIBLY NOSE WHEEL SHIMMY.					1	L	7	1 	3O				2A13 					 
1995042100516	19950421	00516	CE 	1995	4	21	95ZZZX1906 	1	19950321	G	3230	0028200113	IDLER ARM 			BEECH 	33 	F33A 	1151425	CE 										NLG RETRACT	CRACKED 	B			AMYR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	36XZ	1938 				CE1310				DURING NOSE GEAR RIGGING, FOUND NOSE GEAR RETRACT IDLER ARM CRACKED AT THE INBOARD SIDE OF THE RIGHT ATTACHMENT EAR. TH	E LOCATION OF THIS PART IS ON THE RIGHT INSIDE NOSE GEAR WALL AT APPROXIMATELY STA 54. THIS AREA IS COVERED BY NOSE RET	RACT ROD BOOT AND ALUM COVER WHICH IS IMPOSSIBLE TO INSPECT UNLESS BOOT IS BEING REPLACED OR COVER IS REMOVED. THIS IS 	THE SECOND SUCH OCCURRENCE THAT HAS BEEN FOUND ON THE BONANZA SERIES AIRCRAFT. SUBMITTER RECOMMENDS THIS BE THOROUGHLY 	INSPECTED DURING ANNUAL INSPECTIONS.		1	L	7	1 	3O				3A15 					 
1995042100517	19950421	00517	CE 	1995	4	21	95ZZZX1907 	1	19950322	G	5510	17320103	BRACKET 			CESSNA	177 	177RG 	2073709	CE 										STAB BAL ARM WT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	51386	4719 				177RG1138				DURING ANNUAL INSPECTION, FOUND CRACK IN BEND RADIUS OF ONE FORWARD AND ONE AFT STABILATOR BALANCE ARM SUPPORT BRACKET O	N STABILATOR. RECOMMEND REPLACEMENT OF THESE WITH LATER STEEL BRACKETS, PN 1732063-1 AND DASH 2, AND 1732064-1, AND DAS	H 2 PER CESSNA SEB 89-1, REV 3.				1	H	7	1 	3O				A20CE 					 
1995042100518	19950421	00518	CE 	1995	4	21	95ZZZX1908 	1	19950322	G	5510	17320313	BRACKET 			CESSNA	177 	177RG 	2073709	CE 										STAB BAL ARM WT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	51386	4719 				177RG1138				DURING ANNUAL INSPECTION, FOUND CRACK IN BEND RADIUS OF ONE FORWARD AND ONE AFT STABILATOR BALANCE ARM SUPPORT BRACKET O	N STABILATOR. RECOMMEND REPLACEMENT OF THESE WITH LATER STEEL BRACKETS, PN 1732063-1 AND DASH 2, AND 1732064-1, AND DAS	H 2 PER CESSNA SEB 89-1, REV 3.				1	H	7	1 	3O				A20CE 					 
1995042100519	19950421	00519	CE 	1995	4	21	95ZZZX1909 	1	19950316	G	5521	14320108	RIB 			CESSNA	337 	337 	2075702	CE 										ELEV END RIB LT	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	2284X	1060 				3370184				END RIB WHERE PN 1532009-203 ATTACHES, BADLY CORRODED AND CRACKED. ELEVATOR ACTUATING ARM HAS STEEL BRACKET, WAS BADLY 	RUSTED AND RIVETS SHEARED.					1	H	7	2 	3O				A6CE 					 
1995042100520	19950421	00520	EA 	1995	4	21	95ZZZX1910 	2	19950328	G	8550	CH48103	FILTER 	CHAMPION 		PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	IO540C4B5 	41532	EA 					ENGINE OIL	DEFECTIVE 	B			EVGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	2FOR	10 				273827	L935548			WHEN REMOVING OIL FILTER AFTER APPROXIMATELY 10 HOURS OF SERVICE CHANGE, DISCOVERED THE OIL FILTER CAN PORTION WAS SPINN	ING/ROTATING IN THE BASE PLATE. NO LEAKS HAD OCCURRED DURING SERVICE.					1	L	7	2 	3O	3	O		1A10 	1E4				 
1995042100521	19950421	00521	NE 	1995	4	21	95ZZZX1911 	2	19950211	G	7261		HOUSING 			CESSNA	208 	208 	2073702	CE 	PWA 	PT6 	PT6A114 	52043	NE 					SCAVENGE PUMP	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	9825F	1035 				20800228	17474			SCAVENGE PUMP HOUSING WAS CRACKED ON THE 2 TOP HOLES WHERE THE SCAVENGE PUMP BOLTS UP TO THE ACCESSORY CASE ON THE BACK 	OF THE ENGINE. THE LOWER 2 INNER HOUSING BOLTS, NUTS, AND RETAINING LOCKWASHERS WERE OFF ON THE LEFT AND ONE-HALF OFF O	N THE RIGHT. THE VIBRATION FROM THE LOOSE LOWER 2 BOLTS PUT PRESSURE ON THE 2 TOP BOLTS CAUSING THE HOUSING TO CRACK.				1	H	7	1 	3T	3	T	NT	A37CE 	E4EA				 
1995042100522	19950421	00522	GL 	1995	4	21	95ZZZX1912 	2	19950130	G	7230		BLADE 			GOVT 	N22 	N22S 	3880103	WP 	ALLSN 	250B 	250B17 	03012	GL 					COMPRESSOR	SEPARATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	6305U					N22S160	CAE880492			AFTER REGULAR DAILY RUN AND COMPRESSOR RINSE, AIRCRAFT SHUT DOWN WITH NO PROBLEMS. FOUND AFTER SHUT DOWN, COMPRESSOR BL	ADES (STATIONARY) HAD SEPARATED FROM CASE AND FROZE COMPRESSOR.					1	H	7	2 	3T	3	T	RT	A7PC 	E10CE				 
1995042100746	19950421	00746	SW 	1995	4	21	95ZZZX1927 	1	19950327	G	5320	205032815127	PANEL 		212030100133	BELL 	412 	412 	1182202	SW 										BAGG COMP ROOF	SEPARATION 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	396AL	6360 			33164	33169				DURING MAJOR INSPECTION, FOUND PANEL OF BAGGAGE COMPARTMENT ROOF SEPARATED BEYOND LIMITS. STA 101 (AFT SEAM ON PANEL) I	S A HIGHLY STRESSED AREA. SINCE THE ADDITION OF OUTSIDE DOUBLERS (ASB 412-90-49) THIS SEEMS TO BE A MORE COMMON PROBLEM	.				1	G	7	2 	4U				H4SW 					 
1995042800194	19950428	00194	SW 	1995	4	28	95ZZZX1971 	1	19950303	G	3233	940024901	WORM GEAR 	DUKES 	321400 	MOONEY	M20 	M20F 	5870214	SW 										MLG ACTUATOR	RUSTED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	07	6423Q				631	670502				NEW ACTUATOR WORM GEAR RECEIVED A PART OF MOONEY KIT 940024-501 FROM MOONEY AIRCRAFT CO. IN KERRVILLE, TEXAS; THIS IS TH	E SECOND KIT RECEIVED WITH AN UNSERVICEABLE WORM GEAR. FIRST KIT RETURNED TO SOUTHWEST TEXAS AVIATION AT SAN MARCOS, TX	. SECOND KIT PURCHASED FROM MOONEY, BUT RUST AND PITS ON SURFACE SHOW LACK OF ENVIRONMENTAL CONTROL IN STORAGE AREA.				1	L	7	1 	3O				2A3 					 
1995042800195	19950428	00195	SO 	1995	4	28	95ZZZX1972 	1	19950410	G	7810	3122605	PIPE 			PIPER 	PA23 	PA23250 	7102308	SO 										EXH SLIP JOINT	SEPARATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	62647	2724 				277654112				EXHAUST PIPES SEPARATED AT FRONT SLIP JOINT AND BURNED SHROUD AND ALSO DUCT AND COWL. NO PROBLEMS (CRACKS, ETC.) WITH T	HE EXHAUST.					1	L	7	2 	3O				1A10 					 
1995042800196	19950428	00196	SO 	1995	4	28	95ZZZX1973 	1	19950410	G	7810	3288008	PIPE 			PIPER 	PA23 	PA23250 	7102308	SO 										EXH SLIP JOINT	SEPARATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	62647	2724 				277654112				EXHAUST PIPES SEPARATED AT FRONT SLIP JOINT AND BURNED SHROUD AND ALSO DUCT AND COWL. NO PROBLEMS (CRACKS, ETC.) WITH T	HE EXHAUST.					1	L	7	2 	3O				1A10 					 
1995042800197	19950428	00197	EA 	1995	4	28	95ZZZX1974 	2	19950328	G	8550	LW15550	GEROTOR 			PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	TIO540C1A 	41532	EA 					TURBO SCAVANGE	SEIZED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	54748		6 			277554062	L364561A			TURBO SCAVANGE PUMP FAILED. APPEARS THAT THE ROTOR CRACKED WHICH, IN TURN, SHEARED AN ANTI-ROTATION PIN IN THE PUMP HOU	SING IN WHICH THE GEROTOR TURNS. THE HOUSINGS WERE DAMAGED BY THIS PUMP HOUSING SPINNING, THE TURBO WAS NOT SCAVANGED W	ITH OIL LEADING TO THE LOSS OVERBOARD OF THE ENGINE OIL.				1	L	7	2 	3O	3	O		1A10 	E14EA				 
1995042800198	19950428	00198	SO 	1995	4	28	95ZZZX1975 	1	19950409	G	5741	6244803	FITTING 		6226303 	PIPER 	PA28 	PA28140 	7102802	SO 										RT FS 128.737	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	3959X	2912 				287625001				DURING ANNUAL INSPECTION, THE AFT WING SPAR STEEL ATTACHMENT FITTINGS INSIDE THE FUSELAGE WERE FOUND SEVERELY RUSTED, WA	S ABLE TO BREAK OFF FLAKES OF RUST WITH A FINGERNAIL. THIS AREA SEEMS PRONE TO TRAP WATER. THE INSULATION HAD BEEN PRE	VIOUSLY REMOVED FROM THIS AREA. SUBMITTER RECOMMENDS A SMALL DRAIN HOLE TO REMOVE WATER.				1	L	7	1 	3O				2A13 					 
1995042800199	19950428	00199	SO 	1995	4	28	95ZZZX1976 	1	19950409	G	5741	6244802	FITTING 		6226303 	PIPER 	PA28 	PA28140 	7102802	SO 										LT FS 128.737	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	3959X	2912 				287625001				DURING ANNUAL INSPECTION, THE AFT WING SPAR STEEL ATTACHMENT FITTINGS INSIDE THE FUSELAGE WERE FOUND SEVERELY RUSTED WAS	 ABLE TO BREAK OFF FLAKES OF RUST WITH A FINGERNAIL. THIS AREA SEEMS PRONE TO TRAP WATER. THE INSULATION HAD BEEN PREV	IOUSLY REMOVED FROM THIS AREA. SUBMITTER RECOMMENDS A SMALL DRAIN HOLE TO REMOVE WATER.				1	L	7	1 	3O				2A13 					 
1995042800200	19950428	00200	SO 	1995	4	28	95ZZZX1977 	1	19950404	G	7922	75944	VALVE 			PIPER 	PA28 	PA28151 	7102805	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	4326F				59410	287715018				COMPLYING WITH LYCOMING SB 518A - CRIMP NUT WAS FOUND TO BE LOOSE AND NOT MEET CRIMP DEPTH SPEC.						1	L	7	1 	3O				2A13 					 
1995042800202	19950428	00202	CE 	1995	4	28	95ZZZX1979 	1	19950404	G	8011	902018	SEAL 		MZ4214 	CESSNA	150 	150 	2071802	CE 										STARTER	MISINSTALLED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	09	7671U	1106 			6M000085	15077797				SLOW OIL LEAK DEVELOPED ON REAR ACCESSORY CASE. FOUND OIL COMING FROM STARTER BETWEEN MOUNTING PLATE AND FRAME. REMOVE	D STARTER AND DISCOVERED OIL SEAL INSTALLED BACKWARDS. REPLACED STARTER WITH SERVICEABLE UNIT. REMIND MECHANIC'S GARLO	CK SEALS SHOULD HAVE OPEN END FACING OIL PRESSURE.				1	H	7	1 	3O			NT	3A19 					 
1995042800203	19950428	00203		1995	4	28	95ZZZX1980 	4	19950404	G	6113	D4247	BULKHEAD 			BEECH 	23 	C23 	1151242	CE 										SPINNER	CRACKED 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	63745	626 				M2361				DURING PROPELLER REMOVAL, FOUND CRACKS AT EACH BOLT HOLE. SUBMITTER SUGGESTS CRACKS DUE TO POOR DESIGN AND POOR MANUFAC	TURING. THIS REPAIR STATION HAS REPLACED NUMEROUS D4247 BULKHEADS AT LOW INSTALL TIMES.					1	L	7	1 	3O				A1CE 					 
1995042800204	19950428	00204	SO 	1995	4	28	95ZZZX1981 	1	19950401	G	5412		FIREWALL 			PIPER 	PA24 	PA24260 	7102406	SO 										ENG AFT AREA	HAZARDOUS 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	9468P					244978				DURING A SCHEDULED INSPECTION, NOTED FIREWALL AND SCAT TUBE SLEEVES ARE MADE FORM ASBESTOS. IT IS SUGGESTED THAT EXTREM	E CARE BE TAKEN, NOT TO DISTURB THIS MATERIAL, WHILE WORKING IN THE VICINITY OF THE ENGINE REAR CASE.					1	L	7	1 	3O				1A15 					 
1995042800205	19950428	00205	CE 	1995	4	28	95ZZZX1982 	1	19950404	G	7922	53E19600	VALVE 			CESSNA	150 	152 	2071835	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	65473				50133	15281573				COMPLYING WITH LYCOMING SB 518A, CRIMP NUT WAS FOUND TO BE LOOSE AND NOT MEET CRIMP DEPTH SPEC.						1	H	7	1 	3O			NT	3A19 					 
1995042800206	19950428	00206	EU 	1995	4	28	95ZZZX1983 	1	19950404	G	7160	T6765103	AIR BOX 			SLNSBY	T67 	T67M260 	8323006	EU 										INTAKE	HINGE WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3010H	328 				920631				AFTER INSPECTION OF ENGINE AIR BOX, THE REAR FLAPPER HINGED DOOR WAS FOUND LOOSE. THE HINGE HAD WORN AND WORKED ITSELF 	LOOSE.					1	L	7	1 	3O			NT	A73EU 					 
1995042800207	19950428	00207	EU 	1995	4	28	95ZZZX1984 	1	19950404	G	7160	T67650103	AIR BOX 			SLNSBY	T67 	T67M260 	8323006	EU 										INTAKE	HINGE WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3022C	364 				920633				AFTER INPSECTION OF THE ENGINE AIR BOX, REAR FLAPPER HINGED DOOR FOUND LOOSE. THE HINGE HAD WORN AND WORKED ITSELF LOOS	E.					1	L	7	1 	3O			NT	A73EU 					 
1995042800208	19950428	00208		1995	4	28	95ZZZX1985 	4	19950308	G	3416	10145011952	ALTIMETER 	AEROSONIC 		BEECH 	200 	B200 	1152922	CE 										COCKPIT	MALFUNCTION 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	122LC				W10792	BB1490				UNIT 40 FEET OFF AT ZERO, 100 FEET OFF AT 20,000 FEET. ENCODING OUTPUT OUT OF SPECS.						1	L	7	2 	4T				A24CE 					 
1995042800209	19950428	00209	NE 	1995	4	28	95ZZZX1986 	2	19950328	G	7320	800816	CASE 								PWA 	JT8 	JT8D219 	52053	NE 					8TH STAGE STATOR	CRACKED 	B	P		SQ5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03					TF6682		718144			EIGHTH STAGE STATOR SUPPORT SHELF CRACKED. CRACK APPEARS TO HAVE STARTED AT A SLOT. CRACK CAUSED SOME LIBERATION OF MA	TERIAL. FOR SUSPECT CAUSE SEE SB 6117. CASE WAS REMOVED AND IS IN THE PROCESS OF HAVING SB 6117 INCORPORATED.										4	F			E9NE				 
1995042800210	19950428	00210	CE 	1995	4	28	95ZZZX1987 	1	19950330	G	5320	265313457005	SUPPORT SHELF 			RKWELL	NA265 	NA26540 	6402608	CE 										FS 457.406	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	310NT					282077				DURING INSPECTION, FOUND SUPPORT SHELF ON AFT SIDE OF BULKHEAD AT CANTED FS 457.406 CRACKED IN 3 PLACES AND BULGED DUE T	O INTERNAL EXFOLIATION CORROSION. SHELF IS TO BE REMOVED AND REPLACED. RECOMMEND CLOSE INSPECTION OF THIS AREA DURING 	SCHEDULED INSPECTIONS, SINCE ELEVATOR AND RUDDER BELLCRANKS ARE MOUNTED ON THE FORWARD SIDE OF THE BULKHEAD AT FUSELAGE 	CANTED STA 457.406. HRS AIRCRAFT TT: 14,158.7. LANDINGS: 9,351.			2	L	7	2 	4J				A2WE 					 
1995042800211	19950428	00211	WP 	1995	4	28	95ZZZX1988 	2	19950407	G	7261	30714191	GASKET 			LEAR 	35 	35A 	5170602	CE 	GARRTT	TFE731	TFE73122B 	01518	WP 					NR 2 ENG AFT BRG	LEAKING 	B	S		WC7R	E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	25	66LJ	150 				401	P89128			PILOT HAD LOW OIL PRESSURE IN-FLIGHT ON NR 2 ENGINE, SO SHUT ENGINE DOWN. ENGINE HAD 1 QUART OF OIL LEFT IN TANK. FOUN	D GASKET LEAKING AT OIL PRESSURE LINE TO REAR BEARING. INSTALLED NEW GASKET, PN 3071419-1, ADDED 4 QUARTS OIL TO ENGINE	. RUN-UP AND LEAK CHECK GOOD.				2	L	7	2 	4F	4	F		A10CE 	E6WE				 
1995042800212	19950428	00212	EU 	1995	4	28	95ZZZX1989 	1	19950405	G	7830	MS245941	SWITCH 			AMD 	FALC50	FALCON50MYST	2730106	EU 										T/R TOP SIDE RT	OUT OF ADJUST 	B			YL1R	O				OTHER 				N			FALSE WARNING 			CR	CRUISE 	1			SW	11	450K	3897 				186				T/R LIGHT CAME ON IN-FLIGHT. SWITCHES OUT OF ADJUSTMENT GIVING AN INDICATION LIGHT TO COCKPIT. T/R WAS STOWED. SWITCH	ES 36K AND 37K WERE ADJUSTED PER MM AND SYSTEM F/T OKAY. SUSPECT CAUSE: SWITCHES IN A HIGH HEAT AREA AND OVER TIME CAN	 GO OUT OF ADJUSTMENT.				2	L	7	3 	4F				A46EU 					 
1995042800213	19950428	00213	EU 	1995	4	28	95ZZZX1990 	1	19950405	G	7830	MS245941	SWITCH 		F50B583ABD 	AMD 	FALC50	FALCON50MYST	2730106	EU 										T/R TOP SIDE LT	OUT OF ADJUST 	B			YL1R	O				OTHER 				N			FALSE WARNING 			CR	CRUISE 	1			SW	11	450K	3897 				186				T/R LIGHT CAME ON IN-FLIGHT. SWITCHES OUT OF ADJUSTMENT GIVING AN INDICATION LIGHT TO COCKPIT. T/R WAS STOWED. SWITCH	ES 36K AND 37K WERE ADJUSTED PER MM AND SYSTEM F/T OKAY. SUSPECT CAUSE: SWITCHES IN A HIGH HEAT AREA AND OVER TIME CAN	 GO OUT OF ADJUSTMENT.				2	L	7	3 	4F				A46EU 					 
1995042800214	19950428	00214	NE 	1995	4	28	95ZZZX1991 	2	19950309	G	7321	78360014068	EEC 	HAMSTD 		BOEING	757 	757222 	1384956	NM 	PWA 	2037 	PW2037 		NE 					SOLDER JOINTS	DEFECTIVE 	B			OHER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	560UA	16340			20370410	26660				EEC EXHIBITS FRACTURED SOLDER JOINTS: CHAN 'A' PROCESSOR BD. LOCATION U427, PIN NR 15 (UVPROM) BD ASSY 781336-9-068, S	N 89011490. CHAN 'B' PROCESSOR BD. LOCATION U427, PIN NR 14 (UVPROM) BD ASSY 781338-9-068, SN 89012339. CAUSE OF FRAC	TURING IS UNKNOWN AT THIS TIME. SUSPECT OXIDIZED CHIP LEADS.				2	L	7	2 	4F	4	F	RT	A2NM 	E17NE				 
1995042800215	19950428	00215	WP 	1995	4	28	95ZZZX1992 	2	19950405	G	7250	31038391	SEAL 		31070852 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		6751 			0233151120		P70059			DURING CAM INSPECTION, FOUND SEAL CRACKED 3 PLACES. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASE	D PRESSURE AGAINST 1ST STAGE ROTOR. THIS INCREASED PRESSURE RESULTS IN CRACKING OF THE SEAL EDGE DIAMETER. SUGGEST ALL	IED SIGNAL ENGINEERING REVIEW PART/INSTALLATION PROBLEM. CSN, 9,014.									4	T			E4WE				 
1995042800216	19950428	00216	NE 	1995	4	28	95ZZZX1993 	2	19950317	G	7250	634E583P3	WHEEL 								GE 	CJ610 	CJ6106 	30006	NE 					TURB 1ST STAGE	BOGUS PART 	B	L		IY2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15							251562A			THIS WHEEL WAS FOUND IN A COMMERICAL ENGINE. THE PART NUMBER IS NOT RECOGNIZED BY GENERAL ELECTRIC.											4	J			1E16				 
1995042800217	19950428	00217	EA 	1995	4	28	95ZZZX1994 	2	19950406	G	7310	3032090	LINE 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					PRIMARY FUEL	CRACKED 	D				C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			R			PARTIAL RPM/PWR LOSS 			TO	TAKEOFF 	1			SO	11	119CJ					UC19	32250			PRIMARY ENGINE FUEL LINE CRACKED AT FERRULE REINFORCEMENT RESULTNG IN LOSS OF SUFFICIENT FUEL PRESSURE TO MAKE REQUIRED 	POWER. TAKEOFF WAS ABORTED. SUSPECT CAUSED BY FATIGUE FROM ENVIRONMENT.					2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995042800594	19950428	00594	CE 	1995	4	28	95ZZZX2030 	1	19950331	G	7110	45A350371	COWL 			BEECH 	MU300 	400BEECH 		CE 										RT ENGINE	DEPARTED 	B	S	A	JY1R	O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			SW	09	777ND	91 				RK71				THE CREW & FLIGHT SAFETY, PRESENT FOR TRAINING AND ACCEPTANCE FLIGHT, STATE THE COWLINGS WERE PROPERLY ATTACHED AND SECU	RED FOR FLIGHT. DURING FLIGHT, CREW AND PASSENGERS WERE UNAWARE THE RIGHT ENGINE LOWER INBOARD AND OUTBOARD COWLING SECT	IONS SEPARATED FROM AND DEPARTED THE AIRCRAFT. SUBMITTER SUGGESTS ADDING STIFFENERS TO DOORS AND INCREASING DIAMETER OF	 THE FASTENERS TO PROVIDE A MORE POSITIVE INDICATION OF PROPER ENGAGEMENT AND INTRODUCE A METHOD OF MECHANICAL ATTACHMEN	T OF THE LOWER INBOARD COWL SECTION TO THE PYLON.		2	H	7	2 	4F			RT	A16SW 					 
1995042800595	19950428	00595	CE 	1995	4	28	95ZZZX2031 	1	19950331	G	7110	45A3517622	COWL 			BEECH 	MU300 	400BEECH 		CE 										RT ENGINE	DEPARTED 	B		A	JY1R	O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			SW	09	777ND	91 				RK71				THE CREW & FLIGHT SAFETY, PRESENT FOR TRAINING AND ACCEPTANCE FLIGHT, STATE THE COWLINGS WERE PROPERLY ATTACHED AND SECU	RED FOR FLIGHT. DURING FLIGHT, CREW AND PASSENGERS WERE UNAWARE THE RIGHT ENGINE LOWER INBOARD AND OUTBOARD COWLING SECT	IONS SEPARATED FROM AND DEPARTED THE AIRCRAFT. SUBMITTER SUGGESTS ADDING STIFFENERS TO DOORS AND INCREASING DIAMETER OF	 THE FASTENERS TO PROVIDE A MORE POSITIVE INDICATION OF PROPER ENGAGEMENT AND INTRODUCE A METHOD OF MECHANICAL ATTACHMEN	T OF THE LOWER INBOARD COWL SECTION TO THE PYLON.		2	H	7	2 	4F			RT	A16SW 					 
1995042800596	19950428	00596	CE 	1995	4	28	95ZZZX2032 	1	19950227	G	5210	241127657557	BRACKET 		241125014 	LEAR 	35 	35A 	5170602	CE 										LOWER ENTRY DR	CRACKED 	B			DELR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	35AW				1135	233				FOUND CRACK DURING THE 300-HOUR INSPECTION ON AIRCRAFT. REPAIRED CRACK AREA. SUBMITTER RECOMMENDS TO DUPLICATE SUPPORT	 CABLE. ADD TO FORWARD SIDE OF LOWER DOOR HALF. ACTT 5057.4. LANDINGS, 3824.					2	L	7	2 	4F				A10CE 					 
1995042800597	19950428	00597	CE 	1995	4	28	95ZZZX2033 	1	19950329	G	3320	8677813	CONNECTOR ASSY 			BEECH 	B300 	B300 	1159232	CE 										CABIN LIGHTS	BURNED 	B		A	VIBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	97DR	150 				FL4				CREW REPORTED RIGHT CABIN OVERHEAD LIGHTS INOPERATIVE. INVESTIGATION REVEALED THE PLUG FOR RIGHT CABIN LIGHTS HAD OVERH	EATED AND BURNED CAUSING A FIRE HAZARD IN THE CABIN OVERHEAD AREA. THESE LIGHTS ARE AC POWERED LIGHTS. CONNECTOR PN 86	77813 AND PN 8677793.				2	L	7	2 	4T			RT	A24CE 					 
1995042800598	19950428	00598	CE 	1995	4	28	95ZZZX2034 	1	19950405	G	5400	251921617	GASKET 			LEAR 	25 	25D 	5170514	CE 										PYLON	BROKEN 	B		A	IY2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	837CS					351				INSPECTION FOUND HOT AIR GASKET ON PYLON BROKEN IN TWO PIECES. POSSIBLE FIRE HAZARD DUE TO HYDRAULIC LINES NEAR LEAKS I	NSIDE PYLON. SUBMITTER SUGGESTS THERE IS NO TIME CHANGE ON GASKETS. AIRFRAME TOTAL TIME, 2992.9. AIRFRAME TOTAL LANDI	NGS, 2961.				2	L	7	2 	4J				A10CE 					 
1995042800599	19950428	00599	CE 	1995	4	28	95ZZZX2035 	1	19950327	G	5320	521304027	WEB 			CESSNA	441 	441 	2076020	CE 										NLG WHEELWELL	HOLES ELONGATED 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	441K	4442 				4410093				THE NOSE GEAR DRAG BRACE ATTACH BRACKET ATTACH BOLTS WORK LOOSE WITH TIME DUE TO FORE AND AFT LOADS PLACED ON NOSE GEAR 	DURING TOWING. AFTER BOLTS WORK LOOSE, THEY ELONGATE THE WHEELWELL ATTACH AREAS WHERE THE BOLTS GO THROUGH THE SKIN OF 	THE WHEELWELL. THE WHEELWELL SKIN IS ONLY .040 INCH THICK. SUBMITTER RECOMMENDS A .063 INCH DOUBLER INSTALLED TO STIFF	ENER AREA AND PREVENT BOLT HOLE ELONGATION. THIS CONDITION HAS BEEN FOUND ON NUMEROUS 441 CONQUEST II AIRCRAFT.			1	L	7	2 	3T			RT	A28CE 					 
1995042800600	19950428	00600	SO 	1995	4	28	95ZZZX2036 	1	19950314	G	2150	646450	BRACKET 			PIPER 	PA46 	PA46310P 	7104605	SO 										AIR COND PULLEY	FAILED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	375CS	1403 				468508026				PILOT REPORTED AIR CONDITIONER INOPERATIVE. UPON INVESTIGATION, FOUND PULLEY SEVERED FROM MOUNTING BRACKET AND BEARING 	DISINTEGRATED. THIS WAS MOST LIKELY CAUSED BY BEARING SEIZING IN THE PULLEY CAUSING THE FORCES FROM THE DRIVE BELT TO S	HEAR THE SUPPORT BRACKET. RECOMMEND BELT REMOVAL AND INSPECTION OF THE PULLEY BEARING EVERY 1000 HOURS SERVICE.				1	L	7	1 	3O				A25SO 					 
1995042800601	19950428	00601	SO 	1995	4	28	95ZZZX2037 	1	19950415	G	3213	8360607	TRUNNION 			PIPER 	PA46 	PA46310P 	7104605	SO 										NLG	CRACKED 	B	S	A	HX1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	4360U	2557 				468408049				DURING A ROUTINE INSPECTION, A CRACK WAS DETECTED IN THE NOSE GEAR TRUNNION IN THE TUBE PORTION OF THE TRUNNION NEAR THE	 PIVOT ATTACH LUG. NEW TRUNNION INSTALLED IS BEEFIER IN AREA OF CRACK.					1	L	7	1 	3O				A25SO 					 
1995042800602	19950428	00602	SW 	1995	4	28	95ZZZX2038 	1	19950401	G	2730	730006000	CONTROL LINK 			MOONEY	M20 	M20J 	5870219	SW 										RT AILERON	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	5783D	2687 				241517				PILOT SQUAWKED AILERONS FELT FUNNY. INVESTIGATION FOUND THE RIGHT AILERON COULD TRAVEL FURTHER THAN THE STOP. REMOVAL 	OF THE BELLY PAN REVEALED THE RIGHT CONTROL ROD WAS CRACKED IN HALF JUST OUTBOARD OF THE BELLCRANK FOR THE AILERONS. SU	SPECT CAUSE IS (AN INADQUATE CONTROL LOCK AND AGGRESSIVE PRE-FLIGHT MOVEMENT OF THE CONTROLS).				1	L	7	1 	3O				2A3 					 
1995042800603	19950428	00603	CE 	1995	4	28	95ZZZX2039 	1	19950224	G	3340		BUSS 			CESSNA	182 	182P 	2075816	CE 										INST PANEL	MISWIRED 	D	L			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	05	1262M	1552 				18264265				DURING TROUBLESHOOTING A FLASHING BEACON PROBLEM, FOUND BEACON WIRED TO AVIONICS SPLIT BUSS AND WOULD NOT WORK UNTIL AVI	ONICS MASTER WAS TURNED ON (2ND AIRCRAFT IN 1 MONTH). THIS SITUATION COULD BE A PROBLEM IF THE AIRCRAFT WAS IFR AND LOS	E THE POWER RELAY OR AVIONICS MASTER SWITCH, ALL POWER TO THE AVIONICS BOSS WOULD BE LOST.				1	H	7	1 	3O			NT	TA13 					 
1995042800604	19950428	00604	SO 	1995	4	28	95ZZZX2040 	1	19950324	G	5730	6206102	SKIN 			PIPER 	PA28 	PA28181 	7102807	SO 										WING WALK	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	2935V	2994 				287990566				LOWER WING SKIN FOUND CRACKED AT ANNUAL INSP. (PN 62086-01). UPON DRILLING TO PREPARE A SURFACE PATCH, ABNORMAL SOUND O	F SHEETMETAL BREAKING WAS OBSERVED. FURTHER INSP REVEALED THE 2 STIFFENERS ATTACHED TO THIS LOWER SKIN WERE BADLY CRACK	ED AT WING BUTT AND OPPOSITE END. AFTER AN INSP PANEL WAS INSTALLED IN THIS AREA FOR ACCESS, TOP SKIN PN 62061-02 WING 	WALK SKIN WAS FOUND CRACKED. UPON REMOVAL OF THIS SKIN, CRACKS WERE BELIEVED TO BE DUE TO CORROSION. RECOMMEND EXTENSI	VE INSP IF CRACKS ARE FOUND.		1	L	7	1 	3O				2A13 					 
1995042800607	19950428	00607	SO 	1995	4	28	95ZZZX2043 	1	19950404	G	5553	406814	ANCHOR NUT 			PIPER 	PA28 	PA28RT201 	7102818	SO 										V-FIN FWD ATTACH	FAILED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	8085Z	5790 				28R7918260				DURING THE ANNUAL INSPECTION, RT FWD ATTACH BOLT FOR VERTICAL FIN FOUND LOOSE. BOLT REMOVED AND FND IN SERVICEABLE SHAP	E. REPLACED AND ATTEMPTED TO TORQUE TO SPECS. BOLT WOULD NOT TIGHTEN. FURTHER INSP REVEALED ANCHOR NUT SHATTERED. SU	BMITTER SUGGESTS THE NUT APPEARS TO BE TOO HARD AND IS BRITTLE. BOTH FRONT VERT FIN NUTS WERE REPLACED WITH NEW (LT SID	E SEEMED TO BE OKAY). VERT FIN WAS REASSEMBLED WITH NEW BOLTS AND TORQUED TO SPECS.			1	L	7	1 	3O				2A13 					 
1995042800608	19950428	00608	CE 	1995	4	28	95ZZZX2044 	1	19950412	G	3710	B906	HOSE 			CESSNA	182 	182R 	2072731	CE 										INSP PNL VAC SYS	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	09	5481E	772 				18268325				INSP FOUND VACUUM SYSTEM HOSE DETERIORATION AND FAILURE.						1	L	7	1 	3O			NT	3A13 					 
1995042800609	19950428	00609	CE 	1995	4	28	95ZZZX2045 	1	19950412	G	3710	B904	HOSE 			CESSNA	182 	182R 	2072731	CE 										INSP PNL VAC SYS	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	09	5481E	772 				18268325				INSP FOUND VACUUM SYSTEM HOSE DETERIORATION AND FAILURE.						1	L	7	1 	3O			NT	3A13 					 
1995042800610	19950428	00610	SO 	1995	4	28	95ZZZX2046 	1	19950401	G	5740		FITTING 			PIPER 	PA28 	PA28161 	7102803	SO 										WING ATTACH	RUSTED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	4352G	4960 				288416074				IN COMPLYING WITH PIPER SB 977, THE AFT WING ATTACH FITTINGS WERE FOUND RUSTED AND REQUIRE REMOVAL AND REPLACEMENT. THI	S SB SHOULD BE EXTENDED TO COVER ALL STEEL FITTINGS. ALSO, REMOVAL OF FIBERGLASS INSULATION AND INSTALLATION OF FOAM TY	PE WOULD BE A HELP. SUCH AS MOONEY SB 208.				1	L	7	1 	3O				2A13 					 
1995042800611	19950428	00611	SO 	1995	4	28	95ZZZX2047 	1	19950401	G	5740		FITTING 			PIPER 	PA28 	PA28181 	7102807	SO 										WING ATTACH	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	8112S	6470 				288090126				IN COMPLYING WITH PIPER SB 97, AFT WING ATTACH FITTINGS FOUND RUSTED, AND REQUIRED REMOVAL AND REPLACEMENT. SUBMITTER S	UGGESTS THIS SB SHOULD BE EXTENDED TO COVER ALL STEEL FITTINGS. ALSO, REMOVAL OF FIBERGLASS INSULATION AND INSTALLATION	 OF FOAM TYPE WOULD BE A HELP SUCH AS MOONEY SB 208.				1	L	7	1 	3O				2A13 					 
1995042800612	19950428	00612	SO 	1995	4	28	95ZZZX2048 	1	19950301	G	8120	LW10098	CONTROLLER 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					TURBO DIFF	MALFUNCTIONED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	627HA		2 		YA000462	317952241				ENGINE MANIFOLD PRESSURE FLUCTUATED 4 INCHES IN-FLIGHT. TROUBLESHOOTING FOUND NO OBVIOUS DISCREPANCIES WITH ENGINE. DI	FFERENTIAL CONTROLLER WAS CHANGED AND SYMPTOMS CURED. TEST FLOWN AND OPS CHECKED NORMAL.					1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995042800613	19950428	00613	SO 	1995	4	28	95ZZZX2049 	1	19950409	G	3246	4076F	WHEEL 	PARKERHANFIN		PIPER 	PA34 	PA34200T 	7103406	SO 										NLG	CRACKED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4490F	5469 				347670339				FOUR INCH CRACK FOUND IN CURVED SIDE OF NOSE WHEEL.						1	L	7	2 	3O				A7SO 					 
1995042800614	19950428	00614	SO 	1995	4	28	95ZZZX2050 	1	19950404	G	7922	53E19600	VERNATHERM 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	500EE	900 			48986	318052131				VERNATHERM REMOVED FOR INSPECTION PER LYCOMING SB 518A. VERNATHERM FOUND DEFECTIVE. NUT LOOSE ON SHAFT.						1	L	7	2 	3O				A20SO 					 
1995042800615	19950428	00615	CE 	1995	4	28	95ZZZX2051 	1	19950329	G	2410	352030	RETAINER 			CESSNA	150 	150L 	2071826	CE 										ALT DRIVE	BROKEN 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	01	11460	812 				15075439				INVESTIGATION FOR ALTERNATOR DRIVE COUPLING RETAINER FAILURE FOUND DRIVE COUPLING BUSHING TO BE AN INCORRECT PART. BUSH	ING PN 626543 WAS INSTALLED. PN 632050 IS PROPER PART. 812 HOURS TT SINCE INSTALLATION. SUBMITTER STATES RUBBER BUSHI	NGS SHOULD BE CHECKED IF ENGINE HAS 500 HOURS OR MORE TT.				1	H	7	1 	3O				3A19 					 
1995042800616	19950428	00616	SO 	1995	4	28	95ZZZX2052 	1	19950403	G	3232	AN8374D	FITTING 			PIPER 	PA31 	PA31350 	7103110	SO 										LT MLG DR ACT	FAILED 	B			APCR	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			NM	01	50088					31805213				LANDING GEAR FAILED TO COMPLETE 'UP' CYCLE DUE TO FLUID AND PRESSURE LOSS FROM BROKEN AN 387-4D HYDRAULIC FITTING.						1	L	7	2 	3O				A20SO 					 
1995042800617	19950428	00617	CE 	1995	4	28	95ZZZX2053 	1	19950405	G	7602	08502639	CONTROL 			CESSNA	310 	310P 	2074238	CE 										QUADRANT	BROKE 	D				O				OTHER 				O			OTHER 			CR	CRUISE 	1			NM	11	55DL	2730 				310P0038				MIXTURE CONTROL BROKE IN-FLIGHT WITH NO PRIOR INDICATION, NO BINDING, STICKING, ETC. BROKE AT QUADRANT END INSIDE HOUSI	NG.					1	L	7	2 	3O				3A10 					 
1995042800618	19950428	00618	SO 	1995	4	28	95ZZZX2054 	2	19950303	G	7414	10357586	DISTRIBUTOR GEAR		S6RSC25P 	PIPER 	PA46 	PA46310P 	7104605	SO 	CONT 	O520 	TSIO520BE 	17040	SO 					RT MAG	WQORN 	B			LF1R	O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			EA	07	121RF	500 				4608034	273695R			OWNER COMPLAINED OF ROUGHNESS IN FLIGHT. MIXTURE CHANGE OR FUEL PUMP OPERATION WOULD NOT AFFECT ENGINE. PERFORMED MAG	NETO CHECK ON GROUND. FOUND RT MAGNETO WOULD NOT KEEP ENGINE RUNNING. REMOVED RT MAGNETO AND FOUND 10 TEETH MISSING FR	OM DISTRIBUTOR GEAR. POSSIBLY CAUSED AN ENGINE BACKFIRE. GEAR SEEMED TO BE IN GOOD SHAPE. ROTOR GEAR IS METAL IN THES	E MAGNETOS WHICH COULD CONTRIBUTE TO THIS PROBLEM. RECOMMEND 100 HOUR INSPECTIONS FOR THESE MAGNETOS.			1	L	7	1 	3O	3	O		A25SO 	E8CE				 
1995042800619	19950428	00619	EU 	1995	4	28	95ZZZX2055 	1	19950413	G	2150	92005177	COMPRESSOR 			SLNSBY	T67 	T67M260 	8323006	EU 										AIR CONDITIONER	BOLT MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3037H	66 				920639				COWLING REMOVED FOR DAILY MAINTENANCE. INSPECTION FOUND A MOUNT BOLT ON THE A/C COMPRESSOR MISSING AND CAUSED THE A/C C	OMPRESSOR BELT TO SLIP OFF PULLEY. THIS IS THE FIRST OCCASION.					1	L	7	1 	3O			NT	A73EU 					 
1995042800620	19950428	00620	EU 	1995	4	28	95ZZZX2056 	1	19950413	G	3250	T67B45251	ROD 			SLNSBY	T67 	T67M260 	8323006	EU 										NLG STEERING	SHEARED 	D				O				OTHER 				O			OTHER 			TX	TAXI/GRND HDL 	1			SW	17	3045S					920646				WHILE TAXIING ACFT, NOSE STEERING WAS LOST. INSP WAS DONE AND THE NOSE STEERING ROD HAD SHEARED AT THE ADJUSTMENT NUTS.	 UNKNOWN WHY ROD SHEARED. THIS IS THE FIRST OCCASION.					1	L	7	1 	3O			NT	A73EU 					 
1995042800689	19950428	00689	CE 	1995	4	28	95ZZZX2057 	1	19950327	G	3230	HMXL66	ROD END 			BEECH 	58 	58 	1152740	CE 										NLG RETRACT	FAILED 	E		A		A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			SW	05	17915					TH78				UPON RETRACT OF LANDING GEAR, PILOT HEARD A BANG. ON LANDING ROLL-OUT, NOSE LANDING GEAR COLLAPSED. INVESTIGATION FOUN	D AFT RETRACT ROD END HAD BROKEN IN THE THREADED PORTION. THIS ROD END CONNECTS TO THE LANDING GEAR ACTUATOR (TRANSMISS	ION). PART TOTAL TIME UNKNOWN, BUT MORE THAN 20 YEARS OLD. SUSPECT SEIZURE OF THE ROD END DUE TO POOR LUBRICATION. TH	IS ROD END HAS NO LUBRICATION FITTING. MAINTENANCE MANUAL LISTS 10W30 OIL AS THE PROPER LUBRICANT. THIS ROD END ALSO H	AS HOLLOWED SHANK WHICH WAS FULL OF RUST. NEW, SUPERCEDED PART, ADNEL6-317, HAS SOLID SHANK.		1	L	7	2 	3O				3A16 					 
1995042800690	19950428	00690	CE 	1995	4	28	95ZZZX2058 	1	19950407	G	2730	0334106	TORQUE TUBE 		O334200 	CESSNA	170 	170 	2072302	CE 										LT ELEVATOR	RUSTED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4137V					18469				LEFT AND RIGHT ELEVATOR TORQUE TUBES RUSTED AND PITTED. DEFECT FOUND DURING RESKINNING OF ELEVATOR. THESE TUBES ARE NO	T AVAILABLE THROUGH ANY PARTS VENDORS AT THIS TIME. NEW PARTS MUST BE LOCALLY FABRICATED FROM DRAWING. SUBMITTER RECOM	MENDS TUBE BE INSPECTED ON A/C. IF RUSTY, REMOVE AND SANDBLAST RUST OFF. IF PITTED, REMOVE AND REPLACE TORQUE TUBES. I	F NEW, TUBES ARE INSTALLED. INSTALL DISSIMILAR TAPE BETWEEN SKIN AND TUBE ASSEMBLIES.			1	H	7	1 	3O			NT	A799 					 
1995042800691	19950428	00691	CE 	1995	4	28	95ZZZX2059 	1	19950407	G	2730	0334206	TORQUE TUBE 		O3341002 	CESSNA	170 	170 	2072302	CE 										RT ELEVATOR	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4137V					18469				LEFT AND RIGHT ELEVATOR TORQUE TUBES RUSTED AND PITTED. DEFECT FOUND DURING RESKINNING OF ELEVATOR. THESE TUBES ARE NO	T AVAILABLE THROUGH ANY PARTS VENDORS AT THIS TIME. NEW PARTS MUST BE LOCALLY FABRICATED FROM DRAWING. SUBMITTER RECOM	MENDS TUBE BE INSPECTED ON A/C. IF RUSTY, REMOVE AND SANDBLAST RUST OFF. IF PITTED, REMOVE AND REPLACE TORQUE TUBES. I	F NEW, TUBES ARE INSTALLED. INSTALL DISSIMILAR TAPE BETWEEN SKIN AND TUBE ASSEMBLIES.			1	H	7	1 	3O			NT	A799 					 
1995042800692	19950428	00692	CE 	1995	4	28	95ZZZX2060 	1	19950401	G	3222	52435181	FORK BOLT 			CESSNA	402 	402A 	207590M	CE 										RT MLG	BENT 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			WP	19	99AT					402A0022				RT MLG FORK BOLT BENT APPROXIMATELY .3750 INCH TOWARDS INBOARD SIDE OF ACFT WHEELWELL. BECAUSE OF THIS, RT MLG FAILED T	O LOCK DOWN CAUSING RT MLG TO COLLAPSE ON ROLL-OUT. NOTE: THIS FORK BOLT IS COVERED BY AD 76-13-07 AND WAS DUE TIME CH	ANGE AT 2,000 HOURS. AT TIME OF FAILURE, IT HAD 1978.9 HRS SINCE NEW (LAST MLG INSP WAS 107 HRS BEFORE FAILURE). (CAUS	E OF FAILURE UNKNOWN).			1	L	7	2 	3O				A7CE 					 
1995042800693	19950428	00693	SO 	1995	4	28	95ZZZX2061 	1	19950409	G	5712	6502006	RIB 			PIPER 	PA28 	PA28140 	7102802	SO 										LT WING AFT	NOT RIVETED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	3959X	2912 				287625001				DURING ANNUAL INSPECTION, FOUND LEFT WING, TIP RIB WAS NOT RIVETED TO MAIN SPAR. THIS APPEARS TO HAVE NEVER BEEN RIVETE	D. THIS HAS APPARENTLY BEEN OVERLOOKED SINCE THE AIRCRAFT WAS BUILT IN 1975. THE DEFECT IS PLAINLY VISIBLE WITH THE WI	NG TIP REMOVED, IT IS NOT HIDDEN BEHIND ANY LIP OR FLANGE.				1	L	7	1 	3O				2A13 					 
1995042800694	19950428	00694	SO 	1995	4	28	95ZZZX2062 	1	19950409	G	5712	6202400	RIB 			PIPER 	PA28 	PA28140 	7102802	SO 										LT WING FWD	NOT RIVETED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	3959X	2912 				287625001				DURING ANNUAL INSPECTION, FOUND LEFT WING, TIP RIB WAS NOT RIVETED TO MAIN SPAR. THIS APPEARS TO HAVE NEVER BEEN RIVETE	D. THIS HAS APPARENTLY BEEN OVERLOOKED SINCE THE AIRCRAFT WAS BUILT IN 1975. THE DEFECT IS PLAINLY VISIBLE WITH THE WI	NG TIP REMOVED, IT IS NOT HIDDEN BEHIND ANY LIP OR FLANGE.				1	L	7	1 	3O				2A13 					 
1995042800695	19950428	00695	SO 	1995	4	28	95ZZZX2063 	1	19950313	G	2720	6270109	CABLE 			PIPER 	PA28 	PA28180 	7102808	SO 										RUD CONTROL LT	LOOSE 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	8063W	1950 				282145				WHILE INVESTIGATING A LANDING INCIDENT, LOSS OF DIRECTIONAL CONTROL BY STUDENT PILOT. IT WAS NOTICED THAT RUDDER HAD AP	PROXIMATELY 1 INCH LEFT AND RIGHT OF VERTICAL FREE-PLAY MOVEMENT. RUDDER CABLES COULD BE HEARD SLOPPING IN BELLY. INSP	ECTION FOUND NO CABLE TENSION. INSPECTION OF CONTROL SYSTEM COULD FIND NO APPARENT MALFUNCTION, DAMAGE, OR CAUSE FOR LA	CK OF CABLE TENSION. SUGGEST CLOSER ATTENTION TO CONTROLS ON PRE-FLIGHT AND 100-HOUR INSPECTION.			1	L	7	1 	3O				2A13 					 
1995042800696	19950428	00696	SO 	1995	4	28	95ZZZX2064 	1	19950313	G	2720	6270108	CONTROL CABLE 			PIPER 	PA28 	PA28180 	7102808	SO 										RUDDER	LOOSE 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	8063W	1950 				282145				WHILE INVESTIGATING A LANDING INCIDENT, LOSS OF DIRECTIONAL CONTROL BY STUDENT PILOT. IT WAS NOTICED THAT RUDDER HAD AP	PROXIMATELY 1 INCH LEFT AND RIGHT OF VERTICAL FREE-PLAY MOVEMENT. RUDDER CABLES COULD BE HEARD SLOPPING IN BELLY. INSP	ECTION FOUND NO CABLE TENSION. INSPECTION OF CONTROL SYSTEM COULD FIND NO APPARENT MALFUNCTION, DAMAGE, OR CAUSE FOR LA	CK OF CABLE TENSION. SUGGEST CLOSER ATTENTION TO CONTROLS ON PRE-FLIGHT AND 100-HOUR INSPECTION.			1	L	7	1 	3O			 	2A13 					 
1995042800697	19950428	00697	CE 	1995	4	28	95ZZZX2065 	1	19950401	G	3260	1SE13	SWITCH 			CESSNA	402 	402B 	207590P	CE 										RT MLG	WIRE BROKEN 	D				L	O			ABORTED APPROACH 	OTHER 			P			NO WARNING INDICATION 			AP	APPROACH 	1			WP	19	5210J					402B0897				PILOT CALLED IN NO RT MLG DOWN AND LOCK INDICATION. PILOT PERFORMED SAFETY PROCEDURES, LOW ALTITUDE FLYBY'S. ON THIRD 	PASS, PILOT LANDED WITH NO INCIDENT. UPON INSPECTION OF RT MAIN DOWN AND LOCK MICROSWITCH PN 1SE1-3, A BROKEN GROUND WI	RE PN G20AC0 WAS DISCOVERED. THE GROUND WIRE WAS RECONNECTED, SECURITY CHECKED GOOD AND OPERATIONALLY CHECKED NORMAL.				1	L	7	2 	3O				A7CE 					 
1995042800698	19950428	00698	SO 	1995	4	28	95ZZZX2066 	1	19950329	G	3010		BOOT 	BFGOODRICH 		PIPER 	PA23 	PA23250 	7102308	SO 										DEICE	CORRODE WING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	5157Y	2159 				272196				B. F. GOODRICH EDGE SEALER (ESTANE) CAUSED WING SKIN CORROSION UNDER SEALER ON ALL BOOTS. INSTALLATION WAS MADE BY THE 	B. F. GOODRICH CO. IN 1976 AND THE BOOTS STILL LOOK NEW.					1	L	7	2 	3O				1A10 					 
1995042800699	19950428	00699	EA 	1995	4	28	95ZZZX2067 	2	19950408	G	7310	LW102980134	LINE 			PIPER 	PA32 	PA32300 	7103212	SO 	LYC 	O540 	IO540K1A5 	41532	EA 					NR 3 CYL NOZ	BROKEN 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			AL	01	31606	1394 				327840137	L1586248A			DURING FLIGHT, ENGINE BEGAN RUNNING VERY ROUGH. THE PILOT LANDED AT NEAREST AIRPORT. UPON INSPECTION, FOUND LINE GOING	 FROM THE SPIDER TO THE NR 3 CYLINDER FUEL NOZZLE HAD BROKEN. THIS BREAK OCCURRED UNDER THE B-NUT NEXT TO THE BALL AT T	HE END OF THE LINE WHERE IT CONNECTS TO THE FUEL NOZZLE. THE NUT WAS TIGHT AND CONNECTED PROPERLY. FUEL LINE REPLACED 	WITH NEW.			1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995042800700	19950428	00700	CE 	1995	4	28	95ZZZX2068 	1	19950222	G	2410	AN743A	BOLT 			CESSNA	150 	152 	2071835	CE 										ALTERNATOR PIVOT	NUT MISSING 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	6529L					15284427				OWNER COMPLAINED ABOUT LOOSE ALTERNATOR BELT. INSPECTED ALTERNATOR AND FOUND PIVOT BOLT NUT MISSING. REMOVED BOLT AND 	FOUND SEVERELY WORN. LINK AND ALTERNATOR HOUSING WORN FROM ASSY BEING LOOSE. REPLACED WITH NEW HARDWARE. MAY HAVE BEE	N CAUSED BY LOCKNUT LOOSING ITS LOCKING CAPABILITIES. INSTALLATION SHOULD BE CHANGED TO A DRILLED SHANK BOLT WITH COTTE	R PIN. NOTE: CESSNA IPC CURRENTLY SHOWS ELASTIC LOCKNUT.			1	H	7	1 	3O			NT	3A19 					 
1995042800701	19950428	00701	SO 	1995	4	28	95ZZZX2069 	1	19950404	G	2731	62701191	CONTROL CABLE 			PIPER 	PA28 	PA28RT201T 	7102817	SO 										FWD ELEV TRIM	FRAYED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	8392T	1858 				28R8131140				THE FORWARD ELEVATOR TRIM CABLE WAS FOUND SEVERELY FRAYED. THE DAMAGE WAS LOCATED AT THE POINT WHERE THE CABLE CONTACTE	D THE PITCH SERVO CAPSTAN. THE CABLE WAS PROPERLY ROUTED, AND THE TENSION WAS CORRECT. SUBMITTER RECOMMENDS THIS AREA 	BE INSPECTED EVERY 50 HOURS.				1	L	7	1 	3O			 	2A13 					 
1995042800702	19950428	00702	CE 	1995	4	28	95ZZZX2070 	1	19950221	G	3230	358251722	ROD 			BEECH 	58 	58P 	1152744	CE 										NLG RETRACT	MISRIGGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	112Z		400 			TJ371				DURING AN INSPECTION OF THE LANDING GEAR SYSTEM, THE NLG RETRACT ROD WAS FOUND CONTACTING THE AIRCRAFT STRUCTURE IN TWO 	PLACES WITH THE GEAR DOWN AND LOCKED. IT WAS DETERMINED THE NOSE GEAR ACTUATOR RETRACT ARM WAS POSITIONED INCORRECTLY. 	 PROPER INDEXING OF THE NOSE GEAR ACTUATOR RETRACT ARM WILL PREVENT THIS SITUATION FROM OCCURRING.				1	L	7	2 	3O				A23CE 					 
1995042800703	19950428	00703	CE 	1995	4	28	95ZZZX2071 	1	19950204	G	2701	05131682	CONTROL WHEEL 			CESSNA	172 	172 	2072402	CE 										PILOTS	FAILED 	B	S		NTBR	O				OTHER 				O			OTHER 			LD	LANDING 	1			NM	05	9793T	2561 				47593				PILOT'S PLASTIC CONTROL YOKE BROKE OFF IN THE PILOT'S HAND ON LANDING. AIRCRAFT WAS ABOUT 2 FEET OFF THE GROUND. LANDI	NG WAS COMPLETED SAFELY.					1	H	7	1 	3O			NT	3A12 					 
1995042800704	19950428	00704	CE 	1995	4	28	95ZZZX2072 	1	19950315	G	2720		IDLER 			BOEING	75 	A75 	1380108	CE 										RUDDER LT SIDE	FAILED 	H				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			WP	19	1359N					755738				LEFT SIDE IDLER ARM ON RUDDER BROKE.						1	Q	7	1 	3R				A743 					 
1995042800705	19950428	00705	SO 	1995	4	28	95ZZZX2073 	1	19950207	G	7810	40B19850	CROSS-OVER 			PIPER 	PA46 	PA46350P 		SO 										LT EXHAUST	BULGED 	B		A	LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	41003	1204 				4622044				DURING ANNUAL INSPECTION, CROSS-OVER SHIELD REMOVED FOR INSPECTION. FOUND CROSS-OVER PIPE BULGED AND WARPED. PROBLEM A	PPEARS TO BE CAUSED BY EXCESSIVE HEAT. PART IS LOCATED AT REAR OF ENGINE IN AREA OF LOW AIR FLOW. SUBMITTER HIGHLY REC	OMMENDS THIS AREA BE INSPECTED EVERY ANNUAL/OR 100 HOURS. PART CAN ONLY BE INSPECTED PROPERLY BY REMOVING ONE-HALF OF H	EAT SHIELD. THIS IS 3RD AIRCRAFT SEEN WITH THIS PROBLEM.			1	L	7	1 	3O			RT	A25SO 					 
1995042800706	19950428	00706	SW 	1995	4	28	95ZZZX2074 	1	19950119	G	5511	43000256	SPAR CAP 			GULSTM	690TP 	690B 	7630516	SW 										STABILIZER	CRACKED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	15SF	5323 				11528				UPPER FORWARD STABILIZER SPAR CAP FOUND CRACKED IN RADIUS OF UPPER FLANGE ABOVE UPPER RIGHT ATTACH BOLT.						1	H	7	2 	3T				2A4 					 
1995042800707	19950428	00707	NE 	1995	4	28	95ZZZX2075 	2	19950403	G	7310	216365003	MANIFOLD 		216362035 	BAG 	BAE146	BAE146200A 	1500266	EU 	LYC 	ALF502	ALF502R 	41580	NE 					NR 5-6 NOZ PORT	LEAKS 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	13		8997 	1110 		227P					MANIFOLD HAS LEAK IN SCALLOP AREA BETWEEN 5TH AND 6TH NOZZLES. A SB WAS ISSUED, ALF502R73-8, REQUIRING A ONE FPI OF ALL	 MANIFOLDS WITH P/N ENDING IN DASH 09 THROUGH DASH 34. WHEN COMPLETED, MANIFOLDS ARE REIDENTIFIED AS DASH 35 OR DASH 36	. FPI FOR ALL MANIFOLDS HAS SINCE BEEN INCORPORATED INTO THE REPAIR MANUAL AND IS REQUIRED AT EACH OVERHAUL. SUBMITTER	 SUGGESTS SHORTER TIME BETWEEN OVERHAUL/REPAIR OR THAT THESE PARTS BE LIFE-LIMITED.			2	H	7	4 	4F	4	F	RT	A49EU 	E6NE				 
1995042800708	19950428	00708	EU 	1995	4	28	95ZZZX2076 	1	19950407	G	3250	503028531	CONTROL CABLE 			ISRAEL	1124 	1124A 	4500103	EU 										STEERING DRUM	FRAYED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	50XX	3247 				412				DURING COMPLIANCE OF SB 1124-32-116, A SHINY AREA WAS NOTED ON THE CABLE AT THE POINT WHERE THE CABLE WAS SECURED BY THE	 LOCK TAB. THE CABLE WAS REMOVED FOR INSPECTION. SUBSEQUENT INSPECTION REVEALED NUMEROUS BROKEN STRANDS. APPROXIMATELY	 2 INCHES FORWARD OF THE SHINY AREA. THE CABLE APPEARED TO HAVE CORROSION IN THE INNER PORTION OF THE STRANDS. CABLE W	AS REJECTED AND A NEW CABLE WAS INSTALLED.			2	M	7	2 	4F			 	A2SW 					 
1995042800711	19950428	00711	EU 	1995	4	28	95ZZZX2079 	1	19950329	G	2612	9560129980	DETECTOR 			AEROSP	SA365 	SA365N1 	8680668	EU 										NR 2 ENGINE	MALFUNCTION 	B			KY1R	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			EA	07	95MD	788 			9475	6320				NR 2 ENGINE FIRE LIGHT ILLUMINATED. WHILE ENGINE WAS COLD. LIGHT WENT OUT AFTER START. TESTED DETECTOR, INITIAL READI	NG ON TEST BENCH WAS 500 MV.					1	G	7	2 	3U				H10EU 					 
1995042800712	19950428	00712		1995	4	28	95ZZZX2080 	4	19950322	G	2200	41800561612	ACTUATOR 			AEROSP	SA365 	SA365N1 	8680668	EU 										AUTO FLIGHT	DEFECTIVE 	B			KY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	94MD		1272 		687	6317				ACTUATOR CAUSES ROLL CHANNEL FAILURE. ON IN-FLIGHT TEST, BOX COMPARITOR NR 5 IN AAU LIGHT IS LIT. ACTUATOR HAS ONLY 1.	1 MIL OHM RESISTANCE ON PINS 'C' AND 'D', BOTH PLUGS.					1	G	7	2 	3U				H10EU 					 
1995042800713	19950428	00713	EU 	1995	4	28	95ZZZX2081 	1	19950316	G	6210	365A11005004	BLADE 			AEROSP	SA365 	SA365N1 	8680668	EU 										NR 3 LE STRIP	CRACKED 	B			KY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	96MD	2991 			7156	6321				NR 3 LEADING EDGE STRIP CRACKED.						1	G	7	2 	3U				H10EU 					 
1995042800714	19950428	00714	EU 	1995	4	28	95ZZZX2082 	1	19950316	G	6210	365A11005004	BLADE 			AEROSP	SA365 	SA365N1 	8680668	EU 										EROSION GUARD	CRACKED 	B			KY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	96MD	2991 			7186	6321				NR 3 LEADING EDGE EROSION GUARD CRACKED.						1	G	7	2 	3U				H10EU 					 
1995042800720	19950428	00720	SW 	1995	4	28	95ZZZX2088 	1	19950315	G	5302	NAS5778A	NUT 			BELL 	412 	412 	1182202	SW 										TAIL BOOM	FAILED 	B		A	ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2071S	10127				33046				WHILE INSTALLING TAIL BOOM WHEN COMING UP TO REQUIRED TORQUE ON UPPER RT TAIL BOOM TO FUSELAGE ATTACHMENT BOLT PN NAS 62	8, A 'POP' NOISE WAS HEARD AND THE BOLT THREADS SEEMED TO BE STRIPPED. THE BOLT AND NUT WERE REMOVED AND THE NUT WAS FO	UND SPLIT IN TWO PIECES. CAUSE UNKNOWN.				1	G	7	2 	4U				H4SW 					 
1995042800721	19950428	00721	GL 	1995	4	28	95ZZZX2089 	2	19950329	G	7321	953505120	SCREW 	BENDIX 	23059790 	BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30 	03013	GL 					RETAINER PLATE	FAILED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL	1291 			BR53561	51460	CAE895436			ON DAILY SERVICE CHECK, FOUND INBOARD SCREW WHICH SECURES BYPASS VALVE RETAINING PLATE TO THE FUEL CONTROL BODY WAS FOUN	D WITH HEAD BROKEN OFF. CAUSE UNKNOWN. COMPLETE FUEL CONTROL WITH BROKEN SCREW WAS SENT TO ALLIED SIGNAL - BENDIX FOR 	EVALUATION. CEB'S 73-3061 REPLACEMENT OF THESE SCREWS AND LAPPING THE RETAINER PLATE HAS BEEN PREVIOUSLY COMPLIED WITH 	AS HAS CEB 78-A-3065 REPLACMENT OF RELIEF VALVE.			1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995042800722	19950428	00722	NE 	1995	4	28	95ZZZX2090 	1	19950308	G	6520	SB3167101	BEARING CONE 		763357050000	SKRSKY	S76 	S76 	8143010	NE 										INPUT QUILL	FAILED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	703AL	599 			A07300266	760266				DURING GROUND RUN, INTERMEDIATE GEARGBOX BEARING FAILED. CAUSE UNKNOWN. BEARINGS, INPUT QUILL HOUSING AND INPUT GEAR S	ENT TO SIKORSKY FOR EVALUATION. CONE PN SB3167101, CUP PN SB3167201.					1	G	7	2 	3U				H1NE 					 
1995042800723	19950428	00723	SW 	1995	4	28	95ZZZX2091 	1	19950329	G	6510	214040606005	BEARING 		214040600107	BELL 	214 	214ST 	1182106	SW 										OUTER RACE	FRACTURED 	B	S		ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	390AL	3223 	250 			28198				WHILE HANGER ASSY WAS REMOVED TO LUBRICATE FLEX-COUPLINGS. HANGER BEARING FELT ROUGH WHEN ROTATED BY HAND WITH HANGER A	SSY REMOVED. OUTER RACE OF BEARING WAS FOUND FRACTURED WHEN REMOVED FROM THE HOUSING. CAUSE UNKNOWN.					2	G	7	2 	4U				H10SW 					 
1995042800724	19950428	00724	NE 	1995	4	28	95ZZZX2092 	1	19950313	G	6210	761509100041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R TIP	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	712AL	9408 	468 		A08600597A	760280				DEFECT DISCOVERED DURING C.A.M.P. 500-HOUR BLADE INSPECTION, FOUND CRACK IN SPAR AND LOWER SKIN AT TIP END EXTENDING INB	OARD FROM APPROXIMATELY STA 249.88 TO STA 247.65. CAUSE UNKNOWN.					1	G	7	2 	3U				H1NE 					 
1995042800725	19950428	00725	NE 	1995	4	28	95ZZZX2093 	1	19950313	G	6210	7615009100051	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	712AL	9811 	468 		A08601355	760280				DISCOVERED WHEN COMPLYING WITH AD 84-10-2, 500-HOUR INSPECTION. FOUND CRACK IN SPAR AT ROOT END LOWER SIDE ON BLADE EXT	ENDING FROM FORWARD OUTBOARD BUSHING HOLE TO LEADING EDGE APPROXIMATELY 1.5 INCHES LONG.					1	G	7	2 	3U				H1NE 					 
1995050500124	19950505	00124	EU 	1995	5	5	95ZZZX2096 	1	19950305	G	6240	50071550020	SENSOR 			SNIAS 	350 	AS350B 	8680801	EU 										ROTOR TACH	DEFECTIVE 	B				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	85GA	925 				2362				THIS IS THE SECOND FAILURE OF THE NR HORN CIRCUIT ON THE TACH SENSOR IN 1981.4 HOURS ACTT. SUBMITTER STATED IT APPEAR	S TO BE A POORLY DESIGNED UNIT WITH A VERY LOW LIFE EXPECTANCY. INSTALLED NEW TACH SENSOR.					1	G	7	1 	3U				H9EU 					 
1995050500125	19950505	00125	SW 	1995	5	5	95ZZZX2097 	1	19950223	G	6420	MS14145L6	NUT 			BELL 	412 	412 	1182202	SW 										T/R BELLCRANK	FAILED 	B			ALGR	A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			NR	NOT REPORTED 	1			SW	03	2FOR	1440 				33042				THE T/R SUDDENLY DEVELOPED A SEVERE VIBRATION IN-FLIGHT. THE AIRCRAFT WAS LANDED IMMEDIATELY. EVIDENCE INDICATES THE N	UT WHICH SECURES THE COUNTERWEIGHT BELLCRANK TO THE T/R CROSS-HEAD FAILED ALLOWING THE C/W BELLCRANK TO COME OFF STRIKIN	G THE T/R BLADE AS IT DEPARTED THE AIRCRAFT. THE THREADS ON THE T/R CROSS-HEAD WERE STILL IN GOOD CONDITION. PIECES OF	 THE COTTER KEY WERE STILL IN PLACE WHICH INDICATES THAT THE NUT FAILED AND THE FORCE OF THE COUNTERWEIGHT BELLCRANK SHE	ARED OFF THE COTTER KEY. THE BELLCRANK WAS NOT RECOVERED. SUBMITTER STATED NUT IS TOO LIGHT-WEIGHT TO BE USED IN SUCH 	A SAFETY SENSITIVE APPLICATION HAD THE PILOT NOT BEEN ABLE TO LAND IMMEDIATELY. THIS COULD HAVE BEEN A CATASTROPHE.	1	G	7	2 	4U				H4SW 					 
1995050500126	19950505	00126	NE 	1995	5	5	95ZZZX2098 	2	19950407	G	7230	50H067	NUT PLATE 								PWA 	4056 	PW4056 		NE 					STG 9-10 STATOR	MISMANUFACTURED 	B			TUVR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	11										PURCHASED NUT PLATE ASSY HAS OVERALL LENGTH WHICH IS APROXIMATELY ONE INCH LONGER THAN A PN 50H067. IN ADDITION, NUT PA	TTERN IS INCORRECT FOR PN 4000 9/10 STAGE COMPRESSOR STATOR.										4	F			E24NE				 
1995050500127	19950505	00127	CE 	1995	5	5	95ZZZX2099 	1	19950324	G	2435	03600907	BEARING 		23085001 	BEECH 	300 	300BEECH 	1152930	CE 										STARTER/GEN	FAILED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	427P	1990 	553 		1965	FA186				DURING INSPECTION OF STARTER/GENERATOR, FOUND THE COMMUTATOR END BEARING FAILED. BOTH ARMATURE AND STATOR WERE DAMAGED.	 THESE BEARINGS ARE DESIGNED TO LAST 1,000 HOURS.					2	L	7	2 	4T				A24CE 					 
1995050500128	19950505	00128	SW 	1995	5	5	95ZZZX2100 	1	19950405	G	3020	65951202W	INLET 			GULSTM	560 	560 	0141402	SW 										RT ENGINE	DUCT CRACKED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	60GL	897 	321 		RS39224	5600187				DURING INSPECTION, THE DEICE DUCT OF THE RIGHT ENGINE INLET WAS FOUND CRACKED AT THE BLEED PIPE FLANGE. THIS INLET IS T	HE LATEST MOD, UPDATED TO RE-ENFORCE THIS AREA TO PREVENT CRACKING. CESSNA HAS BEEN ALERTED TO THIS SITUATION. INLET W	AS INSTALLED AS A REPLACEMENT UNIT ON 4-4-94 AT 575.9 HRS ACTT, AND 644 LANDINGS.				1	H	7	2 	3O				6A1 					 
1995050500129	19950505	00129	SW 	1995	5	5	95ZZZX2101 	1	19950405	G	3020	65951201W	INLET 			GULSTM	560 	560 	0141402	SW 										LT ENGINE	DUCT CRACKED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	60GL	897 	450 		RB68935	5600187				DURING INSPECTION, THE DEICE DUCT OF THE LEFT ENGINE INLET WAS FOUND CRACKED AT THE BLEED PIPE FLANGE. THIS INLET WAS T	HE LATEST MOD, UPDATED TO RE-ENFORCE THIS AREA TO PREVENT CRACKING. CESSNA HAS BEEN ALERTED TO THIS SITUATION. INLET W	AS INSTALLED AS A REPLACEMENT UNIT ON 10-27-93 AT 446.9 HOURS, AND 522 LANDINGS.				1	H	7	2 	3O				6A1 					 
1995050500130	19950505	00130	WP 	1995	5	5	95ZZZX2102 	1	19950411	G	7500	6876667	AIR TUBE 			HUGHES	369 	369D 	4470706	WP 										FIREWALL FLANGE	CRACKED 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL OF CUSTOMER ACFT, THE ENGINE DISCHARGE AIR TUBE WAS FOUND CHAFED FORWARD OF THE FIREWALL FLANGE BY THE WAV	Y WASHER HAVING BEEN DISPLACED SOME HOW. PART SENT IN FOR REPAIR.					1	G	7	1 	3U				H3WE 					 
1995050500131	19950505	00131	CE 	1995	5	5	95ZZZX2103 	1	19950207	G	2520	T1280G1516	SEAT 			BEECH 	B300 	B300 	1159232	CE 										CABIN	LOCK MALFUNCTION	B		A	KI2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	65CR	2296 				FL60				SEAT LOCKING MECHANISM IS INADEQUATE. SEAT CAN BE OVERPOWERED WITH THE SLIGHTEST BODY MOVEMENT. RE-ADJUSTED PER FACTOR	Y SPECS. WITH NO IMPROVEMENT. SUBMITTER STATED OTHER OPERATORS ARE HAVING SAME PROBLEMS.					2	L	7	2 	4T			RT	A24CE 					 
1995050500133	19950505	00133	CE 	1995	5	5	95ZZZX2105 	1	19950414	G	8010	6041H202A	RELAY 			LEAR 	35 	35A 	5170602	CE 										GEN CONT PANEL	MALFUNCTION 	B	L	A	JGVR	A				UNSCHED LANDING 				J			WARNING INDICATION 			CL	CLIMB 	1			CE	09	72DA					098				LEFT ENGINE START RELAY GENERAL CONTROL PANEL FAILED TO THE ENGAGE POSITION IN-FLIGHT CAUSING LEFT ENGINE STARTER TO ENG	AGE. INVESTIGATION REVEALED K-9 RELAY CONTACTS WELDED TOGETHER AND THE K-7 RELAY TO HAVE HIGHLY PITTED CONTACTS. BOTH 	THE K-7 AND K-9 RELAYS WERE REPLACED PER GCP REPAIR MANUAL RM-117. THE RELAYS ARE IN THE POSSESSION OF DUNCAN AVIATION 	AND AVAILABLE FOR EXAMINATOIN UPON REQUEST. THE LEFT STARTER SHOWED EVIDENCE OF OVERHREATING AND WAS REPLACED.			2	L	7	2 	4F				A10CE 					 
1995050500134	19950505	00134	SO 	1995	5	5	95ZZZX2106 	1	19950214	G	3240	30106	BRAKE 	PARKERHANFIN		PIPER 	PA31 	PA31 	7103102	SO 										LT MLG	LOCKED UP 	E				K				NONE 				O			OTHER 			LD	LANDING 	1			NM	08	22DT	5353 	329 			31T8020057				UPON LANDING, LEFT BRAKE FROZE RESULTING IN A FLAT TIRE ON RUNWAY. DEPARTURE HAD BEEN FROM AN UNPLOWED SNOW COVERED RUN	WAY. SUSPECT SNOW PACKED AND FROZEN BRAKE. INSPECTION REVEALED NORMAL OPERATION.					1	L	7	2 	3O				A20SO 					 
1995050500135	19950505	00135	SO 	1995	5	5	95ZZZX2107 	1	19950411	G	5751		RIB 			PIPER 	PA31 	PA31310 	7103103	SO 										RT AILERON	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	6620L					31554				REMOVED AND REPLACED SPAR AND RIB IN RT AILERON IAW SB 974. SPAR AND RIB BOTH CRACKED. TT OF ACFT 6772.4.						1	L	7	1 	3O			RT	A20SO 					 
1995050500136	19950505	00136	SO 	1995	5	5	95ZZZX2108 	1	19950411	G	5751		SPAR 			PIPER 	PA31 	PA31310 	7103103	SO 										RT AILERON	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	6620L					31554				REMOVED AND REPLACED SPAR AND RIB IN RT AILERON IAW SB 974. SPAR AND RIB BOTH CRACKED. TT OF ACFT 6772.4.						1	L	7	1 	3O			RT	A20SO 					 
1995050500137	19950505	00137	CE 	1995	5	5	95ZZZX2109 	1	19950410	G	7430	C2925010105	SWITCH 			CESSNA	150 	152 	2071835	CE 										ENG IGNITION	INTERMITTENT 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	68969	5830 				15282419				INTERMITTENT FAILURE OF IGNITION SWTICH CAUSING ENGINE TO FAIL GIVING INTERMITTENT MAGNETO DROPS UP TO 500-600 RPM.						1	H	7	1 	3O			NT	3A19 					 
1995050500138	19950505	00138	CE 	1995	5	5	95ZZZX2110 	1	19950401	G	7922	53E19600	VALVE 			BEECH 	23 	B24R 	1151253	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	B			BPGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	53EM		104 			MC395				CRIMP NUT LOOSE ON SHAFT PER SB 518B (LYCOMING) DATED 3-21-95. TIME SINCE FACTORY OH, 104 HOURS. OVERHAULED BY LYCOMIN	G ON 12-22-92. PLACED IN SERVICE ON 3-1-93. REPLACED VALVE WITH NEW PART FROM LYCOMING.					1	L	7	1 	3O				A1CE 					 
1995050500139	19950505	00139	EA 	1995	5	5	95ZZZX2111 	2	19950410	G	8550		DRIVE COUPLING 			PIPER 	PA44 	PA44180 	7104402	SO 	LYC 	O360 	O360E1A6 	41514	EA 					ENG OIL SUMP	BLOCK OIL GALLEY	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	357DA					447995271				DURING COMPLETION OF AD 78-09-07 ON LT ENGINE AND WHILE INSTALLING LT MAG, RUBBER DRIVE COUPLING WAS DROPPED INTO ENGINE	. WHEN SUMP DRAIN WAS REMOVED TO RETRIEVE COUPLING, TWO WERE FOUND NEAR THE QUICK DRAIN. ENGINE HAD A HISTORY OF LOW O	IL PRESSURE ON OCCASIONS, BUT REASON HAD NOT BEEN FOUND. IT IS BELIEVED THE PREVIOUSLY LOST COUPLING WAS REASON FOR LOW	 OIL PRESSURES.			1	L	7	2 	3O	3	O		A19S0 	E286				 
1995050500140	19950505	00140	CE 	1995	5	5	95ZZZX2112 	1	19950401	G	7120	650695	BRACKET 			BEECH 	55 	E55 	1152732	CE 										ENGINE MOUNT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	88MB	2881 				TE844				WHILE PERFORMING INSPECTION IAW AD 94-09-07 AND AD 95-03-14, THE ENGINE LOWER LEFT MOUNT BRACKET WAS FOUND CRACKED. THE	 CRACK WAS .3750 INCH LONG AND WAS LOCATED TO THE AREA DESCRIBED BY THE AD AND TCM SB MSB94-9. BOTH LOWER MOUNTS WERE R	EPLACED IAW AD.				1	L	7	2 	3O				3A16 					 
1995050500141	19950505	00141	CE 	1995	5	5	95ZZZX2113 	1	19950420	G	7120	630694	MOUNT LEG 		630723 	BEECH 	35 	N35 	1151528	CE 										RT ENGINE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	574T	1100 				D6748				COMPLIED WITH AD 95-03-14 RM AMD NR 39-9150. FOUND NO DISCREPANCIES, NO CRACKS IN LOWER LEFT MOUNTS. COMPLETED DYE PEN	ETRANT INSPECTION OF REMAINING MOUNTS, FOUND LOWER RT MOUNT ON RT ENGINE CRACKED. REMOVED MOUNT AND FOUND SEVERAL CRACK	S IN MOUNT CONFIRMED BY DYE PENETRANT INSPECTION. PART SENT TO A+1 CERT, OFFICE FOR EVALUATION. AD SHOULD INCLUDE LOWE	R RT AND LOWER LT MOUNTS. PART WAS AT A POINT OF TOTAL FAILURE.			1	L	7	1 	3O				3A15 					 
1995050500142	19950505	00142	CE 	1995	5	5	95ZZZX2114 	1	19950404	G	8120	4078109006	TURBOCHARGER 	GARRTT 		CESSNA	414 	414 	2075908	CE 	CONT 	O520 	TSIO520BB 	17040	SO 					RT ENGINE	FAILED 	B			EB1R	E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			EA	13	99EF				XI000097	414A0666	236935R			AIRCRAFT EXPERIENCED LOSS OF POWER ON RIGHT ENGINE DURING FLIGHT. THE ENGINE WAS SHUT DOWN AND MADE AN EMERGENCY LANDIN	G. INVESTIGATION REVEALED THE TURBOCHARGER UNIT HAD FAILED INTERNALLY. THE TURBOCHARGER WAS REPLACED AND ENGINE WAS GR	OUND AND FLIGHT CHECKED SATISFACTORILY.				1	L	7	2 	3O	3	O	RT	A7CE 	E8CE				 
1995050500143	19950505	00143	CE 	1995	5	5	95ZZZX2115 	1	19950404	G	2410	626543	BUSHING 	FORD 	DOFF10300 	CESSNA	172 	172 	2072402	CE 										ALTERNATOR DRIVE	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	01	9837T	1170 			A5531	47637				ALTERNATOR HAD GENERATOR DRIVE COPULING BUSHING INSTALLED, PN 626543, IN PLACE OF PN 632050. THIS CAN CAUSE BREAKAGE OF	 HUB FOR BUSHING AND MAY EVEN CAUSE BREAKING OF ALT SHAFT. THESE BUSHINGS SHOULD BE CHANGED AT 1,000 HR INTERVALS TO MA	INTAIN PROPER OPERATION AND ALL ALTERNATORS SHOULD BE CHECKED FOR PROPER BUSHING 632050 IS INSTALLED. THIRD ONE FOUND I	N 30 DAYS.			1	H	7	1 	3O			NT	3A12 					 
1995050500144	19950505	00144	SO 	1995	5	5	95ZZZX2116 	1	19950410	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	NUT MISSING 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	27343	1100 			41083	317752163				DURING INSPECTION OF RIGHT ENGINE OIL VERNATHERM PER LYCOMING SB 518A, FOUND RETAINING NUT MISSING FROM END OF VERNATHE	RM. RETAINING NUT WAS RETRIEVED FROM ENGINE OIL COOLER.					1	L	7	2 	3O				A20SO 					 
1995050500145	19950505	00145	SO 	1995	5	5	95ZZZX2117 	1	19950410	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	NUT LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	27343	1000 			36220	317752163				REMOVED FOR INSPECTION PER SB 518A. VERNATHERM FAILED INSPECTION. CRIMP ON NUT WAS GREATER THAN MAX ALLOWANCE OF .167 	INCH AND NUT MOVED ON SHAFT.					1	L	7	2 	3O				A20SO 					 
1995050500146	19950505	00146	EA 	1995	5	5	95ZZZX2118 	2	19950412	G	8550	LW14888	SUMP ASSY 			PIPER 	PA44 	PA44180 	7104402	SO 	LYC 	O360 	LO360E1A6 	41514	EA 					INDUCTION DRAIN	BOSS CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	3040A					447995093	L17672			DURING INSPECTION AT ENGINE OVERHAUL, BOTH INDUCTION DRAIN BOSSES ON OIL SUMPS WERE FOUND CRACKED. SUSPECT BOSSES CRACK	ED FROM OVER TIGHTENING DRAIN VALVE ASSY, PN 24995-00.					1	L	7	2 	3O	3	O		A19S0 	E286				 
1995050500375	19950505	00375	SO 	1995	5	5	95ZZZX2119 	1	19950404	G	7120	6711957	MOUNT 			PIPER 	PA28 	PA28R200 	7102811	SO 										ENGINE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	75340	5458 			JT1000	28R7635292				FLIGHT CREW MEMBER IDENTIFIED CRACK ON ENGINE MOUNT RING TUBE ADJACENT TO DIP STICK. INTERESTINGLY, THIS CRACK IS IDENT	ICAL TO THOSE FOUND ON AIRCRAFT AFFECTED BY PIPER SL 568. SUBMITTER RECOMMENDS A REVIEW/EXPANSION OF THIS SL AND THE AD	DITION OF REINFORCEMENT TO PRECLUDE CRACKING AT NEXT ENGINE OVERHAUL.				1	L	7	1 	3O				2A13 					 
1995050500376	19950505	00376	CE 	1995	5	5	95ZZZX2120 	1	19950317	G	5520	5061000090	BRACKET 			BEECH 	90 	E90 	1152914	CE 										LT ELEVATOR	CRACKED 	B			BIOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	75JP	5575 				LW158				FOUND RIB AND BRACKET CRACKED ON LEFT ELEVATOR INBOARD WHERE TORQUE TUBE ATTACHED TO END RIB. CAUSE UNKNOWN. REPLACED 	PARTS WITH NEW. SPAR END ALSO CRACKED FROM WORKING OF TORQUE TUBE. REPAIRED BY DOUBLER IAW AC 43.13.					1	L	7	2 	3T				3A20 					 
1995050500377	19950505	00377	CE 	1995	5	5	95ZZZX2121 	1	19950317	G	5521		RIB 			BEECH 	90 	E90 	1152914	CE 										LT ELEVATOR	CRACKED 	B			BIOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	75JP	5575 				LW158				FOUND RIB AND BRACKET CRACKED ON LEFT ELEVATOR INBOARD WHERE TORQUE TUBE ATTACHED TO END RIB. CAUSE UNKNOWN. REPLACED 	PARTS WITH NEW. SPAR END ALSO CRACKED FROM WORKING OF TORQUE TUBE. REPAIRED BY DOUBLER IAW AC 43.13.					1	L	7	2 	3T				3A20 					 
1995050500378	19950505	00378	CE 	1995	5	5	95ZZZX2122 	1	19950317	G	5520		BRACKET 			BEECH 	90 	E90 	1152914	CE 										LT ELEVATOR	CRACKED 	B			BIOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	75JP	5575 				CW158				INSPECTION ON LEFT ELEVATOR INBOARD WHERE TORQUE TUBE ATTACHES TO END RIB, FOUND RIB AND BRACKET CRACKED. REPLACED PART	S WITH NEW.					1	L	7	2 	3T				3A20 					 
1995050500379	19950505	00379	CE 	1995	5	5	95ZZZX2123 	1	19950317	G	5521	50610000355	RIB 			BEECH 	90 	E90 	1152914	CE 										LT ELEVATOR	CRACKED 	B			BIOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	75JP	5575 				CW158				INSPECTION ON LEFT ELEVATOR INBOARD WHERE TORQUE TUBE ATTACHES TO END RIB, FOUND RIB AND BRACKET CRACKED. REPLACED PART	S WITH NEW.					1	L	7	2 	3T				3A20 					 
1995050500380	19950505	00380	SO 	1995	5	5	95ZZZX2124 	1	19950317	G	5312	65640803	BULKHEAD 			PIPER 	PA28 	PA28181 	7102807	SO 										FS 156	CRACKED 	B			BIOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	3024M	5896 				287890286				WHILE DOING SB 977, PULLED UP BAGGAGE FLOOR, FOUND AFT STEEL STEP SUPPORT BRACKET SEVERELY CORRODED. WHEN REMOVED, FOUN	D STEEL SUPPORT BRACKET BROKEN AND EMPENNAGE TO FUSELAGE BULKHEAD WITH 2 FOOT CRACK IN LOWER RADIUS. SUSPECT BATTERY AC	ID STARTED CORROSION PROCESS. REPLACE WITH BRACKET OF DIFFERENT MATERIAL.				1	L	7	1 	3O				2A13 					 
1995050500381	19950505	00381	SO 	1995	5	5	95ZZZX2125 	1	19950317	G	5320		BRACKET 			PIPER 	PA28 	PA28181 	7102807	SO 										STEP SUPPORT	BROKEN 	B			BIOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	3024M	5896 				287890286				WHILE DOING SB 977, PULLED UP BAGGAGE FLOOR, FOUND AFT STEEL STEP SUPPORT BRACKET SEVERELY CORRODED. WHEN REMOVED, FOUN	D STEEL SUPPORT BRACKET BROKEN AND EMPENNAGE TO FUSELAGE BULKHEAD WITH 2 FOOT CRACK IN LOWER RADIUS. SUSPECT BATTERY AC	ID STARTED CORROSION PROCESS. REPLACE WITH BRACKET OF DIFFERENT MATERIAL.				1	L	7	1 	3O				2A13 					 
1995050500382	19950505	00382	SO 	1995	5	5	95ZZZX2126 	1	19950301	G	5260	4131400	ARM ASSY 			PIPER 	PA31 	PA31350 	7103110	SO 										STEP BRACKET	CORRODED 	B			BIOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	64JP	4272 				317632156				BOTTOM STOP, FORWARD BRACKET BROKE INTO 2 PIECES, 2 INCHES FROM PIVOT BOLTS. INSPECTION FOUND SEVERE INTERGRANULAR CORR	OSION ON THE FORWARD LOWER STEP BRACKET THAT LEAD TO THIS FAILURE. NO OTHER CORROSION WAS FOUND ON THE LOWER DOOR OR ST	EPS. THIS IS NOT AN AREA PRONE TO TRAPPED WATER.				1	L	7	2 	3O				A20SO 					 
1995050500383	19950505	00383	SW 	1995	5	5	95ZZZX2127 	2	19950124	G	8530		RINGS 			CESSNA	195 	195B 	2073112	CE 	JACOBP	R755 	R755A2 	35006	SW 					ENGINE	EXCESS WORN 	D				O				OTHER 				A			FLAME/FIRE 			IN	INSP/MAINT 	1			NM	08	2164C					16149	31151			DURING HOT ENGINE START, A CARBURETOR FIRE RESULTED. FIRE EXTINGUISHED USING DRY CHEM. ENGINE WASHED DOWN AND FLOWN. E	XCESS OIL CONSUMPTION NOTED (1 GALLON PER HOUR). TEAR DOWN OF ENGINE REVEALED WORN PISTON RINGS AND GUMMED-UP INTAKE VA	LVES PLUS GRIT IN OIL. SUBMITTER RECOMMENDS TO NOT USE DRY CHEMICAL ON ENGINE FIRES.				1	H	7	1 	3R	3	R		A790 	TC237				 
1995050500385	19950505	00385	CE 	1995	5	5	95ZZZX2129 	1	19950412	G	7160	NAS39734	CLAMP 			CESSNA	150 	150K 	2071822	CE 										RT HEAT MUFF	FAILED 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			GL	23	5767G	5513 				15071267				THE HOSE CLAMP WAS THE 'SPRING RATCHET' TYPE INSTALLED BY CESSNA. THIS CLAMP CAME LOOSE IN-FLIGHT AND CAUSED CARBURETOR	 HEAT DUCT TO BECOME DIS-ENGAGED FROM THE HEAT MUFF. THE PILOT WAS UNABLE TO GET RID OF CARBURETOR ICE WHICH CAUSED THE	 ENGINE TO QUIT.				1	H	7	1 	3O				3A19 					 
1995050500386	19950505	00386	EA 	1995	5	5	95ZZZX2130 	2	19950225	G	8530	LW12416	CYLINDER 			CESSNA	172 	172P 	2072436	CE 	LYC 	O320 	O320D2J 	41508	EA 					NR 1 CYLINDER	RING BROKE 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			EA	25	99441	1021 				17276446	L1096439A			PILOT REPORTED POWER LOST. FOUND NR 1 CYLINDER HAD A BROKEN COMPRESSION RING. REPLACED WITH AN OVERHAULED CYLINDER, NE	W RINGS AND PISTON. RAN-UP OKAY.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995050500387	19950505	00387	SO 	1995	5	5	95ZZZX2131 	1	19950313	G	5751	4019015	SPAR 		4020023 	PIPER 	PA31 	PA31350 	7103110	SO 										RT AILERON	CRACKED 	B		A	IGXR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	711EB	7070 				317305049				FOUND RT AILERON SPAR AND RIB (INBOARD) CRACKED AT HINGE ATTACHMENT. THE RIB IS INSPECTABLE THROUGH THE AILERON SKIN CU	T-OUT FOR THE TAB PUSH/PULL ROD. REPLACED SPAR ASSY, RIB, AND NEW STYLE BRACKET, PN 74461-03 (REF. SB 974).					1	L	7	2 	3O				A20SO 					 
1995050500388	19950505	00388	SO 	1995	5	5	95ZZZX2132 	1	19950313	G	5751	4011800	RIB 		4020023 	PIPER 	PA31 	PA31350 	7103110	SO 										RT AILERON	CRACKED 	B			IGXR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	711EB	7070 				317305049				FOUND RT AILERON SPAR AND RIB (INBOARD) CRACKED AT HINGE ATTACHMENT. THE RIB IS INSPECTABLE THROUGH THE AILERON SKIN CU	T-OUT FOR THE TAB PUSH/PULL ROD. REPLACED SPAR ASSY, RIB, AND NEW STYLE BRACKET, PN 74461-03 (REF. SB 974).					1	L	7	2 	3O				A20SO 					 
1995050500390	19950505	00390	SW 	1995	5	5	95ZZZX2134 	1	19950315	G	3150	214175122111	SWITCH 			BELL 	412 	412 	1182202	SW 										PRESS-TO-TEST	DEFECTIVE 	B			BAQR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			EA	03	4UV				0192282	33199				IN THE TEST MODE OF THE CAUTION PANEL, NONE OF THE CAUTION LIGHTS ILLUMINATE EXCEPT FOR THE CAUTION PANEL LIGHT. WHEN A	N ACTUAL MALFUNCTION EXISTS, GET LIGHT AND A MASTER CAUTION LIGHT. EVERYTHING WORKS NORMALLY EXCEPT FOR THE PRESS-TO-TE	ST MODE. SUSPECT CAUSE: INTERNAL FAILURE OF PRESS-TO-TEST CIRCUITRY.				1	G	7	2 	4U				H4SW 					 
1995050500391	19950505	00391	SW 	1995	5	5	95ZZZX2135 	1	19950401	G	3150	214175122111	SWITCH 			BELL 	412 	412 	1182202	SW 										PRESS-TO-TEST	DEFECTIVE 	B			BAQR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			EA	03	4UV				683001	33199				IN THE TEST MODE OF THE CAUTION PANEL, NONE OF THE CAUTION LIGHTS ILLUMINATE EXCEPT FOR THE CAUTION PANEL LIGHT. WHEN A	N ACTUAL MALFUNCTION EXISTS. GET LIGHT AND A MASTER CAUTION LIGHT. EVERYTHING WORKS NORMALLY EXCEPT FOR THE PRESS-TO-TE	ST-MODE. SUSPECT CAUSE: INTERNAL FAILURE OF PRESS-TO-TEST CIRCUITRY.				1	G	7	2 	4U				H4SW 					 
1995050500392	19950505	00392	SW 	1995	5	5	95ZZZX2136 	1	19950401	G	3150	214175122111	SWITCH 			BELL 	412 	412 	1182202	SW 										PRESS-TO-TEST	DEFECTIVE 	B			BAQR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			EA	03	4UV				0489177	33199				IN THE TEST MODE OF THE CAUTION PANEL, NONE OF THE CAUTION LIGHTS ILLUMINATE EXCEPT FOR THE CAUTION PANEL LIGHT. WHEN A	N ACTUAL MALFUNCTION EXISTS GET LIGHT A ND A MASTER CAUTION LIGHT. EVERYTHING WORKS NORMALLY EXCEPT FOR THE PRESS-TO-TE	ST-MODE. SUSPECT CAUSE: INTERNAL FAILURE OF PRESS-TO-TEST CIRCUITRY.				1	G	7	2 	4U				H4SW 					 
1995050500393	19950505	00393	SW 	1995	5	5	95ZZZX2137 	1	19950401	G	3150	214175122111	SWITCH 			BELL 	412 	412 	1182202	SW 										PRESS-TO-TEST	DEFECTIVE 	B			BAQR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			EA	03	4UV				0893346	33199				IN THE TEST MODE OF THE CAUTION PANEL, NONE OF THE CAUTION LIGHTS ILLUMINATE EXCEPT FOR THE CAUTION PANEL LIGHT. WHEN A	N ACTUAL MALFUNCTION EXISTS. GET LIGHT AND A MASTER CAUTION LIGHT. EVERYTHING WORKS NORMALLY EXCEPT FOR THE PRESS-TO-TE	ST-MODE. SUSPECT CAUSE: INTERNAL FAILURE OF PRESS-TO-TEST CIRCUITRY.				1	G	7	2 	4U				H4SW 					 
1995050500394	19950505	00394	SW 	1995	5	5	95ZZZX2138 	1	19950401	G	3150	214175122111	SWITCH 			BELL 	412 	412 	1182202	SW 										PRESS-TO-TEST	DEFECTIVE 	B			BAQR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			EA	03	4UV				0594369	33199				IN THE TEST MODE OF THE CAUTION PANEL, NONE OF THE CAUTION LIGHTS ILLUMINATE EXCEPT FOR THE CAUTION PANEL LIGHT. WHEN A	N ACTUAL MALFUNCTION EXISTS. GET LIGHT AND A MASTER CAUTION LIGHT. EVERYTHING WORKS NORMALLY EXCEPT FOR THE PRESS-TO-TE	ST-MODE. SUSPECT CAUSE: INTERNAL FAILURE OF PRESS-TO-TEST CIRCUITRY.				1	G	7	2 	4U				H4SW 					 
1995050500395	19950505	00395	WP 	1995	5	5	95ZZZX2139 	1	19950320	G	3210	369A6107	FITTING 			HUGHES	369 	369D 	4470706	WP 										GEAR SKID TUBE	FAILED 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V	3998 				490487D				WHILE MOVING AIRCRAFT INTO THE HANGAR, GROUND HANDLING WHEEL 'POPPED' OFF. SUBSEQUENT INSPECTION REVEALED THE WHEEL FIT	TING ATTACHED TO THE SKID TUBE HAD FAILED. REMOVED AND REPLACED OLD FITTING.					1	G	7	1 	3U				H3WE 					 
1995050500396	19950505	00396	NE 	1995	5	5	95ZZZX2140 	1	19950312	G	5343	S6180631514	FITTING 			SKRSKY	S61 	S61A 	814210C	NE 										AFT MLG ATTACH	CRACKED 	B	S		JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	318Y	33911	5795 			61094				RIGHT REAR MAIN LANDING FUSELAGE FITTING FOUND CRACKED FROM BOLT HOLE. CRACK WAS ON INSIDE OF FORWARD EAR OF FITTING, A	ND WAS ABOUT 1 INCH LONG AND DID NOT GO THROUGH EAR.					2	G	7	2 	4U				H2EA 					 
1995050500397	19950505	00397	GL 	1995	5	5	95ZZZX2141 	2	19950328	G	7320	23033400	FILTER 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					PC AIR	DEFECTIVE 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			GL	03	541	3225 				711023D	833976			WHILE TROUBLESHOOTING AN N2 DROOP PROBLEM, FOUND PC AIR FILTER HAD SEVERAL FOLDS OF THE METAL FILTER ELEMENT BROKEN OFF,	 WITH MANY SMALL PIECES MISSING. PC AIR FILTER CLEANS SENSING AIR GOING INTO BENDIX FUEL CONTROL SYSTEM. GOVERNOR AND 	FUEL CONTROL HAD TO BE REPLACED DUE TO CONTAMINATION. SUBMITTER RECOMMENDS CLOSE INSPECTION OF ELEMENT DURING REGULAR 3	00-HOUR CLEANING OF FILTER. ALLISON IS ANXIOUS TO SEE AND INSPECT DAMAGED FILTER.			1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995050500398	19950505	00398	NE 	1995	5	5	95ZZZX2142 	1	19950329	G	6520	SB3151A1B1	BEARING 			SKRSKY	S61 	S61N 	8142104	NE 										INTERMED GEARBOX	FAILED 	D				A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			EA	05	612RM		1522 			61744				DURING A ROUTINE CROSS-COUNTRY FLIGHT, AN UNUSUAL VIBRATION WAS FELT BY THE FLIGHT CREW AND A PRECAUTIONARY LANDING WAS 	MADE. POST-FLIGHT INSPECTION FOUND THE OUTPUT HOUSING ON THE INTERMEDIATE GEARBOX WAS COMPLETELY BROKEN AROUND THE CIRC	UMFERENCE, AT A POINT JUST BEHIND THE SB 3151A1 BEARING. THIS BROKEN HOUSING NOW ROTATED WITH THE TAIL ROTOR DRIVE SHAF	T INSTEAD OF BEING A FIXED PART. SUSPECT BEARING FAILURE.			2	G	7	2 	4U				1H15 					 
1995050500399	19950505	00399	SW 	1995	5	5	95ZZZX2143 	1	19950315	G	6220	206011104109	PITCH HORN 			BELL 	206 	206L1 	1182107	SW 										M/R HUB	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	09	57441	8649 	2281 			45438				DURING A 100-HOUR INSPECTION, FOUND PITCH HORN ON M/R HUB CRACKED THROUGH AT GREASE FITTING HOLE AS INDICATED IN DRAWING	. OVER-TORQUE OF GREASE FITTING OR FATIGUE OF PART MAY BE THE RESULT OF CRACK.					1	G	7	1 	3U				H2SW 					 
1995050500400	19950505	00400	EU 	1995	5	5	95ZZZX2144 	1	19950330	G	6420	109013105111	TRUNNION 		109813102115	AGUSTA	A109 	A109K2 	0260502	EU 										T/R HUB	DAMAGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	911RX	7 			A40076	10017				POST-FLIGHT INSPECTION FOUND PLAY IN T/R HUB ASSY. END CAPS OF TRUNNION WERE REMOVED TO SHOW BURNED TEFLON DEBRIS, SOLD	ER, AND PRO-SEAL, AND ONE SLEEVE PULLED OFF TRUNNION OUTBOARD .0625 INCH. SUBMITTER STATES REDESIGN IS UNDER WAY.					1	G	7	2 	3U			RT	H7EU 					 
1995050500402	19950505	00402	WP 	1995	5	5	95ZZZX2146 	1	19950413	G	5610	269A2345011	SLAT ASSY 			HUGHES	269 	269C 	4470504	WP 										CANOPY	MISMFG 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	07	7511E	316 				S1693				THE NEW STYLE CANOPY SLAT (ALUMINUM) REPLACES THE FIBERGLASS SLATS. THE ALUMINUM SLAT APPEARS TO BE MANUFACTURED TOO WI	DE TO FIT PROPERLY ON THE CANOPY. THIS RESULTS IN THE SLAT BEING BOWED AT THE CENTER WHEN INSTALLED. THE CENTER SLAT S	UPPORT PULLED AWAY FROM THE SLAT, WHILE IN-FLIGHT, AT THE RIVET HOLES. SCHWEIZER WAS INFORMED OF THE PROBLEM AND SENT A	 REPLACEMENT PART. THERE IS NO SHIMMING PROCEDURE TO MAKE UP FOR THE EXCESS WIDTH OF THE SLAT ASSY.			1	G	7	1 	3O				4H12 					 
1995050500403	19950505	00403	NE 	1995	5	5	95ZZZX2147 	1	19950324	G	7500	0301027300	P2 PIPE 			SKRSKY	S76 	S76A 	8143006	NE 	TMECA 	ARRIEL	ARRIEL1S 	60030	NE 					FREE TURBINE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	65MS	1503 				760259	3516TEC			DURING APPLICATION OF SB 292 75 0193, (TU 247 A), PN 9562810760 CLAMP WAS REMOVED. SERIOUS CORROSION WAS FOUND ON THE P	2 AIR PIPE WHERE THE CLAMP ATTACHES TO THE PIPE. THE PIPE SUPPLIES COMPRESSOR DISCHARGE AIR WHICH IS EXTERNALLY ROUTED 	TO THE FREE TURBINE BEARING LABYRINTH SEAL. FAILURE OF THIS TUBE WILL CAUSE AN ENGINE FAILURE, POSSIBLY CATASTROPHIC IN	 NATURE. THE SB INCORPORATES AN IMPROVED STAINLESS STEEL CLAMP WHICH SHOULD ELIMINATE THE CORROSION PROBLEM. THE PURPO	SE FOR THE BULLETIN IS TO REDUCE MECHANICAL STRESSES AND INCREASE MECHANICAL RESISTANCE ON END OF THE PIPE, AS STATED BY	 THE MANUFACTURER.	1	G	7	2 	3U	3	U		H1NE 	E19EU				 
1995050500404	19950505	00404	GL 	1995	5	5	95ZZZX2148 	2	19950329	G	7323	23007506	GOVERNOR 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	MALFUNCTION 	B			EOOR	K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			AL	03	3115Y				24622	500716D	CAE830750			PILOT COMPLAINED THE ENGINE DROOPED AT HIGH POWER. REMOVED AND REPLACED GOVERNOR, CURED THE PROBLEM. UNIT SENT IN FOR 	REPAIR ON ALLISON REPORT NR A 160111.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995050500405	19950505	00405	WP 	1995	5	5	95ZZZX2149 	1	19950331	G	8011	369A455011	STARTER 			HUGHES	369 	369D 	4470706	WP 										ENGINE	MALFUNCTION 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R		355 			1151D				AIRCRAFT HAS HAD INTERMITTENT STARTER MOTORING PROBLEMS. ALL SYSTEMS WORKING, BUT IT WOULD NOT MOTOR WHEN START BUTTON 	WAS DEPRESSED AND NEXT TIME IT WOULD OPERATE FOR SEVERAL DAYS. FINAL REPLACEMENT OF STARTER SEEMS TO HAVE REMEDIED THE 	PROBLEM. UNIT SENT IN FOR REPAIR.				1	G	7	1 	3U				H3WE 					 
1995050500406	19950505	00406	WP 	1995	5	5	95ZZZX2150 	1	19950331	G	1100	369N2666505	CONTROL 			HUGHES	369 	369D 	4470706	WP 										M/R MIXER	DATA PLATE GONE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION, DATA PLATE WAS FOUND MISSING. THESE ARE TINFOIL DATA PLATES GLUED IN PLACE AND ARE OFTEN MISS	ING. SUBMITTED PAPER WORK FOR REPLACEMENT DATA PLATE.					1	G	7	1 	3U				H3WE 					 
1995050500407	19950505	00407	WP 	1995	5	5	95ZZZX2151 	1	19950331	G	1100	369D2360503	STABILZIER 			HUGHES	369 	369D 	4470706	WP 										VERT STAB	DATA PLATE GONE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 			0575	490496D				DURING ANNUAL INSPECTION, DATA PLATE WAS FOUND MISSING. THESE ARE TINFOIL DATA PLATES GLUED IN PLACE AND ARE OFTEN MISS	ING. SUBMITTED PAPER WORK TO GET A NEW DATA PLATE.					1	G	7	1 	3U				H3WE 					 
1995050500408	19950505	00408	SW 	1995	5	5	95ZZZX2152 	1	19950401	G	7100	70009H000V320	HOSE 			BELL 	206 	206B 	1181511	SW 										POWER PLANT	CORRODED 	B			PN5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	35Q					3073				MOISTURE IS TRAPPED BETWEEN FIRE SLEEVE AND ALUMINUM FITTINGS AND CAUSES CORROSION OF THE FITTINGS AND FIRE SLEEVE.						1	G	7	1 	3U				H2SW 					 
1995050500409	19950505	00409	SW 	1995	5	5	95ZZZX2153 	1	19950130	G	5311	206031302187	FRAME 			BELL 	206 	206B3 	1181506	SW 										FWD RT ENG MOUNT	CRACKED 	B		A	PN5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	35Q	8338 				3073				THE FRAME WAS FOUND CRACKED IN THE RADIUS AFT OF THE FORWARD RIGHT ENGINE MOUNT. THE CRACK EXTENDED 1.5 INCHES OUTBOARD	 AND 3 INCHES INBOARD OF THE MOUNT BOLT HOLE AND FORWARD 2.5 INCHES AT THE OUTBOARD END. THE STIFFENERS AT BOTH FORWARD	 ENGINE MOUNTS WERE ALSO CRACKED. UPON FURTHER INSPECTION, FRAME WAS ALSO FOUND CRACKED AT THE LEFT FORWARD ENGINE MOUN	T. SUSPECT CAUSES INCLUDE FLEXING THE ENGINE MOUNT TO FACILITATE ENGINE REMOVAL AND INSTALLATION INSTEAD OF LOOSENING T	HE MOUNT HARDWARE OPERATING THE AIRCRAFT FOR EXTENDED PERIODS OF TIME WITH LOOSE ENGINE MOUNT HARDWARE.		1	G	7	1 	3U				H2SW 					 
1995050500410	19950505	00410	NE 	1995	5	5	95ZZZX2154 	2	19950124	G	7230	496706	DISK 			SKRSKY	S64 	S64A 	8142504	NE 	PWA 	JFTD12	JFTD12A5A 	52047	NE 					ENGINE	PITTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09		1536 	604 		8V1080		496706			P AND W SB 1508, REQUIRES ALL ENGINES TO BE COMPLETELY DISASSEMBLED TO CONDUCT A CORROSION INSPECTION EVERY 7 YEARS. SE	RIOUS CORROSION PITTING FOUND WHEN CONVERTING MILITARY T73-P-1 OR T73-P-700 ENGINES TO COML. USE. DISK FAILURE CAN OCCU	R IF CORROSION INSPECTION NOT C/W. EXAMPLE SUBMITTED.				2	G	7	2 	4U	4	U		H1EA 	E15EA				 
1995050500411	19950505	00411	WP 	1995	5	5	95ZZZX2155 	1	19950331	G	1100	369D23500101	TAIL BOOM 			HUGHES	369 	369D 	4470706	WP 										AIR FRAME	DATA PLATE GONE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION, THE DATA PLATE WAS FOUND MISSING. THESE ARE TINFOIL DATA PLATES GLUED IN PLACE AND ARE OFTEN 	MISSING. SUBMITTED PAPER WORK FOR REPLACEMENT DATA PLATE.					1	G	7	1 	3U				H3WE 					 
1995050500412	19950505	00412	GL 	1995	5	5	95ZZZX2156 	2	19950315	G	7250	A6871505	BEARING 		C20B 	HILLER	UH12 	UH12E 	4360122	WP 	ALLSN 	250C 	250C20B 	03013	GL 					NR 5	FAILED 	B			HDNR	O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	03	114HA	265 			CAT35461	HA3014				NR 5 BEARING FAILED AT THE BALLS RETAINER. CHIP LIGHT CAME ON IN-FLIGHT. NO CAUSE AT THE TIME. THIS PART IS A P.M.A. 	F.A.A. APPROVED.					1	G	7	1 	3O	3	U		4H11 	E4CE				 
1995050500413	19950505	00413	SW 	1995	5	5	95ZZZX2157 	1	19950411	G	3030		HEATER 			BELL 	412 	412 	1182202	SW 										STATIC PORT	SHORTED 	D				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			EA	03	4UV					33199				PILOT AND CREW NOTICED ELECTRICAL FUMES IN COCKPIT AND CABIN. FOUND SHORTED WIRE. DISABLED SYSTEM AND DEFERRED WIRE TO	 STATIC PORT HEATER (PILOT SIDE) AIRCRAFT RESTRICTED TO V.F.R. FLIGHT UNTIL REPAIRS ARE MADE.					1	G	7	2 	4U				H4SW 					 
1995050500414	19950505	00414	WP 	1995	5	5	95ZZZX2158 	1	19950411	G	3340	369D236603	BRACKET 		369D23600503	HUGHES	369 	369D 	4470706	WP 										ANTI-COLL LIGHT	CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 			0575	490496D				DURING ANNUAL INSPECTION ON CUSTOMER AIRCRAFT, THE ANTI-COLLISON STROBE LIGHT BRACKET WAS FOUND CRACKED. REPAIRED ON 33	7.					1	G	7	1 	3U				H3WE 					 
1995050500415	19950505	00415	WP 	1995	5	5	95ZZZX2159 	1	19950411	G	5553	MS2R50H05036	BOLT 		369D23600503	HUGHES	369 	369D 	4470706	WP 										VERT STAB	CORRODED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 			0575	490496D				DURING ANNUAL INSPECTION OF CUSTOMER AIRCRAFT, THE VERTICAL STABILIZER ATTACH BOLTS WERE FOUND BADLY CORRODED. REPLACED	 BOLTS AND WASHERS.					1	G	7	1 	3U				H3WE 					 
1995050500416	19950505	00416	WP 	1995	5	5	95ZZZX2160 	1	19950411	G	7800	369A823611	CUSHION 			HUGHES	369 	369D 	4470706	WP 										EXHAUST	DETERIORATED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y					490496D				DURING ANNUAL ON CUSTOMER AIRCRAFT, THE UPPER EXHAUST STACK CUSHION BRACKET ASSEMBLY WAS FOUND WITH THE ATTACH RIVET ALM	OST CUT IN HALF BY THE SPRING AND THE SPRING BADLY CHAFED AND THE CUSHIONS ALMOST NON-EXISTANT. PART WAS REPLACED.					1	G	7	1 	3U				H3WE 					 
1995050500417	19950505	00417	WP 	1995	5	5	95ZZZX2161 	1	19950411	G	7110	51L13XAA	LATCH 			HUGHES	369 	369D 	4470706	WP 										ENGINE DOOR	WORN 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION OF CUSTOMER AIRCRAFT, DISCOVERED ENGINE DOORS WERE QUITE LOOSE. INSPECTION FOUND ALL THREE LAT	CHES WERE ADJUSTED TO THE LIMIT AND PIVOT PINS WERE WORN QUITE BADLY. REPLACED PARTS.					1	G	7	1 	3U				H3WE 					 
1995050500418	19950505	00418	WP 	1995	5	5	95ZZZX2162 	1	19950411	G	6220	369A1231	ROLLER 		369D21200 	HUGHES	369 	369D 	4470706	WP 										M/R HUB	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	2687 			1313	490496D				ALL 5 M/R DROOP ROLLERS HAD THE TEFLON BEARING MATERIAL MISSING AS FOUND ON CUSTOMER AIRCRAFT. THE ROTOR HUB WAS EXTREM	ELY DIRTY AND COLLECTION OF DIRT AND GRIME QUITE POSSIBLY CONTRIBUTED TO THIS CONDITION. PARTS REPLACED.					1	G	7	1 	3U				H3WE 					 
1995050500419	19950505	00419	WP 	1995	5	5	95ZZZX2163 	1	19950411	G	6710		CYCLIC 			HUGHES	369 	369D 	4470706	WP 										FLT CONTROL	MISRIGGED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y					490496D				DURING ANNUAL OF CUSTOMER AIRCRAFT, PILOT HAD MENTIONED THE CYCLIC STICK WAS OFF CENTER TO THE LEFT. WHEN HE DELIVERED 	THE ACFT, RIGGING WAS BEYOND LIMITS TO THE LEFT. ACFT WAS RERIGGED.					1	G	7	1 	3U				H3WE 					 
1995050500420	19950505	00420	WP 	1995	5	5	95ZZZX2164 	1	19950411	G	7910	369A83013	OIL TANK 			HUGHES	369 	369D 	4470706	WP 										VENT LINE	BRACKET CRACKED 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION ON CUSTOMER ACFT, THE VENT LINE FITTING BRACKET ON THE OIL TANK WAS FOUND CRACKED. PART WAS SE	NT IN FOR REPAIR.					1	G	7	1 	3U				H3WE 					 
1995050500421	19950505	00421	WP 	1995	5	5	95ZZZX2165 	1	19950411	G	2810	369H8108	VALVE 			HUGHES	369 	369D 	4470706	WP 										EMERG FUEL VENT	INOPERATIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION ON CUSTOMER ACFT, THE EMERGENCY FUEL VENT 'TROMBONE' VALVE WAS REMOVED FOR INSPECTION AND WAS F	OUND NOT TO FUNCTION PROPERLY. PART WAS SENT IN FOR REPAIR.					1	G	7	1 	3U				H3WE 					 
1995050500422	19950505	00422	GL 	1995	5	5	95ZZZX2166 	2	19950417	G	7230	6890550	COMPRESSOR 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	STALLS 	B			EOOR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	3115Y	8437 	2785 		CAC31132	500116D	CAE832750			COMPRESSOR STALLS WITH SMALL, BUT RAPID POWER CHANGES. UNIT SENT IN FOR REPAIR.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995050500423	19950505	00423	WP 	1995	5	5	95ZZZX2167 	1	19950411	G	6720	369D27521	SPRING 			HUGHES	369 	369D 	4470706	WP 										T/R BUNGEE	WORN 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION OF CUSTOMER ACFT, THE T/R BUNGEE SPRING AND EYE BOLTS WERE WORN BEYOND LIMITS FROM CHAFING. PA	RTS REPLACED.					1	G	7	1 	3U				H3WE 					 
1995050500424	19950505	00424	WP 	1995	5	5	95ZZZX2168 	1	19950402	G	7160	369D28094501	INLET FILTER 			HUGHES	369 	369D 	4470706	WP 										ENGINE	CRACKED 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL, INLET FILTER WAS FOUND CRACKED AT ATTACH FLANGE. THIS IS A PLASTIC PIECE.						1	G	7	1 	3U				H3WE 					 
1995050500425	19950505	00425	GL 	1995	5	5	95ZZZX2169 	2	19950407	G	7323	23007506	GOVERNOR 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y		711 			500716D	CAE830750			THE GOVERNOR WOULD NOT HOLD RPM WITH SLIGHT POWER CHANGES. THIS UNIT HAS BEEN SENT IN FOR REPAIR 2 TIMES BEFORE IN THE 	LAST 239.8 HOURS FOR THE SAME PROBLEM. SEE ALLISON 250 REPORT A160113.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995050500426	19950505	00426	WP 	1995	5	5	95ZZZX2170 	1	19950407	G	6710	369A7010501	UNILOCK 			HUGHES	369 	369D 	4470706	WP 										M/R CONTROL	LEAKING 	B			EOOR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 			3061	490496D				DURING ANNUAL INSPECTION, THE UNILOCK WAS FOUND LEAKING. UNIT SENT IN FOR REPAIR.						1	G	7	1 	3U				H3WE 					 
1995050500427	19950505	00427	GL 	1995	5	5	95ZZZX2171 	2	19950406	G	7240	6871486	COMBUSTION LINER			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					TURBINE	CRACKED 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y				127481	490496D	CAE831718			DURING INSPECTION, FOUND 2 SPOTS BURNED THROUGH AND CRACKED AT 6:30 AND 2:00, 1 INCH FORWARD OF SKIRT LOUVERS.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995050500428	19950505	00428	WP 	1995	5	5	95ZZZX2172 	1	19950411	G	2550	143232	HOOK CABLE 			HUGHES	369 	369D 	4470706	WP 										CARGO HOOK	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL ON CUSTOMER ACFT, THE CARGO HOOK RELEASE CABLE HOUSING WAS FOUND TO HAVE DISINTEGRATED ALMOST FULL LENGTH.	 REPLACED PART.					1	G	7	1 	3U				H3WE 					 
1995050500429	19950505	00429	WP 	1995	5	5	95ZZZX2173 	1	19950411	G	6710	369H657371	COVER 			HUGHES	369 	369D 	4470706	WP 										CYCLIC	DETERIORATED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION, THE CYCLIC CONTROL COVER (BOOT) WAS FOUND TO BE ROTTED TO A POINT WHERE, ASIDE FROM THE PLASTI	C EDGES AND PLASTIC REINFORCEMENT GROMMETS, THERE WAS NOTHING LEFT. REPLACED PART. THIS IS A CUSTOMER MACHINE.					1	G	7	1 	3U				H3WE 					 
1995050500430	19950505	00430	WP 	1995	5	5	95ZZZX2174 	1	19950410	G	5320	369D23040	BRACKET 			HUGHES	369 	369D 	4470706	WP 										WHIP DAMPER	CHAFED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION WHILE INVESTIGATING A NOISE IN THE WHIP DAMPER AREA, DISCOVERED THE WHIP DAMPER BRACKET WAS BAD	LY CHAFED. THE BRACKET IS COVERED WITH WHAT LOOKS LIKE AUTOMOTIVE BELT DRESSING COMPOUND. PART WAS REPLACED ALONG WITH	 THE WHIP DAMPER.				1	G	7	1 	3U				H3WE 					 
1995050500518	19950505	00518	EA 	1995	5	5	95ZZZX2175 	2	19950406	G	8530		CYLINDER 			DOUG 	DC3 	DC3C 	3021457	WP 	WRIGHT	R1820 	R182022 	67020	EA 					ENG NR 1 CYL 6	FAILED 	H				A	E			UNSCHED LANDING 	ENGINE SHUTDOWN 			E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	CR	CRUISE 	1			WP	13	99131	6128 	1128 			18949	73469			LEFT ENGINE RAN SLIGHTLY ROUGH AT CRUISE ALTITUDE (5,000 FEET). NOTED OIL LEAK AT NR 6 CYLINDER POSITION. FEATHERED LT	 ENGINE AND RETURNED TO HONOLULU. AFTER LANDING, FOUND NR 6 CYLINDER FAILURE. (METAL PARTICLES (ALUMINUM) FOUND IN OIL	 SCREEN. REMOVED ENGINE. NO RECOMMENDATIONS FOR THIS PROBLEM.				2	L	7	2 	4R	4	R		A669 	TC154				 
1995050500519	19950505	00519	SO 	1995	5	5	95ZZZX2176 	2	19950414	G	8520		CYLINDER 			BEECH 	58 	58 	1152740	CE 	CONT 	O520 	IO520C 	17032	SO 					CYLINDER BASE	STUD SHEARED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	05	111AW	1637 				TH841	561631			PILOT REPORTED OIL LEAK. UPON INSPECTION, 3 UPPER CYLINDER BASE STUDS FOUND SHEARED. REMOVED CYLINDER AND NOTICED CASE	 CRACKED AT LOWER RIGHT STUD.					1	L	7	2 	3O	3	O		3A16 	E5CE				 
1995050500520	19950505	00520	CE 	1995	5	5	95ZZZX2177 	1	19950413	G	2460	4532	FUSE HOLDER 			BEECH 	200 	200BEECH 	1152920	CE 										BUS BAR	SCREWS WRONG 	B		A	AHTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	11	743R					BB729				DURING ROUTINE MAINTENANCE, NOTED SOME OF THE SCREWS THAT ATTACHED THE ELECTRICAL LEADS TO THE PN 4532 FUSE HOLDERS, WHI	CH ARE ON THE PN 50-369101-125 (BUS BAR), WERE TOO LONG. THIS CONDITION CREATES THE POTENTIAL FOR AN ELECTRICAL SHORT.					1	L	7	2 	4T				A24CE 					 
1995050500521	19950505	00521	SO 	1995	5	5	95ZZZX2178 	1	19950323	G	3252		ROD END 			PIPER 	PA28 	PA28R201 	7102816	SO 										SHIMMY DAMPER	WRONG PART 	B	P		OG5R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	21	806ND					2837009				DURING RAMP CHECK, FOUND SHIMMY DAMPER SHAFT ROD END BENT. FOUND CAUSE TO BE INCORRECT SHAFT INSTALLED. SHAFT LENGTH S	HOULD BE APPROXIMATELY 6.450 INCHES WITHOUT ROD END. SHAFT INSTALLED WAS APPROXIMATELY 6.950 INCHES (LONGER SHAFTS ARE 	FOR PA-28-161 SHIMMY DAMPERS). INCORRECT SHAFT INSTALLATION IN EITHER MODEL LIMITS STEERING TRAVEL.				1	L	7	1 	3O				2A13 					 
1995050500524	19950505	00524	SW 	1995	5	5	95ZZZX2181 	1	19950318	G	3213	9010	STRUT 			BBAVIA	7 	7GCAA 	21101N8	SW 										THREAD CONNECT	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	17	9692S	3923 				126				OLEO STRUT DEFECTIVE AT THREADED CONNECTION.						1	H	7	1 	3O				A759 					 
1995050500525	19950505	00525	EA 	1995	5	5	95ZZZX2182 	2	19950224	G	8530	LW17540RW	VALVE 			CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					NR 3 CYL EXH	FAILED 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			GL	17	64373	1350 				17265201	3794427A			DURING FLIGHT, ENGINE STARTED RUNNING ROUGH, ENGINE FAILED ON LANDING. NR 3 CYLINDER VALVE EXHAUST FAILED. REPLACED/OV	ERHAULED CYLINDER. AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995050500526	19950505	00526	EA 	1995	5	5	95ZZZX2183 	2	19950412	G	8530	LW12416	CYLINDER 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					NR 2	CRACKED 	B			LCPS	K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			SO	17	38897	2410 	160 			287716288	L780139A			ENGINE ROUGH. FOUND NR 2 CYLINDERS CRACKED WHERE HEAD AND BARREL ATTACH.						1	L	7	1 	3O	3	O		2A13 	E274				 
1995050500527	19950505	00527	CE 	1995	5	5	95ZZZX2184 	1	19950406	G	7922	53E19600	VALVE 			CESSNA	177 	177RG 	2073709	CE 										THERMO BYPASS	NUT MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	2530V					177RG0604				DURING COMPLIANCE WITH LYCOMING SB 518A DATED 2-3-95, THE CRIMP NUT ON THE THERMOSTATIC BYPASS VALVE WAS FOUND MISSING.						1	H	7	1 	3O				A20CE 					 
1995050500528	19950505	00528	SO 	1995	5	5	95ZZZX2185 	1	19950321	G	2750	63900174	BUSHING 			PIPER 	PA28 	PA28R201 	7102816	SO 										FLAP HANDLE	WORN 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	806ND	953 				2837009				FOUND FLAP HANDLE HORN HOLE AND BUSHING WORN. BUSHING WAS INSTALLED PER PIPER SB 965 ON 11-14-93. BUSHING STILL WEARS 	ON HORN REQUIRING HORN/HANDLE REPLACEMENT. SUGGEST BALL BEARING OR SWAGABLE BUSHING TO PREVENT HORN DAMAGE.					1	L	7	1 	3O				2A13 					 
1995050500529	19950505	00529	EA 	1995	5	5	95ZZZX2186 	2	19950411	G	8530	LW18289	CYLINDER 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					CYLINDER BARREL	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	96082	52 				15286004	L2498015			CRACK FOUND DURING AN INSPECTION TO FIND AN OIL LEAK. LOCATION OF CRACK IS AT THE BOTTOM PORTION OF CYLINDER BARREL, 3.	75 INCHES FROM BOTTOM OF FLANGE. THE CRACK IS APPROXIMATELY 2 INCHES LONG AND EXTENDS PARALLEL TO COOLING FINS.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995050500530	19950505	00530	CE 	1995	5	5	95ZZZX2187 	1	19950217	G	3230	08421211	PUSH-PULL TUBE 			CESSNA	310 	310K 	2074228	CE 										NLG	DAMAGED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	17	7017L					310K0117				NOSE GEAR PUSH-PULL TUBE PROBABLY DAMAGED DURING TOWING OR HARD LANDING ON THE NOSE GEAR. THE PUSH-PULL TUBE REPLACEMEN	T RECEIVED FROM CESSNA AND INSTALLED INTO AIRCRAFT, APPEARS TO BE STRONGER COMPARED TO THE REMOVED PUSH-PULL TUBE.					1	L	7	2 	3O				3A10 					 
1995050500531	19950505	00531	SO 	1995	5	5	95ZZZX2188 	2	19950413	G	8530		CYLINDER 			CESSNA	402 	402B 	207590P	CE 	CONT 	O520 	TSIO520E 	17040	SO 					CYL NR 5	CRACKED 	C				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			GL	17	3748C		1030 			402B606	183845R			AFTER TAKEOFF, LEFT ENGINE STARTED VIBRATING. ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO THE AIRPORT. INSPECTION RE	VEALED A CRACK IN THE NR 5 CYLINDER. SINCE OVERHAULED CYLINDERS HAVE HIGH TOTAL TIME, THEY ARE MORE LIKELY TO CRACK DUE	 TO AGE AND STRESS. RECOMMEND USING NEW CYLINDERS AT OVERHAUL TO REDUCE RECURRENCE OF THIS PROBLEM.				1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995050500532	19950505	00532	SO 	1995	5	5	95ZZZX2189 	2	19950310	G	7322	30764	FLOAT 	FACET 	MA45 	CESSNA	182 	182Q 	2072732	CE 	CONT 	O470 	O470U 	17026	SO 					CARBURETOR	FAILED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	17	182HM	1077 			C002042	18266720	467536			AFTER FINDING A 4 FOOT DIAMETER FUEL STAIN ON THE FLOOR AND FUEL DRIPPING FROM COWLING, INVESTIGATION DISCOVERED THE FLO	AT RIGHT PONTOON SOLDER JOINT HAD BROKE ALLOWING THE PONTOON TO COME FREE FROM THE FLOAT LEVER AND HOLD THE NEEDLE OFF I	TS SEAT. RECORDS INDICATE THAT AT ENGINE OVEHAUL, CARUBURETOR WAS OVERHAULED, BUT NO MENTION OF FLOAT REPLACEMENT. MAN	UFACTURE DATE OF FLOAT: 4-84.			1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995050500533	19950505	00533	CE 	1995	5	5	95ZZZX2190 	1	19950413	G	5540	51915261	HINGE BRACKET 			CESSNA	402 	402B 	207590P	CE 										RUDDER	MISMANUFACTURED 	E				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	19	1547T					402B0314				OBTAINED REPLACEMENT HINGE BRACKET ASSY FROM CESSNA DISTRIBUTOR. PART WAS MIS-DRILLED APPARENTLY BY CESSNA FACTORY. TH	IS PART DID NOT MEET MINIMUM EDGE DISTANCE PER AC 43.13, THE HOLES DID NOT MATCH THE AIRPLANE, AND THE UNIT WAS ASSEMBLE	D IMPROPERLY FROM THE FACTORY.				1	L	7	2 	3O				A7CE 					 
1995050500534	19950505	00534	EA 	1995	5	5	95ZZZX2191 	2	19950419	G	8530	SL10301AZP	CYLINDER 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					HEAD	MISMANUFACTURED 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	17	48670					15283359				NEW SUPERIOR CYLINDERS WERE INSTALLED AT ROUTINE OVERHAUL. AT FIRST OIL CHANGE, SIGNIFICANT AMOUNTS OF ALUMINUM WERE FO	UND IN THE OIL FILTER. AFTER 5 MORE FLIGHT HOURS, THE FILTER WAS AGAIN INSPECTED, MORE ALUMINUM WAS FOUND. THE ENGINE 	WAS DISASSEMBLED AND INSPECTED. IT WAS FOUND THE OUTER SPRINGS (VALVE) WERE RUBBING AGAINST THE SPRING POCKETS, REMOVIN	G ALUMINUM FROM THE INSIDE OF THE HEAD CASTING. THIS CONDITION WAS FOUND IN SEVERAL OTHER ENGINES WITH SUPERIOR MILLENI	UM O-235-L2C CYLINDERS.		1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995050500535	19950505	00535	SO 	1995	5	5	95ZZZX2192 	2	19950404	G	7322		VENTURI 	FACET 		CESSNA	172 	172 	2072402	CE 	CONT 	O300 	O300D 	17022	SO 					CARBURETOR	MISINSTALLED 	D				K				NONE 				E	R	W	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	INADEQUATE Q C 	IN	INSP/MAINT 	1			GL	09	1706F	100 				17255101	34670D6D			ON TWO SEPARATE AIRCRAFT WITH ENGINE ROUGHNESS, FOUND ONE PIECE VENTURI INSTALLED INCORRECTLY WITH THE NOTCH IN THE VENT	URI NOT ALIGNED WITH THE NOZZLE. THIS MISALIGNMENT SEEMS TO CAUSE AN EXTREMELY RICH RUNNING ENGINE. THE MECHANICS ARE 	NOT OBSERVING THE ALIGNMENT AND ARE PROBABLY NOT USING THE OVERHAUL MANUAL. THIS PROBLEM COULD CAUSE ENGINE OPERATION/P	OWER TO NOT BE ADEQUATE FOR SAFE OPERATION.			1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995050500536	19950505	00536	CE 	1995	5	5	95ZZZX2193 	1	19950401	G	7920		HOSE 			BEECH 	55 	E55 	1152732	CE 										ENGINE	DETERIORATED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	88MB	2881 				TE844				DURING ANNUAL INSPECTION, NOTED HOSES ON BOTH ENGINES AND BRAKE HOSES WERE DETERIORATING. HOSES ON RIGHT ENGINE WERE DA	TED 1983, AND HOSES ON LEFT ENGINE AND BRAKE HOSES WERE DATED 1970. FUEL AND OIL HOSES WERE DETERIORATED BY FRAYING AND	 CORROSION. SUGGEST CLOSE INSPECTION OF HOSES AND FOLLOWING RECOMMENDED REPLACEMENT TIMES. THESE HOSES HAVE A REPLACEM	ENT TIME OF 5 YEARS OR AT ENGINE OVERHAUL.			1	L	7	2 	3O				3A16 					 
1995050500596	19950505	00596	WP 	1995	5	5	95ZZZX2196 	1	19950411	G	5210		DOOR 			HUGHES	369 	369D 	4470706	WP 										CABIN	OUT OF RIG 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y					490496D				ALL CABIN DOORS ON CUSTOMER AIRCRAFT NEEDED TO BE RIGGED ON THE LATCH BLOCKS. THE DOORS WERE QUITE DIFFICULT TO OPEN AN	D CLOSE.					1	G	7	1 	3U				H3WE 					 
1995050500597	19950505	00597	WP 	1995	5	5	95ZZZX2197 	1	19950411	G	5330		SKIN 			HUGHES	369 	369D 	4470706	WP 										INLET FAIRING	CRACKED 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y					490496D				DURING ANNUAL INSPECTION ON CUSTOMER AIRCRAFT, THE FUSELAGE WAS FOUND CRACKED AROUND THE NUTPLATES FOR THE FORWARD MOST 	ATTACH POINT OF THE FORWARD ENGINE INLET FAIRING. OLD DN25 BRACKETS BROKEN OUT ALSO.					1	G	7	1 	3U				H3WE 					 
1995050500598	19950505	00598	WP 	1995	5	5	95ZZZX2198 	1	19950411	G	7720	369H412651	HARNESS 			HUGHES	369 	369D 	4470706	WP 										TOT	DETERIORATED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL ON CUSTOMER AIRCRAFT, THE TOT HARNESS LEAD WAS FOUND WITH THE OUTER INSULATION SLEEVE DETERIORATED TO A PO	INT WHERE A LIGHT RUB WOULD REMOVE IT FROM THE WIRES. PART WAS REPLACED.					1	G	7	1 	3U				H3WE 					 
1995050500599	19950505	00599	WP 	1995	5	5	95ZZZX2199 	1	19950411	G	5350	369A8128	FAIRING 			HUGHES	369 	369D 	4470706	WP 										FUEL VENT	BROKEN 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y	4350 				490496D				DURING ANNUAL INSPECTION ON CUSTOMER AIRCRAFT, DISCOVERED UPPER FUEL VENT FAIRING BROKEN. REPLACED PART.						1	G	7	1 	3U				H3WE 					 
1995011300330	19950113	00330	NE 	1995	1	13	95ZZZX220 	1	19950104	G	7900		BREATHER 			CONAER	LA4 	LA4200 	5110310	NE 										FRONT NOSE COWL	ICE BLOCKED 	G		A		A				UNSCHED LANDING 				K			FLUID LOSS 			CR	CRUISE 	1			GL	15	2FOR					568				AIRCRAFT DEPARTED INL ON A MINUS 9 DEGREE FAHRENHEIT DAY. OIL BREATHER PLUGGED WITH ICE, FRONT OIL SEAL BLEW OUT ALONG 	WITH ALL THE ENGINE OIL. AIRCRAFT WAS SUBSTANTIALLY DAMAGED DURING 'OFF-FIELD' LANDING. AD 64-17-05 IS NOT APPLICABLE 	BECAUSE BREATHER HAS A 'NICKLE SLOT' CUT IN IT DURING MANUFACTURE, BUT SLOT WAS FILLED WITH ICE. SUBMITTER RECOMMENDS M	OVING BREATHER LINE AND AIR/OIL SEPARATOR TO A WARMER PART OF THE ENGINE COWLING. IT IS CURRENTLY MOUNTED IN THE FRONT 	NOSE COWL WHICH PROVIDES NO PROTECTION FROM THE ELEMENTS.		1	H	7	1 	3O				1A13 					 
1995050500614	19950505	00614	SW 	1995	5	5	95ZZZX2215 	1	19950411	G	6410	212010750105	BLADE 		212011701001	BELL 	212 	212 	1181420	SW 										T/R ASSY	THREADS STRIPPED	B			ALGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03					A9569					FOUND CRACKED SCREW HOLDING BALANCE WEIGHTS AND THREADS ARE STRIPPED IN BLADE THAT SECURED SCREW. BETTER QUALITY CONTRO	L BY MANUFACTURER.					1	G	7	1 	4U				H4SW 					 
1995050500615	19950505	00615	SW 	1995	5	5	95ZZZX2216 	1	19950320	G	5302	206033426001	SUPPORT ASSY 		206033004045	BELL 	206 	206L1 	1182107	SW 										TAIL BOOM	DEFECTIVE 	B			ALGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	3188P				A0KP00954	45778				FOUND ON INCOMING INSPECTION, 90 DEGREE GEARBOX ALIGNMENT HOLES IN SUPPORT, ELONGATED BEYOND LIMITS. HOLES HAVE A VERY 	TIGHT TOLERANCE (.253 INCH - .255 INCH) AND COME FROM FACTORY AT .254 INCH. A STEEL PIN GOING THROUGH CAST ALUMINUM MAY	 AGGRAVATE THE PROBLEM.				1	G	7	1 	3U				H2SW 					 
1995050500616	19950505	00616	SW 	1995	5	5	95ZZZX2217 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	366AL		522 			51470				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 522.0.				1	G	7	1 	3U				H2SW 					 
1995050500617	19950505	00617	SW 	1995	5	5	95ZZZX2218 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	366AL		522 			51470				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 522.0.				1	G	7	1 	3U				H2SW 					 
1995050500618	19950505	00618	SW 	1995	5	5	95ZZZX2219 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D		425 			45280				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 425.3.				1	G	7	1 	3U				H2SW 					 
1995050500619	19950505	00619	SW 	1995	5	5	95ZZZX2220 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D		425 			45280				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 425.3.				1	G	7	1 	3U				H2SW 					 
1995050500620	19950505	00620	SW 	1995	5	5	95ZZZX2221 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3185P		326 			45775				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 326.3.				1	G	7	1 	3U				H2SW 					 
1995050500621	19950505	00621	SW 	1995	5	5	95ZZZX2222 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3185P		326 			45775				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 326.3.				1	G	7	1 	3U				H2SW 					 
1995050500622	19950505	00622	SW 	1995	5	5	95ZZZX2223 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27483		426 			45230				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 425.9.				1	G	7	1 	3U				H2SW 					 
1995050500623	19950505	00623	SW 	1995	5	5	95ZZZX2224 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27483		426 			45230				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 425.9.				1	G	7	1 	3U				H2SW 					 
1995050500624	19950505	00624	SW 	1995	5	5	95ZZZX2225 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A		475 			45256				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 475.0.				1	G	7	1 	3U				H2SW 					 
1995050500625	19950505	00625	SW 	1995	5	5	95ZZZX2226 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A		475 			45256				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 475.0.				1	G	7	1 	3U				H2SW 					 
1995050500626	19950505	00626	SW 	1995	5	5	95ZZZX2227 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	115AL		555 			2383				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 554.9.				1	G	7	1 	3U				H2SW 					 
1995050500627	19950505	00627	SW 	1995	5	5	95ZZZX2228 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	115AL		555 			2383				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 554.9.				1	G	7	1 	3U				H2SW 					 
1995050500628	19950505	00628	SW 	1995	5	5	95ZZZX2229 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	174AL		560 			52067				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 559.7.				1	G	7	1 	3U			NC	H2SW 					 
1995050500629	19950505	00629	SW 	1995	5	5	95ZZZX2230 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	174AL		560 			52067				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 559.7.				1	G	7	1 	3U			NC	H2SW 					 
1995050500630	19950505	00630	SW 	1995	5	5	95ZZZX2231 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	173AL		262 			52066				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 261.6.				1	G	7	1 	3U			NC	H2SW 					 
1995050500631	19950505	00631	SW 	1995	5	5	95ZZZX2232 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	173AL		262 			52066				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 261.6.				1	G	7	1 	3U			NC	H2SW 					 
1995050500632	19950505	00632	SW 	1995	5	5	95ZZZX2233 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	364AL		474 			51434				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 473.6.				1	G	7	1 	3U			NC	H2SW 					 
1995050500633	19950505	00633	SW 	1995	5	5	95ZZZX2234 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	364AL		474 			51434				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 473.6.				1	G	7	1 	3U			NC	H2SW 					 
1995050500634	19950505	00634	SW 	1995	5	5	95ZZZX2235 	1	19950330	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	170AL		485 			52063				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 484.9.				1	G	7	1 	3U			NC	H2SW 					 
1995050500635	19950505	00635	SW 	1995	5	5	95ZZZX2236 	1	19950330	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	170AL		485 			52063				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. SPACERS, BUSHINGS, AND BEARINGS, TT 484.9.				1	G	7	1 	3U			NC	H2SW 					 
1995050500636	19950505	00636	SW 	1995	5	5	95ZZZX2237 	1	19950330	G	2820	206063665001	TUBE ASSY 			BELL 	206 	206L1 	1182107	SW 										FUEL VALVE	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3184P					45774				DURING MAJOR INSPECTION, BUILD-UP NOTICED ON INLET AND OUTLET TUBE ASSEMBLIES IN FUEL VALVE BAY. WHEN CLEANED, SEVERE C	ORROSION FOUND ESPECIALLY UNDER B-NUTS. THESE PARTICULAR TUBES WERE MANUFACTURED WITH STEEL SLEEVES, AND ALUMINUM TUBIN	G AND NUTS.				1	G	7	1 	3U				H2SW 					 
1995050500637	19950505	00637	SW 	1995	5	5	95ZZZX2238 	1	19950330	G	2820	206063689001	TUBE ASSEMBLY 			BELL 	206 	206L1 	1182107	SW 										FUEL VALVE	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3184P					45774				DURING MAJOR INSPECTION BUILD-UP, NOTICED ON INLET AND OUTLET TUBE ASSEMBLIES IN FUEL VALVE BAY. WHEN CLEANED, SEVERE C	ORROSION FOUND ESPECIALLY UNDER B-NUTS. THESE PARTICULAR TUBES WERE MANUFACTURED WITH STEEL SLEEVES, AND ALUMINUM TUBIN	G AND NUTS.				1	G	7	1 	3U				H2SW 					 
1995050500701	19950505	00701	EU 	1995	5	5	95ZZZX2240 	1	19950330	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	EXCESS WEAR 	B		A	XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		189 	189 		716					THE BRUSHES ARE SEVERELY WORN. THE BRUSHES ARE WORN 50 PERCENT WITHIN 189.0 FLIGHT HOURS. SUBMITTER RECOMMENDS REDESIG	NING DEFECTIVE BRUSHES. THIS IS A CONTINUAL PROBLEM. OPER CONTROL NR XC4R9531624.					2	L	7	3 	4F				A46EU 					 
1995050500702	19950505	00702	EU 	1995	5	5	95ZZZX2241 	1	19950321	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B		A	XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	50HM	142 			803	153				THIS UNIT'S BRUSHES WERE EXCESSIVELY WORN. THE BRUSHES WERE WORN 60 PERCENT WITHIN 142.0 FLIGHT HOURS. SUBMITTER RECOM	MENDS REDESIGNING DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995050500703	19950505	00703	EU 	1995	5	5	95ZZZX2242 	1	19950321	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B		A	XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	8300E	311 			618	33				THIS UNIT'S BRUSHES WERE EXCESSIVELY WORN. THE BRUSHES WERE WORN 80 PERCENT WITHIN 311.0 FLIGHT HOURS. SUBMITTER RECOM	MENDS REDESIGNING DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995050500704	19950505	00704	EU 	1995	5	5	95ZZZX2243 	1	19950330	G	2435	410965	BEARING 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										DRIVE END	FAILED 	B		A	XC4R	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			SO	19		189 			716					AIRCRAFT DEPARTED UNITED KINGDOM; 15 TO 20 MINUTES OUT, NR 3 GENERATOR INOP LIGHT ILLUMINATED AND WOULD NOT RESET. UPON	 GEAR-DOWN INSPECTION, FOUND DRIVE END BEARING FAILED CATASTROPHICALLY. BEARING FAILED AFTER 189.0 FLIGHT HOURS. DRIVE	 END RETAINING BAND ON ARMATURE DETACHED. ARMATURE, FIELD AND DRIVE END BELL WERE DAMAGED SEVERELY. THE UNIT'S DRIVE S	HAFT HAD SHEARED. SUBMITTER RECOMMENDS REDESIGNING DEFECTIVE BEARINGS. OPER CONTROL NR XC4R9531624.			2	L	7	3 	4F				A46EU 					 
1995050500705	19950505	00705	NM 	1995	5	5	95ZZZX2244 	1	19950408	G	2730	321153011	PCU 			BOEING	757 	757236 		NM 										LT ELEVATOR	LEAKS 	B			GJPY	O				OTHER 				K	J		FLUID LOSS 	WARNING INDICATION 		AP	APPROACH 	1			WP	33	769BE					24118				FLT 3554 - THE LEFT SYSTEM LEAKED HYDRAULIC TO 0.3 WHILE APPROACHING. CHECK FOUND LEFT PCU FOR ELEVATOR HAD SERIOUS LEA	KAGE. REPLACED PCU. OKAY.					2	L	7	2 	4F			RT	A2NM 					 
1995050500706	19950505	00706	NM 	1995	5	5	95ZZZX2245 	1	19950327	G	3230	S11504D0232	HYDRACULIC LINE 			BOEING	757 	757236 		NM 										LT MLG DOWNLOCK	FAILED 	B			GJPY	A	O			UNSCHED LANDING 	OTHER 			J	K		WARNING INDICATION 	FLUID LOSS 		CL	CLIMB 	1			WP	33	769BE					24118				FLT 3551. 'L HYD QTY' MESSAGE DISPLAYED AFTER TAKEOFF. THE LEFT HYDRAULIC QUANTITY DECREASED RAPIDLY. INTERRUPTED THE	 FLIGHT AND EXTENDED LANDING GEAR WITH STANDBY SYSTEM. TOWED TO PARKING APRON AFTER LANDING. CHECK FOUND THE HYDRAULIC	 DUCT FOR LT LANDING GEAR DOWNLOCK ACTUATOR BROKEN. REPLACED THE DUCT. OKAY.				2	L	7	2 	4F			RT	A2NM 					 
1995050500707	19950505	00707	NM 	1995	5	5	95ZZZX2246 	1	19950401	G	2913	3508806	PUMP 			BOEING	757 	757236 		NM 										LT HYD	FAILED 	B			GJPY	O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			WP	33	769BE					24118				FLT 3551 - DURING TRANSIT, THE HYDRAULIC PUMP FOR LT ENGINE LEAKED. CANCELLED THE FLIGHT. SENT MAINTENANCE TO REMOVE F	AULT. REPLACED THE DRIVING HYDRAULIC PUMP FOR LT ENGINE. THE REPLACED HYDRAULIC PUMP WAS SENT TO MANUFACTURER FOR REPA	IR.				2	L	7	2 	4F			RT	A2NM 					 
1995050500708	19950505	00708	NM 	1995	5	5	95ZZZX2247 	1	19950408	G	2750	285N001140	FSEU 			BOEING	757 	757236 		NM 										FLA/SLAT UNIT	MALFUNCTION 	B			GJPY	O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			WP	33	770BE					24119				FLT 3158 - THE FLAP FAILED TO EXTEND WHILE APPROACHING. EXTENDED THE FLAP BY STANDBY MODE. ON THE GROUND, EXTENDED AND	 RETRACTED THE FLAP BY NORMAL MODE AND OKAY, BUT 'ELEVATOR DISAGREE' MESSAGE APPEARED. THE FLIGHT WAS DELAYED. CHECK F	OUND FSEU SHOWED NO FAULT CODE AND STABILIZER TRIM AND DISAGREE ASSEMBLIES WERE OKAY. SENT A MECHANIC TO CHECK AND HE F	OUND NO PROBLEM. REPLACED FSEU NR 1 ASSY WITH PN 285N001-40 TO DETECT FAULT.			2	L	7	2 	4F			RT	A2NM 					 
1995050500709	19950505	00709	CE 	1995	5	5	95ZZZX2248 	1	19950329	G	2770	556527575	CONTROL CABLE 			CESSNA	501 	501 	2076603	CE 										CONTROL LOCK	BROKEN 	B		A	NVIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	13RC	4776 				5010059				THE PILOT REPORTED WHEN THE 'CONTROL LOCK' WAS RELEASED, THE FLIGHT CONTROLS WERE FREE, BUT THE THROTTLES COULD NOT BE M	OVED ABOVE THE IDLE POSITION. INVESTIGATION REVEALED A BROKEN CABLE FROM THE FLIGHT CONTROL LOCK BELLCRANK TO THE THROT	TLE LOCK CAM.				1	L	7	2 	4F			 	A27CE 					 
1995050500710	19950505	00710	SW 	1995	5	5	95ZZZX2249 	1	19950405	G	7830	31183801	BYPASS DUCT 			GULSTM	560 	560 	0141402	SW 										RT ENG T/R	CRACKED 	B		A	EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	75G	1129 				5600140				WHILE PERFORMING OTHER MAINTENANCE ON THE AIRCRAFT, A TECHNICIAN NOTED LIGHT SHOWING THROUGH THE TAILPIPE FROM THE BYPAS	S DUCT TO THRUST REVERSER ATTACH FLANGE. THE COWLING RING WAS REMOVED AND THE OUTBOARD T/R ATTACH FLANGE WAS FOUND CRAC	KED AND DEFORMED. ONE PIECE HAD BROKEN OFF THE FLANGE RING AND TWO PIECES HAD STARTED TO PULL AWAY. THE DUCT WAS REMOV	ED AND REPLACED. SUBJECT DUCT WAS RETURNED TO PRATT AND WHITNEY.			1	H	7	2 	3O				6A1 					 
1995050500711	19950505	00711	EU 	1995	5	5	95ZZZX2250 	1	19950413	G	2435	P6048233	ARMATURE 	AUXILEC 	8260121 	AEROSP	ATR42 	ATR42* 	8680900	EU 										COMMUTATOR	DEFECTIVE 	B		a	XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		1120 			279					UPON TEAR-DOWN INSPECTION FOR OVERHAUL, FOUND ARMATURE INSULATION DEFECTIVE UNDER COMMUTATOR AT REAR. INSULATION COMING	 OUT OF ARMATURE - DEFECT, TSN 1120.0. SUBMITTER RECOMMENDS REDESIGNING DEFECTIVE ARMATURE. OPER CONTROL NR XC4R954183	2.				2	H	7	2 	4T			RT	A53EU 					 
1995050500712	19950505	00712	SW 	1995	5	5	95ZZZX2251 	1	19950401	G	5330		SKIN 			SWRNGN	SA227 	SA227AC 	8780603	SW 										WINDOW OPENING	CORRODED 	B			VH2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	787C	17310				AC550				NOTED CORROSION AT AIRCRAFT WINDOW OPENING AREAS AND SKIN SEAMS. SUSPECT AREAS, AND ALL X-RAY(S) SHOT TO ENSURE CORROSI	ON DID NOT PENETRATE STRINGER AND SKIN MATING SURFACES. DETERMINED TO BE ONLY SURFACE CORROSION AND TREATED AREAS. WIL	L MONITOR THIS CONDITION. SUSPECT CAUSE IS FROM PAINT STRIPPING OPERATIONS. X-RAYS ON FILE AT FAIRCHILD AIRCRAFT SERVI	CES CRSVH2R240L SAN ANTONIO, TX.			1	L	7	2 	4T				A8SW 					 
1995050500713	19950505	00713	EA 	1995	5	5	95ZZZX2252 	1	19950405	G	2752	C2CF1561A	ACTUATOR 			DHAV 	DHC2 	DHC2MK1 	2800102	EA 										FLAP	CORRODED 	B			V2AR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	692F				JH1633	1407				ACTUATOR SUFFERED SEVERE EXFOLIATION AND INTERGRANULAR CORROSION ALONG TOP AND BOTTOM OF ACTUATOR. ACTUATOR IS DIFFICUL	T TO INSPECT ALONG BACK AND TOP SIDES.					1	H	7	1 	3R				A806 					 
1995050500714	19950505	00714	CE 	1995	5	5	95ZZZX2253 	1	19950410	G	7120	66003093	ISOLATOR 			LEAR 	35 	35A 	5170602	CE 										AFT ENG MOUNT	TORN 	B		A	TJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	7XJ	1055 				3A669				ISOLATOR MOUNT RUBBER IS TORN/CUT. THIS CONDITION OCCURS ONLY ON LEARS WITH THE DEE HOWARD TR 4000 SERIES THRUST REVERS	ERS. THE NORMAL TIME CHANGE INTERVAL IS 8400 HOURS. DEE HOWARD CO. HAS ISSUED SERVICE BULLETINS TO CORRECT THIS PROBLE	M THINKING IT IS HEAT RELATED. SUSPECT CAUSE IS VIBRATION OR BUFFETING DURING NORMAL ENGINE OPERATION AND REVERSE THRUS	T.			2	L	7	2 	4F				A10CE 					 
1995050500715	19950505	00715	NE 	1995	5	5	95ZZZX2254 	2	19950407	G	7250	50H067	NUTPLATE 								PWA 	4056 	PW4056 		NE 					FLANGE STG 9-10	MISMFG 	B			TUVR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	11										PURCHASED NUTPLATE ASSY IDENTIFIED AS PN 50H069, WAS ONE OFFSET NUT WITH RELATION TO THE OTHERS. THIS CONFIGURATION IS 	CONSISTANT WITH PN 50H067. APPEARS NUTPLATE ASSY HAS BEEN MISIDENTIFIED.										4	F			E24NE				 
1995050500719	19950505	00719	EA 	1995	5	5	95ZZZX2258 	1	19950330	G	3222	73007	HOUSING 			CNDAIR	CL600 	CL6002A12 	1900304	EA 										NLG	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	999JR				DEC388083	3061				INSP FOUND NLG UPPER HOUSING CORRODED. NOSE GEAR ASSY ON 601 ACFT SHOULD HAVE PN 601-85008-15 (CANADAIR), PN 7300-9 - (	DOWTY). HAD ASSY PN 600-85008-27 (CANADAIR) AND PN 200924004 (DOWTY). LANDING GEAR WAS A 600 GEAR SENT BACK TO DOWTY T	O UPGRADE TO A 601 APRIL 14, 1986, AND DATA PLATE WAS NEVER CHANGED. IT HAS NOW BEEN CHANGED TO PN 601-85008-15 DOWTY P	N 7300-7.			2	L	7	2 	4F			RT	A21EA 					 
1995050500720	19950505	00720	EA 	1995	5	5	95ZZZX2259 	1	19950330	G	1100		DATA PLATE 			CNDAIR	CL600 	CL6002A12 	1900304	EA 										NLG	NOT CHANGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	999JR	3547 	2763 			3061				INSP FOUND NLG UPPER HOUSING CORRODED. NOSE GEAR ASSY ON 601 ACFT SHOULD HAVE PN 601-85008-15 (CANADAIR), PN 7300-9 - (	DOWTY). HAD ASSY PN 600-85008-27 (CANADAIR) AND PN 200924004 (DOWTY). LANDING GEAR WAS A 600 GEAR SENT BACK TO DOWTY T	O UPGRADE TO A 601 APRIL 14, 1986, AND DATA PLATE WAS NEVER CHANGED. IT HAS NOW BEEN CHANGED TO PN 601-85008-15 DOWTY P	N 7300-7.			2	L	7	2 	4F			RT	A21EA 					 
1995050500721	19950505	00721	SO 	1995	5	5	95ZZZX2260 	2	19950323	G	8530	648044	PISTON 								CONT 	O520 	TSIO520BE 	17040	SO 					NR 1 THU NR 6	PIN BOSS CRACKED	B			DC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15		791 					273705R			UPON DISASSEMBLY OF ENGINE FOR PROP STRIKE INSPECTION AND TOP O/H, PISTONS FOUND CRACKED IN THE PIN BOSS AREA EXTENDING 	UP TO THE TOP INSIDE SURFACE (ONE SIDE ONLY). SUBMITTER UNSURE OF CAUSE. COULD BE MANUFACTURE DEFECT, DETONATION, MISU	SE, ETC.									3	O			E8CE				 
1995050500722	19950505	00722	SO 	1995	5	5	95ZZZX2261 	2	19950410	G	8550	538517	OIL PAN 			BEECH 	55 	D55 	1152730	CE 	CONT 	O520 	IO520C 	17032	SO 					UNDER 2-4 CYLS	CRACKED 	D				O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			SW	07	69RP	479 				TE766	287258R			DURING FLIGHT, PILOT NOTICED OIL STREAMING FROM RT COWLING. INSPECTION BY MAINTENANCE PERSONNEL REVEALED A 2 INCH CRACK	 IN THE OIL PAN AT LOWER RADIUS. SUSPECT FATIGUE, POOR STAMPING, DURING MANUFACTURING.					1	L	7	2 	3O	3	O		3A16 	E5CE				 
1995050500723	19950505	00723	SO 	1995	5	5	95ZZZX2262 	1	19950328	G	5551	29108	FITTING 			LUSCOM	8 	8E 	8190112	SO 										HORIZ STAB	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	1216B					5843				DURING AN INSPECTION, SLIGHT LOOSNESS NOTICED IN THE HORIZ STABILIZER. FURTHER DISASSEMBLY SHOWED FORWARD FITTING CRACK	ED COMPLETELY THROUGH NEAR RT BOLT HOLE. THE ACFT RECORDS SHOWED THAT EXTENSIVE REPAIRS HAD BEEN MADE TO THE EMPENNAGE 	AFTER A LANDING INCIDENT. THE AFFECTED PART WAS MOST LIKELY DAMAGED DUE TO THE BAD LANDING, AND BECAUSE OF ITS LOCATION	, THIS WAS NOT DETECTED. PART IS A CASTING AND SUBMITTER RECOMMENDS INSPECTING THIS PART VERY CAREFULLY ANY TIME REPAIR	S BE MADE TO THE EXPENNAGE, HORIZONTAL OR VERTICAL STABILIZERS.		1	H	7	1 	3O				A694 					 
1995050500724	19950505	00724	SO 	1995	5	5	95ZZZX2264 	1	19950424	G	2810		FUEL SYSTEM 			LUSCOM	8 	8E 	8190112	SO 										GASCOLATOR	WATER CONTAM 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CL	CLIMB 	1			SW	15	2232K					4959				LOST ENGINE POWER DURING TAKEOFF AT 200 FEET AGL. AIRCRAFT DESTROYED. FOUND WATER IN GASCOLATOR. BOTH FUEL FILL CAPS 	LEAKING. FUEL FILL CAPS DID NOT PROVIDE A TIGHT SEAL. SUSPECT WATER DAMMED AROUND FILTER NECKS DURING HEAVY RAIN AND E	NTERED FUEL TANKS.				1	H	7	1 	3O				A694 					 
1995050500725	19950505	00725	CE 	1995	5	5	95ZZZX2265 	1	19950410	G	5220	52111302	DOOR 			CESSNA	402 	402CESSNA 	207590K	CE 										EMERG EXIT	LATCH FAILED 	D				O				OTHER 				D			INFLIGHT SEPARATION 			AP	APPROACH 	1			SW	07	4046Q	5661 				4020146				DURING AN APPROACH TO LAND, THE EMERGENCY EXIT DEPARTED THE AIRCRAFT. AFTER AN UNEVENTFUL LANDING, INSPECTION REVEALED 	THE REAR LATCH WAS INTACT, BUT THE 4 MOUNTING RIVETS WERE SHEARED. ONE FORWARD LATCH WAS FOUND AND APPEARED CRACKED IN 	THE RADIUS OF THE BOND, WITH SECURING PIN STILL INSTALLED. SUSPECT CRACKED, CORRODED LATCHES.				1	L	7	2 	3O				A7CE 					 
1995050500726	19950505	00726	SO 	1995	5	5	95ZZZX2266 	1	19950330	G	2710	828154	CONTROL CABLE 			PIPER 	PA46 	PA46350P 	7104602	SO 										AILERONS	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	9167Q	329 				4622031				AILERON BALANCE CABLE FLAT SPOTTING WHERE CABLE PASSES THROUGH PHENOLIC RUB BLOCK AT WS 51.54. SL 1012 ANNOUNCES AVAILA	BILITY OF IMPROVED AILERON CABLES. IT APPEARS OLD CABLES ARE 'SOFT' IF THEY ARE WEARING BY CONTACTING PHENOLIC. SUBMIT	TER RECOMMENDS MANDATORY REPLACEMENT IF THESE REPORTS CONTINUE. SAME CONDITION NOTED ON RIGHT SIDE.				1	L	7	1 	3O			RT	A25SO 					 
1995050500727	19950505	00727	CE 	1995	5	5	95ZZZX2267 	1	19950410	G	5312		BULKHEAD 			CESSNA	402 	402CESSNA 	207590K	CE 										AFT TAILCONE	DAMAGED 	D				K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			SW	07	4046Q	5661 				4020146				DURING A GROUND INSPECTION, DISCOVERED TAIL CONE AND REAR BULKHEAD ASSEMBLIES CRACKED AND CRUSHED. THE TAIL CONE WAS AL	SO PUSHED UP AND OBSTRUCTING RUDDER MOVEMENT. THE CRUSHED BULKHEAD WAS ALSO IN DANGER OF OBSTRUCTION TO ELEVATOR CONTRO	L TRAVEL. SUSPECT IMPROPER LOADING OR UNLOADING OF AIRCRAFT ALLOWING IT TO FALL ON TAIL ASSY. (UNLOADING NOSE FIRST).				1	L	7	2 	3O				A7CE 					 
1995050500728	19950505	00728	SO 	1995	5	5	95ZZZX2268 	1	19950420	G	7602	455361	CONTROL CABLE 			PIPER 	PA28 	PA28RT201T 	7102817	SO 										MIXTURE CONTROL	BINDING 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	2869X	2850 				28R7931231				MIXTURE CONTROL CABLE, OVER A 6-MONTH PERIOD, BECAME INCREASINGLY DIFFICULT TO MOVE. LUBRICATION TEMPORARILY RESOLVED P	ROBLEM, ONLY TO RETURN. FIRE STOP INSULATION SHEATH ALONG WITH NEW MIXTURE CABLE INSTALLED BY A & P. PROBLEM RESOLVED.	 SUSPECT CAUSE AS EXCESSIVE HEAT FROM TURBOCHARGER, UNSHIELDED, CAUSED CORROSION TO OCCUR INSIDE CABLE HOUSING. RECOMM	ENDATION: INSTALL NEW CABLE WITH FIRE SHIELD.			1	L	7	1 	3O			 	2A13 					 
1995050500729	19950505	00729		1995	5	5	95ZZZX2269 	1	19950419	G	7922	53E19600	VALVE 								LYC 	O540 	AEIO540D4A5 	41532	EA 					THERMO BYPASS	NUT LOOSE 	G		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17							L2334348A			BYPASS VALVE REMOVED TO COMPLY WITH LYCOMING SB 518A. THE NUT WAS FOUND LOOSE AND HALF-WAY UNSCREWED FROM THE THREADED 	SHAFT OF THE VALVE. IT WAS NOTED THE S/N OF VALVE WAS HIGHER THAN THE AFFECTED S/N'S LISTED IN SB. SUBMITTER RECOMMEND	S INSPECTION PER SB OF ALL VALVES REGARDLESS OF S/N'S SB SHOULD BE AMENDED OR AN AD ISSUED.									3	O			1E4				 
1995051200001	19950512	00001	SO 	1995	5	12	95ZZZX2270 	2	19950429	G	8520		CRANKSHAFT 								CONT 	O520 	IO520A 	17032	SO 					ROD WEIGHTS	OUT OF BALANCE 	B	L		YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11			1 				112746			THE CONNECTING ROD WEIGHTS ON THE LARGE END FROM THE LIGHTEST TO THE HEAVIEST WAS 57 GRAMS. THIS ENGINE HAS NEVER BEEN 	INSTALLED IN AN AIRCRAFT.										3	O			E5CE				 
1995051200002	19950512	00002	SO 	1995	5	12	95ZZZX2271 	2	19950429	G	8530	629401	PISTON 								CONT 	O520 	IO520A 	17032	SO 					SCRAPER RING	RING BROKEN 	B	L		YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11			1 				112746			PISTON SCRAPER RING WAS BROKEN AT ASSEMBLY. PART OF THE BROKEN RING WAS IN THE OIL SUMP. THIS ENGINE HAS NEVER BEEN IN	STALLED IN AN AIRCRAFT.										3	O			E5CE				 
1995051200003	19950512	00003	EA 	1995	5	12	95ZZZX2272 	1	19950417	G	7120	44911601	MOUNT BODY 	BARRYCTRLS 		SCWZER	G164 	G164C 	3952803	EA 										ENGINE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	8341K				X11607	35C				FOUND ENGINE MOUNT BODY CRACKED DURING ENGINE CHANGE. SUSPECT OVERTORQUE OF MOUNTING BOLTS. (PT6 CONVERSION STC SA2444	SW). MOUNT SN'S - 3 REPORTS, X11607, X11792, X11898.					1	Q	7	1 	3R				1A16 					 
1995051200004	19950512	00004	NM 	1995	5	12	95ZZZX2273 	1	19950327	G	5311		FRAME RIB 			BOEING	727 	72723 	1384004	NM 										FS 1362 LT-RT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				BOTH THE LT AND RT STA 1362 FRAME RIBS WERE FOUND CRACKED DURING THE VERTICAL STABILIZER REAR SPAR TERMINAL FITTING CHAN	GE. FATIGUE IS THE LIKELY CAUSE AND MORE FREQUENT INSPECTION APPEARS TO BE REQUIRED.					2	L	7	3 	4F				A3WE 					 
1995051200005	19950512	00005	NM 	1995	5	12	95ZZZX2274 	1	19950327	G	5320	65236511	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342 LBL 18	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE LT VERTICAL STABILIZER TORQUE BOX LOWER CHORD WAS FOUND CORRODED DURING VERTICAL STABILIZER TERMINAL FITTING REPLACE	MENT. THE CAUSE IS PROBABLY DISSIMILAR METALS AND A LACK OF DRAINAGE. DUE TO A LACK OF ACCESSIBILITY, THE ONLY WAY TO 	FIND THIS DEFECT IS BY X-RAY INSPECTION.				2	L	7	3 	4F				A3WE 					 
1995051200006	19950512	00006		1995	5	12	95ZZZX2275 	4	19950419	G	2215	30513136	ACTUATOR 			AIRBUS	300 	A300B4605R 	3930308	EU 										AUTOPILOT	PINS MISSING 	B		A	IX1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					2294					AUTOPILOT ACTUATOR RETURNED FOR REPAIR. WHEN OPENED, FOUND STOP SLEEVES AND PIN ADRIFT IN UNIT. TWO SECURING COTTER PI	NS WERE MISSING, (iTEMS 100, REF. CMM 22-11-41). OPERATOR WAS FEDEX, REPAIR CARD 48505 REFERS.					2	L	7	2 	4F			RT	A35EU 					 
1995051200008	19950512	00008	EU 	1995	5	12	95ZZZX2277 	1	19950420	G	3610	AB50B1927	RELIEF VALVE 			BAC 	111 	111419EP 	1480280	EU 										HEAT EXCHANGER	LEAKING 	D				A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	09	524AC	8480 				BAC120				AFTER CLIMB-OUT, AIRCRAFT EXPERIENCED A STUB WING OVERTEMP WITH SUBSEQUENT PACK TRIP ON THE LT SIDE. PILOT RETURNED TO 	BASE. INSPECTION REVEALED HEAT EXCHANGER 'BLOW-OUT' RELIEF VALVE LEAKING BLEED AIR INTO STUB WING. VALVE WAS REPLACED 	WITH NO FURTHER PROBLEMS.				2	L	7	2 	4F				A5EU 					 
1995051200009	19950512	00009	NM 	1995	5	12	95ZZZX2278 	1	19950331	G	5711	20005101	RIB 			PIPER 	PA60 	PA60601 	7106010	NM 										RT OUTBD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	7529S	3226 				600566796118				DURING AN ANNUAL INSPECTION, OUTBOARD AILERON BEARING BRACKET APPEARED TO HAVE WORKING RIVETS. REMOVAL OF THE BRACKET R	EVEALED CRACKS IN THE RIB IN TWO OF THE RIVET HOLES. IT WAS FURTHER NOTED THAT THE BEARING WAS A SOLID ROLLER AND NOT A	 SPHERICAL BEARING LIKE THE INBOARD AND CENTER BEARINGS CAUSING A ROTATION OF THE RIB SINCE THE PIVOT AXIS OF THE AILERO	N IS NOT PERPENDICULAR TO THE RIB WHICH IS CAUSING CRACKS IN THE RIB. INSTALLING A SPHERICAL BEARING NR 452-745 LIKE US	ED IN THE OTHER BEARING HINGE BRACKETS REMOVES THE TWISTING MOTION BY ALMOST 100 PERCENT.		1	M	7	2 	3O			RT	A17WE 					 
1995051200010	19950512	00010	NM 	1995	5	12	95ZZZX2279 	1	19950331	G	5751	452742	BEARING 			PIPER 	PA60 	PA60601 	7106010	NM 										OUTBD AILERON	WRONG PART 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	7529S	3226 				600566796118				DURING AN ANNUAL INSPECTION, OUTBOARD AILERON BEARING BRACKET APPEARED TO HAVE WORKING RIVETS. REMOVAL OF THE BRACKET R	EVEALED CRACKS IN THE RIB IN TWO OF THE RIVET HOLES. IT WAS FURTHER NOTED THAT THE BEARING WAS A SOLID ROLLER AND NOT A	 SPHERICAL BEARING LIKE THE INBOARD AND CENTER BEARINGS CAUSING A ROTATION OF THE RIB SINCE THE PIVOT AXIS OF THE AILERO	N IS NOT PERPENDICULAR TO THE RIB WHICH IS CAUSING CRACKS IN THE RIB. INSTALLING A SPHERICAL BEARING NR 452-745 LIKE US	ED IN THE OTHER BEARING HINGE BRACKETS REMOVES THE TWISTING MOTION BY ALMOST 100 PERCENT.		1	M	7	2 	3O			RT	A17WE 					 
1995051200011	19950512	00011	NM 	1995	5	12	95ZZZX2280 	1	19950417	G	5752	65217088	HINGE FITTING 			BOEING	727 	72723 	1384004	NM 										RT OTBD AILERON	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THREE HINGE FITINGS IN THE RT OTBD AILERON WERE FOUND SEVERELY CORRODED DURING A C-CHECK. THE FITTINGS ARE MAGNISIUM, T	HAT AND TIME ARE THE MOST LIKELY CAUSE. CAREFUL INSPECTION IS NEEDED IN THIS AREA.					2	L	7	3 	4F				A3WE 					 
1995051200012	19950512	00012	NM 	1995	5	12	95ZZZX2281 	1	19950417	G	5752	65217087	HINGE FITTING 			BOEING	727 	72723 	1384004	NM 										RT OTBD AILERON	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THREE HINGE FITINGS IN THE RT OTBD AILERON WERE FOUND SEVERELY CORRODED DURING A C-CHECK. THE FITTINGS ARE MAGNISIUM, T	HAT AND TIME ARE THE MOST LIKELY CAUSE. CAREFUL INSPECTION IS NEEDED IN THIS AREA.					2	L	7	3 	4F				A3WE 					 
1995051200013	19950512	00013	NM 	1995	5	12	95ZZZX2282 	1	19950304	G	5320	65209812	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE BS 1342 FORWARD CENTER CHORD WAS FOUND CRACKED DURING A RE-ENGINING MODIFICATION. THE CHORD PROBABLY CRACKED DUE TO	 FLEXING OF THE 1342 BULKHEAD WEB CAUSED BY THE S-DUCT.					2	L	7	3 	4F				A3WE 					 
1995051200179	19950512	00179	NM 	1995	5	12	95ZZZX2285 	1	19950327	G	5751	65217088	HINGE FITTING 			BOEING	727 	72723 	1384004	NM 										LT OTBD AILERON	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WP	36471				20045				TWO HINGE FITTINGS IN THE LT OTBD AILERON WERE FOUND SEVERELY CORRODED DURING A C-CHECK INSPECTION. THE FITTINGS ARE MA	GNISIUM, THAT AND TIME ARE THE MOST LIKELY CAUSE. CAREFUL INSPECTION IS NEEDED TO CATCH THIS KIND OF PROBLEM.					2	L	7	3 	4F				A3WE 					 
1995051200180	19950512	00180	NM 	1995	5	12	95ZZZX2286 	1	19950327	G	5751	65217087	HINGE FITTING 			BOEING	727 	72723 	1384004	NM 										LT OTBD AILERON	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WP	36471				20045				TWO HINGE FITTINGS IN THE LT OTBD AILERON WERE FOUND SEVERELY CORRODED DURING A C-CHECK INSPECTION. THE FITTINGS ARE MA	GNISIUM, THAT AND TIME ARE THE MOST LIKELY CAUSE. CAREFUL INSPECTION IS NEEDED TO CATCH THIS KIND OF PROBLEM.					2	L	7	3 	4F				A3WE 					 
1995051200181	19950512	00181	NM 	1995	5	12	95ZZZX2287 	1	19950327	G	7120	65229135	CHORD 			BOEING	727 	72723 	1384004	NM 										NR 2 ENG AFT MT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE VERTICAL BEAM AT THE NR 2 ENGINE AFT MOUNT WAS FOUND SEVERELY CORRODED DURING A RE-ENGINE MODIFICATION. BECAUSE OF 	ITS LOCATION AND LACK OF ACCESSIBILITY THE ONLY WAY TO DISCOVER THIS DEFECT WOULD BE BY X-RAY INSPECTION.					2	L	7	3 	4F				A3WE 					 
1995051200182	19950512	00182	NM 	1995	5	12	95ZZZX2288 	1	19950327	G	5532		CHORD 			BOEING	727 	72723 	1384004	NM 										V-STAB STA 22.5	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	26471				20045				THE VERTICAL STABILIZER, REAR SPAR, LT CHORD AT STABILIZER, STA 225, WAS FOUND SEVERELY CORRODED DURING A RE-ENGINE MODI	FICATION. THE CAUSE IS PROBABLY A LACK OF DRAINAGE AND AGE. THE ONLY WAY TO FIND THIS PROBLEM IS WITH AN X-RAY INSPECT	ION.				2	L	7	3 	4F				A3WE 					 
1995051200183	19950512	00183	NM 	1995	5	12	95ZZZX2289 	1	19950327	G	5751	6595600312	ATTACH FITTING 			BOEING	727 	72723 	1384004	NM 										LT OTBD AIL TAB	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				BOTH LT OTBD AILERON TAB PUSH ROD ATTACH FITTINGS WERE FOUND CORRODED BEYOND LIMITS DURING A C-CHECK. THE FITTINGS ARE 	MAGNISIUM, THAT AND TIME ARE THE MOST LIKELY CAUSES. CAREFUL INSPECTION IS NEEDED TO CATCH THIS KIND OF PROBLEM.					2	L	7	3 	4F				A3WE 					 
1995051200184	19950512	00184	NM 	1995	5	12	95ZZZX2290 	1	19950327	G	5320	65236512	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342 RBL 18	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF					20045				THE RT VERTICAL STABILIZER TORQUE BOX LOWER CHORD WAS FOUND CORRODED DURING VERTICAL STABILIZER TERMINAL FITTING REPLACE	MENT. THE CAUSE IS PROBABLY DISSIMILAR METALS AND A LACK OF DRAINAGE. DUE TO LACK OF ACCESSIBILITY, THE ONLY WAY TO FI	ND THIS DEFECT IS BY X-RAY INSPECTION.				2	L	7	3 	4F				A3WE 					 
1995051200185	19950512	00185	NM 	1995	5	12	95ZZZX2291 	1	19950304	G	5320	65225511	CHANNEL 			BOEING	727 	72723 	1384004	NM 										FS 1342 LBL 18	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE BS 1342, LBL 18 CHANNEL WAS FOUND SEVERELY RUSTED WHERE IT ATTACHES TO THE STRUCTURE. DEFECT WAS DISCOVERED DURING 	A RE-ENGINING MODIFICATION. THIS CONDITION HAS BEEN FOUND ON 38 OF THE 38 AIRCRAFT MODIFIED SO FAR. CONDITION IS PROBA	BLY CAUSE BY DISSIMILAR METAL AND LACK OF DRAINAGE. NOTE: THE DEFECT COULD NOT BE SEEN WITHOUT REMOVING PART, MAY NEED	 TO BE X-RAYED EVERY 5 YEARS.			2	L	7	3 	4F				A3WE 					 
1995051200186	19950512	00186	NM 	1995	5	12	95ZZZX2292 	1	19950321	G	5320	65225512	CHANNEL 			BOEING	727 	72723 	1384004	NM 										FS 1342 RBL 18	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE BS 1342, RBL 18 CHANNEL WAS FOUND SEVERELY RUSTED WHERE IT ATTACHES TO THE STRUCTURE. DEFECT WAS DISCOVERED DURING 	A RE-ENGINING MODIFICATION. THIS CONDITION HAS BEEN FOUND ON ALL 38 AIRCRAFT MODIFIED THUS FAR. CONDITION IS PROBABLY 	CAUSED BY DISSIMILAR METAL AND LACK OF DRAINAGE. NOTE: THE RUST CANNOT BE SEEN WITHOUT REMOVING THE PART, MAY NEED TO 	BE X-RAYED EVERYY SO MANY YEARS.			2	L	7	3 	4F				A3WE 					 
1995051200187	19950512	00187	NM 	1995	5	12	95ZZZX2293 	1	19950321	G	5320	6519321	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342 LBL 30	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE BS 1342, LBL 30 CHORD WAS FOUND SEVERELY RUSTED. THE DEFECT WAS DISCOVERED DURING A RE-ENGINING MODIFICATION. THIS	 CONDITION HAS BEEN FOUND ON ALL 38 A/C MODIFIED THUS FAR. THE CONDITION IS PROBABLY CAUSED BY DISSIMILAR METAL AND LAC	K OF DRAINAGE. NOTE: THE RUST CANNOT BE SEEN WITHOUT REMOVING THE PART, SO IT MAY NEED AN X-RAY INSPECTION TO FIND.				2	L	7	3 	4F				A3WE 					 
1995051200188	19950512	00188	NM 	1995	5	12	95ZZZX2294 	1	19950321	G	5320	65175085	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342 LT	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE BS 1342, LT LOWER FRAME CHORD WAS FOUND SEVERELY RUSTED DURING A RE-ENGINING MODIFICATION. THIS CONDITION HAS BEEN 	DISCOVERED ON ALL 38 A/C MODIFIED SO FAR. SUSPECT CAUSED BY DISSIMILAR METAL AND LACK OF DRAINAGE. THE RUST CANNOT BE 	SEEN WITHOUT REMOVING THE PART, SO IT MAY NEED AN X-RAY INSPECTION EVERY SO MANY YEARS.				2	L	7	3 	4F				A3WE 					 
1995051200189	19950512	00189	NM 	1995	5	12	95ZZZX2295 	1	19950321	G	5320	65175086	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342 RT	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF					20042				THE BS 1342, RT LOWER FRAME CHORD WAS FOUND SEVERELY RUSTED DURING A RE-ENGINING MODIFICATION. THIS CONDITION HAS BEEN 	DISCOVERED ON ALL 38 A/C MODIFIED THUS FAR. THE CONDITION IS PROBABLY CAUSED BY DISSIMILAR METALS AND LACK OF DRAINAGE.	 NOTE: THE RUST CANNOT BE SEEN WITHOUT REMOVING THE PART, SO IT MAY NEED AN X-RAY INSPECTION EVERY SO MANY YEARS.				2	L	7	3 	4F				A3WE 					 
1995051200190	19950512	00190	NM 	1995	5	12	95ZZZX2296 	1	19950321	G	5320	65195321	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342 RBL 30	RUSTED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF					20045				THE BS 1342, LBL 30 CHORD WAS FOUND SEVERELY CORRODED (RUSTY) DURING A RE-ENGINING MODIFICATION. THIS CONDITION HAS BEE	N DISCOVERED ON ALL 38 A/C MODIFIED SO FAR. THE RUST IS PROBABLY CAUSED BY DISSIMILAR METAL AND LACK OF DRAINAGE. NOTE	: THE RUST CANNOT BE SEEN WITHOUT REMOVING THE PART, SO IT MAY NEED TO BE X-RAYED EVERY SO MANY YEARS.				2	L	7	3 	4F				A3WE 					 
1995051200191	19950512	00191	NM 	1995	5	12	95ZZZX2297 	1	19950321	G	5320	65225513	CHANNEL 			BOEING	727 	72723 	1384004	NM 										FS 1342	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE BS 1342, AFT CENTER CHANNEL (AT TOP OF FIREWALL) WAS FOUND SEVERELY RUSTED DURING A RE-ENGINE MODIFICATION. THIS CO	NDITION HAS BEEN FOUND ON ALL 38 A/C MODIFIED SO FAR. THE CONDITION IS PROBABLY CAUSED BY DISSIMILAR METAL AND LACK OF 	DRAINAGE. NOTE: THE RUST CANNOT BE SEEN WITHOUT REMOVING THE PART, SO IT MAY NEED AN X-RAY INSPECTION EVERY SO MANY YE	ARS.			2	L	7	3 	4F				A3WE 					 
1995051200192	19950512	00192	NM 	1995	5	12	95ZZZX2298 	1	19950324	G	5320	69154054	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342 RT	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE BS 1342, RT INBD FRAME CHORD WAS FOUND SEVERELY RUSTED DURING A RE-ENGINING MODIFICATION. THIS CONDITION HAS BEEN D	ISCOVERED ON ALL 38 A/C MODIFIED SO FAR. THE CONDITION IS PROBABLY CAUSED BY DISSIMILAR METAL AND A LACK OF DRAINAGE. N	OTE: THE RUST CANNOT BE SEEN WITHOUT REMOVING THE PART, SO IT MAY NEED AN X-RAY INSPECTION EVERY SO MANY YEARS.				2	L	7	3 	4F				A3WE 					 
1995051200193	19950512	00193	NM 	1995	5	12	95ZZZX2299 	1	19950321	G	5320	65154053	CHORD 			BOEING	727 	72723 	1384004	NM 										FS 1342 LT	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	727WF	36471				20045				THE BS 1342, LT INBD FRAME CHORD WAS FOUND SEVERELY RUSTED DURING A RE-ENGINING MODIFICATION. THIS CONDITION HAS BEEN F	OUND ON ALL 38 A/C MODIFIED SO FAR. THIS CONDITION IS PROBABLY CAUSED BY DISSIMILAR METALS AND A LACK OF DRAINAGE. NOT	E: THE RUST CANNOT BE SEEN WITHOUT REMOVING THE PART, SO IT MAY NEED X-RAY INSPECTION EVERY S0 MANY YEARS.				2	L	7	3 	4F				A3WE 					 
1995051200194	19950512	00194	EU 	1995	5	12	95ZZZX2300 	1	19950315	G	5102		FUEL SYSTEM 			THUNDR	AX8 	AX890 	8970111	EU 										TANK & BURNER	CONTAMINATED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01		93 				2526USA				METAL FILINGS WERE FOUND IN FUEL SYSTEM, SUSPECTED FROM TANK MANUFACTURE. BURNER VALVES AND COMPONENTS FOULED DUE TO ME	TAL FILINGS AND EXCESSIVE PIPE DOPE DURING CONSTRUCTION. SUSPECT CAUSE - POOR QUALITY CONTROL IN FACTORY DURING PRODUCT	ION.				1	B	0	0 					B2EU 					 
1995051200351	19950512	00351	SW 	1995	5	12	95ZZZX2301 	1	19950314	G	6220	204011121003	BOLT 			BELL 	204 	UH1H 	1181407	SW 										M/R HEAD	FAILED 	H	P	A		A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			EX	EXTERNAL LOAD 	1			NM	01	98NW					6413822				PILOT REPORTED SEVERE MAIN ROTOR VIBRATION DURING FLIGHT. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. INSPECTION REVEALED	 PILLOW BLOCK BOLT HAD FAILED. MAIN ROTOR HEAD PILLOW BLOCK HAD LIFTED .1250 INCH ABOVE MAIN ROTOR HEAD YOKE AND PILL	OW BLOCK BUSHING HAD LIFTED .25 INCH OUT OF PILLOW BLOCK. BOLT FAILED AT THREADED AREA OF BOLT. SEALANT AROUND NUT ON 	YOKE ALLOWED NUT AND LOWER PART OF BOLT TO STAY ATTACHED TO YOKE. ALL FOUR BOLTS HAD BEEN REPLACED 731.8 HRS PRIOR IAW 	AD 92-23-01. AIRCRAFT PERFORMING FAR PART 133 EXTERNAL LOAD OPERATIONS.		1	G	7	1 	4U				EXPA1G71					 
1995051200352	19950512	00352	EU 	1995	5	12	95ZZZX2302 	1	19950322	G	6420	109013105111	TRUNNION ASSY 		109813102115	AGUSTA	A109 	A109K2 	0260502	EU 										T/R HUB	WORN 	D	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	911RX	186 			A40001	10017				ON PRE-FLIGHT, A BLUING (HEATED) AREA WAS FOUND ON THE T/R HUB AT THE BUSHING END, ONE SIDE. A TEAR-DOWN REVEALED THE T	RUNNION SLEEVE AND BUSHING HAD SEVERE GALLING AND HEAT DAMAGE. BOTH TRUNNION AND BUSHINGS WERE REPLACED. SUBMITTER SUG	GESTED RE-DESIGN WITH DIFFERENT MATERIALS AND TOLERANCES MIGHT HELP EXTEND THE LIFE OF THESE PARTS. OPER CONTROL NR QKZ	A029W.			1	G	7	2 	3U			RT	H7EU 					 
1995051200353	19950512	00353	CE 	1995	5	12	95ZZZX2303 	1	19950418	G	2752	C4860912	CAP 		48C48609 	LEAR 	35 	36LEAR 	5170601	CE 										FLAP ACTUATOR	DEFECTIVE 	B		A	BHKR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	21	101AJ	8290 			030	36008				INSPECTION OF FLAP ACTUATOR FOUND A HOLE APPROXIMATELY .1250 INCH LONG IN THE CAP WHERE THE PISTON HEAD WOULD SEAT. THI	S DEFECT WAS FOUND DURING A REPACK, ALTHOUGH THIS HOLE DID NOT CAUSE THE ACTUATOR TO LEAK. THE RETURN PORT OF THE ACTUA	TOR IS JUST OPPOSITE OF THE HOLE. IT IS BELIEVED THAT DURING MANUFACTURE, THE HOLE DRILLED AND TAPPED FOR THE RETURN PO	RT WAS OFF CENTER CAUSING TOP TO CUT THROUGH THE PARENT MATERIAL FORMING SEAT FOR THE PISTON HEAD, OR THE PISTON SEAT WA	S MILLED TOO DEEPLY. CLOSER QUALITY CONTROL SHOULD PREVENT IMPROPERLY MACHINED COMPONENTS FROM ENTERING CIRCULATION.		2	L	7	2 	4F				A10CE 					 
1995051200355	19950512	00355	NM 	1995	5	12	95ZZZX2305 	1	19950428	G	5753	6522244	SUPPORT FITTING 			BOEING	707 	707323C 	138367D	NM 										RT FILLET FLAP	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15						19380				WHILE PERFORMING OTHER INSPECTION, THE RIGHT FILLET FLAP TRANSMISSION SUPPORT FITTING FOUND WITH SEVERAL CRACKS. REPAIR	 KIT 65C15737 INSTALLED FOR FERRY FLIGHT PER SB BOEING 3251, REV. 2.					2	L	7	4 	4F				4A26 					 
1995051200358	19950512	00358	WP 	1995	5	12	95ZZZX2309 	2	19950423	G	7200		ENGINE 			AMD 	FALC50	FALCON50MYST	2730106	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					NR 1	FAILED 	B			NV1R	E				ENGINE SHUTDOWN 				E	B		VIBRATION/BUFFET 	SMOKE/FUMES/ODORS/SPARKS 		CR	CRUISE 	1			GL	05	4350M	6352 				142	P76568			DAY/EWR - IN-FLIGHT SHUT DOWN 4-23-95, ENGINE EXPERIENCED INTERMITTENT VIBRATION AND ODOR EMISSION INTO CABIN. ABNORMAL	 N1 AND ITT READINGS INCREASED VIBRATION, PROMPTED SHUT DOWN WHILE DESCENDING INTO EWR AT 6,000 FEET. THE NR 1 ENGINE O	N THIS AIRCRAFT HAD FAILED PREVIOUSLY UNDER SIMILAR CIRCUMSTANCES AND TIMES. SAME BLOCK OF SERIAL NUMBERS.				2	L	7	3 	4F	4	F		A46EU 	E6WE				 
1995051200469	19950512	00469	SO 	1995	5	12	95ZZZX2313 	1	19950427	G	7922	75944	VALVE 			PIPER 	PA28 	PA28180 	7102808	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	H		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	16435				99692	287305254				FOUND LOOSE CRIMP NUT IAW LYCOMING SB 518B. NUT MEETS CRIMP DEPTH, BUT IS LOOSE ON SHAFT. RECOMMEND RETURNING TO OLD S	TYLE WITH ROLL PIN THROUGH-NUT.					1	L	7	1 	3O				2A13 					 
1995051200470	19950512	00470	SO 	1995	5	12	95ZZZX2314 	2	19950429	G	8530	629401	RING 								CONT 	O520 	IO520A 	17032	SO 					PISTON SCRAPER	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11							112746			PISTON SCRAPER RING WAS BROKEN AT ASSEMBLY. PART OF THE BROKEN RING WAS IN THE OIL SUMP.											3	O			E5CE				 
1995051200471	19950512	00471	SO 	1995	5	12	95ZZZX2315 	2	19950419	G	8520	SA530213	ROD BOLT 								CONT 	O200 	O200A 	17020	SO 					CON ROD	MISMANUFACTURED 	B			CT3R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	17										INSPECTION OF CONNECTING ROD BOLTS REVEALED ONE SIDE OF THE BOLT HEAD WAS FLAT ON THE EDGE INSTEAD OF ROUND. SUBMITTER 	SUGGESTS IN VIEW OF ALL THE PROBLEMS INVOLVING SUPERIOR PARTS. THIS IS SUSPECT.										3	O			E252				 
1995051200472	19950512	00472	EA 	1995	5	12	95ZZZX2316 	2	19950420	G	8530	SL74241P10	RING 								LYC 	O360 	IO360A1B 	41514	EA 					NR 1 CYLINDER	DEFECTIVE 	B			CT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17							L2282151A			AFTER 2-HOUR TEST RUN, NR 1 CYLINDER WAS STILL BURNING OIL AND HAD NOT SEATED. INSPECTION OF THE CYLINDER FOUND CHROME 	HAD CHIPPED OFF THE EDGE OF THE RING AT THE GAP. IT APPEARS TO BE A MANUFACTURING DEFECT.										3	O			1E10				 
1995051200473	19950512	00473	CE 	1995	5	12	95ZZZX2317 	1	19950428	G	2410		BRACKET 		1101912 	CESSNA	182 	182G 	2072716	CE 										GENERATOR	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	3281S				4165	18255781				DURING ANNUAL INSPECTION, GENERATOR BELT WAS FOUND LOOSE. INVESTIGATION SHOWED THE REAR BRACKET OF THE GENERATOR WAS BR	OKEN. THE BRACKET WAS REPLACED. A/C TOTAL TIME 4,645 HRS. TIME ON PART UNKNOWN.					1	H	7	1 	3O			NT	3A13 					 
1995051200474	19950512	00474	CE 	1995	5	12	95ZZZX2318 	1	19950410	G	2571		BATTERY VENT 			CESSNA	172 	R172K 	2072431	CE 										AFT BAG COMPT	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	758HV	2197 				R1723117				BATTERY ACID IN BELLY OF AIRCRAFT FROM BATTERY BOX FORWARD. CAUSED FROM BATTERY BOX OVERBOARD VENT DISCONNECTING FROM B	OX WHEN BATTERY IS REMOVED. OVERBOARD VENT SHOULD BE CLAMPED TO BATTERY BOX TO PREVENT PROBLEM.					1	H	7	1 	3O				3A17 					 
1995051200475	19950512	00475		1995	5	12	95ZZZX2319 	1	19950419	G	7922	53E19600	VALVE 								LYC 	O540 	AEIO540D4A5 	41532	EA 					THERMO BYPASS	CRIMP NUT LOOSE 	B			CT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17							L2334348A			BYPASS VALVE REMOVED TO COMPLY WITH LYCOMING SB 518A. THE NUT WAS FOUND LOOSE AND HALF-WAY UNSCREWED FROM THE THREADED 	SHAFT OF THE VALVE. IT WAS NOTED THE SERIAL NUMBER OF VALVE WAS HIGHER THAN THE AFFECTED SERIAL NUMBERS LISTED IN SB. R	ECOMMEND INSPECTION PER SB OF ALL VALVES REGARDLESS OF SERIAL NUMBERS. SB SHOULD BE AMENDED OR AN AD ISSUED.									3	O			1E4				 
1995051200476	19950512	00476	SO 	1995	5	12	95ZZZX2320 	1	19950315	G	7160		HEAT BOX 			MAULE 	MX7 	MXT7180 	5470206	SO 										CARBURETOR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	800CP	400 				14058C				DURING THE COURSE OF AN ANNUAL INSPECTION, CARBURETOR HEAT BOX FOUND CRACKED ON BOX AREA 5 INCHES LONG AND AROUND THROAT	 AREA RADIUS CRACKED 2 INCHES LONG. CARBURETOR HEAT BOX MOUNTS UP TO HORIZONTAL CARBURETOR. TOTAL TIME SINCE NEW 399.9	9. MAY BE A VIBRATION PROBLEM OR HEAT BOX METAL MAY BE TOO THIN.				1	H	7	1 	3O			NC	3A23 					 
1995051200477	19950512	00477	SO 	1995	5	12	95ZZZX2321 	2	19950420	G	8520		CAMSHAFT 			BEECH 	33 	F33A 	1151425	CE 	CONT 	O550 	IO550B 		SO 					NR 5 CYLINDER	LOBES ROUNDED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	7289R	1100 				TC1829	249218R			PILOT COMPLAINED OF FOULED PLUGS. REMOVED NR 5 CYLINDER, FOUND CAMSHAFT LOBES ROUNDED AND FOLLOWERS SPALLED. ALSO, FOU	ND VERY VISIBLE WEAR OF THE PISTON PIN. FOUND SOME EVIDENCE THERE MAY HAVE BEEN SOME CORROSION ON PIN AND FOLLOWERS. H	OWEVER, THE ENGINE WAS OPERATED REGULARLY. IT HAS ACCUMULATED 1100 HRS IN 4.5 YEARS.				1	L	7	1 	3O	3	O		3A15 	E3SO				 
1995051200478	19950512	00478	SO 	1995	5	12	95ZZZX2322 	1	19950412	G	3010	950D0123001	TIMER 			PIPER 	PA31T 	PA31T1 	7103126	SO 										DEICE	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	9266Y					31T1104008				THE DEICE TIMER IS INTERMITTENT ON THE GROUND AND IS INOPERABLE AFTER SEVERAL MINUTES OF OPERATION IN-FLIGHT.						1	L	7	2 	3T				A8EA 					 
1995051200479	19950512	00479	SO 	1995	5	12	95ZZZX2323 	2	19950401	G	8520	646297	BRACKET 			BEECH 	36 	A36 	1151604	CE 	CONT 	O550 	IO550B 		SO 					CYLINDERS 2-4	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	4759M					E1300	249125R			SEVENTH STUD, CYLINDERS 2 AND 4: BRACKET BROKEN IN HALVES. ONE ONE-HALF FOUND LYING NEXT TO KEEL, OTHER ONE-HALF MISSI	NG. (ANNUAL 100-HOUR INSPECTION.) REPLACED BRACKET AND NUT, PN 646312. SUSPECT CAUSE: PROGRESSIVE CRACK LEADING TO U	LTIMATE FAILURE.				1	L	7	1 	3O	3	O		3A15 	E3SO				 
1995051200480	19950512	00480	SO 	1995	5	12	95ZZZX2324 	1	19950503	G	5312	6244400	BULKHEAD 			PIPER 	PA28 	PA28150 	7102804	SO 										STA 228.3	CORRODED 	G	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	5849W	3846 				282293				SEVERE CORROSION ON BULKHEAD LOCATED AT STA 228.3. THE CORROSION IS AT THE UPPER PART OF THE BULKHEAD WHERE THE FORWARD	 STEEL ATTACHMENT FITTING IS LOCATED. THIS STEEL FITTING SERVES AS THE FORWARD VERTICAL STABILIZER ATTACHMENT POINT. P	IPER SB 977 DOES NOT COVER THIS SUBJECT. THIS CONDITION WAS VERY DIFFICULT TO DETECT. THE ONLY INDICATION WAS A VERY S	LIGHT AMOUNT OF PITTING ON THE DOUBLER.			1	L	7	1 	3O				2A13 					 
1995051200481	19950512	00481	SO 	1995	5	12	95ZZZX2325 	1	19950503	G	5341	62695003	FRAME ASSY 		6269500 	PIPER 	PA28 	PA28150 	7102804	SO 										FWD OF BAGGAGE	CORRODED 	G	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	5849W	3846 				282293				SEVERE CORROSION ON THE REAR WING CARRY-THROUGH SPAR LOCATED AT STA 128.737. THE CORROSION IS LOCATED WHERE THE WING RE	AR ATTACH FITTING IS LOCATED. PIPER SB 977 COVERS THIS SUBJECT. THIS CORROSION WAS VERY DIFFICULT TO DETECT EVEN WHEN 	COMPLYING WITH THE PIPER SB.				1	L	7	1 	3O				2A13 					 
1995051900459	19950519	00459	NM 	1995	5	19	95ZZZX2363 	1	19950428	G	2752	6522244	SUPPORT FITTING 			BOEING	707 	707338C 	138367N	NM 										RT FILLET FLAP	CRACKED 	B			GZ1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	770JS					19626				PERFORMING A FLEET COMPANY INSPECTION, THE LT FILLET FLAP TRANSMISSION SUPPORT FITTING WAS FOUND CRACKED. SUPPORT FITTI	NG IN THE PROCESS TO BE REPLACED IAW BOEING SIB 3251, REV. 2.					2	L	7	4 	4F				4A26 					 
1995051900461	19950519	00461	EU 	1995	5	19	95ZZZX2365 	1	19950315	G	6320	4639302037	SEAL 		72B 	BOLKMS	105 	BO105C 	5626005	EU 										INPUT QUILL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	23	505TJ	5701 	1601 		1054	S186				NOTICED OIL ON TRANSMISSION DECK DURIING POST-FLIGHT AFTER FIRST FLIGHT OF THE DAY, 3-15-95. SUSPECT CHANGES IN TEMPERA	TURE OR LACK OF FLYING.					1	G	7	2 	3U				H3EU 					 
1995051900462	19950519	00462	WP 	1995	5	19	95ZZZX2366 	1	19950427	G	6320	369D2512711	RING GEAR 			HUGHES	369 	369D 	4470706	WP 										M/R TRANSMISSION	DEFECTIVE 	B			EOOR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03										UPON INPSECTION PRIOR TO ASSEMBLY IN A M/R TRANSMISSION, ONE OF THE BOLT HOLES WAS DISCOVERED TO HAVE VOIDS IN THE WALL 	OF THE HOLE DEEPER AND PERPENDICULAR TO THE THREADS. PART WAS RETURNED TO MANUFACTURER.					1	G	7	1 	3U				H3WE 					 
1995051900463	19950519	00463	GL 	1995	5	19	95ZZZX2367 	2	19950421	G	7230	6890550	COMPRESSOR 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	STALLS 	B			EOOR	K				NONE 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			AL	03	5074R	5623 	2432 			1151D	CAE832750			COMPRESSOR STALLS WITH SLIGHT BUT RAPID POWER CHANGES. NOTE: THIS ENGINE WAS REMOVED FROM ANOTHER A/C WITH THESE SYMPT	OMS AND ANOTHER ENGINE INSTALLED SO IT COULD START A JOB. THIS COMPRESSOR WAS INSTALLED FOR TROUBLESHOOTING WHEN THIS E	NGINE WAS INSTALLED IN 5074R. *(PREVIOUS MDR FOR THE SAME PROBLEM WAS FILLED OUT ON THIS ENGINE WHEN IT WAS INSTALLED O	N N3115Y). BOTH COMPRESSORS HAVE BEEN SENT IN FOR REPAIR.			1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995051900464	19950519	00464	GL 	1995	5	19	95ZZZX2368 	2	19950425	G	7323	23007506	GOVERNOR 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V		478 		4447	490487D	CAE830976			'BEEP' RANGE IS ERRATIC. RPM JUMPS FROM POINT-TO-POINT DURING SMOOTH GOVERNOR TRIM MOTOR ACTUATION. UNIT SENT IN FOR R	EPAIR ON ALLISON 250 REPORT NR A160118.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995051900465	19950519	00465	GL 	1995	5	19	95ZZZX2369 	2	19950430	G	7323	23007506	GOVERNOR 		6887190 	HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y		917 		17979	500716D	CAE838348			PILOT COULD NOT MAKE SMOOTH 'BEEP' ADJUSTMENTS. REMOVED AND REPLACED UNIT. FELT A NOTCH IN THE ROTATION OF THE LEVER A	RM. UNIT SENT TO BE REPAIRED ON ALLISON 250 REPORT A160119.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995051900467	19950519	00467	WP 	1995	5	19	95ZZZX2371 	1	19950428	G	5343	369H600151	GEAR LEG 			HUGHES	369 	369D 	4470706	WP 										KEEL ATTACH RT	LOOSE 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y					490496D				DURING ANNUAL OF CUSTOMER AIRCRAFT, THE LANDING GEAR KEEL ATTACH FITINGS WERE FOUND LOOSE. PARTS WERE REMOVED AND NEW H	ARDWARE INSTALLED.					1	G	7	1 	3U				H3WE 					 
1995051900468	19950519	00468	WP 	1995	5	19	95ZZZX2372 	1	19950428	G	5343	369H600152	GEAR LEG 			HUGHES	369 	369D 	4470706	WP 										KEEL ATTACH LT	LOOSE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y					490496D				DURING ANNUAL OF CUSTOMER AIRCRAFT, THE LANDING GEAR KEEL ATTACH FITINGS WERE FOUND LOOSE. PARTS WERE REMOVED AND NEW H	ARDWARE INSTALLED.					1	G	7	1 	3U				H3WE 					 
1995051900469	19950519	00469	SO 	1995	5	19	95ZZZX2373 	2	19950429	G	8520		CONNECT RODS 								CONT 	O520 	IO520A 	17032	SO 					CRANKSHAFT	OUT OF BALANCE 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11							112746			THE CONNECTING ROD WEIGHTS ON THE LARGE END FROM THE LIGHTEST TO THE HEAVIEST WAS 57 GRAMS.											3	O			E5CE				 
1995051900470	19950519	00470	EA 	1995	5	19	95ZZZX2374 	2	19950417	G	8550		BOLT 								LYC 	O320 	O320B2C 	41508	EA 					OIL SUMP	MISSING 	B			YV3R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	05							L1656639A			ONE BOLT, PN STD-1204, NUT, P/N STD-1411 AND WASHERS, P/N STD-160 AND STD-8 WERE MISSING FROM THE OIL SUMP-TO-CRANKCASE 	INSTALLATION. THE AREAS NORMALLY COVERED BY THE BOLT AND NUT DURING PAINTING OF THE ENGINE WERE PAINTED, INDICATING THA	T THE PARTS WERE OMITTED DURING ASSEMBLY. THIS WAS A LYCOMING FACTORY OVERHAUL; WORK ORDER A-3996. RHC CRS YV3R012M.									3	O			E274				 
1995051900471	19950519	00471		1995	5	19	95ZZZX2375 	2	19950404	G	7322	MA4SPA	CARBURETOR 	FACET 																THROTTLE SHAFT	WORN 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			WP	07					BL2011688					PILOT REPORTED ENGINE RAN/IDLED ROUGHLY AND WAS HARD TO START. ROUGH/ERRATIC IDLE NARROWED DOWN TO CARBURETOR. UNIT RE	MOVED FOR INSPECTION. THROTTLE SHAFT AND BUSHINGS WORN BADLY ALLOWING AIR TO BLEED BY. ALSO FOUND ONE STEEL SCREW MISS	ING FROM BUTTERFLY. UNABLE TO LOCATE MISSING SCREW. FOUND NO EVIDENCE OF DAMAGE TO CYLINDERS, PISTONS, VALVES, HEADS. 	 USED PROCTOSCOPE FOR ENGINE INSPECTION. WORKS GREAT. UNIT (CARB) SENT OUT FOR OVERHAUL, REINSTALLED, OPS CHECKS GOOD.																 
1995051900472	19950519	00472	CE 	1995	5	19	95ZZZX2376 	1	19950503	G	3230	4603522	CASTING 			BEECH 	MU300 	400BEECH 		CE 										RT MLG DOWNLOCK	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	8239E	784 				RK46				DURING INSPECTION, FOUND DOWNLOCK CASTING CRACKED ON RIGHT MLG, REPLACED CASTING WITH NEW. NOTE: CASTING CRACKED BY FO	RGE/CAST LINE.					2	H	7	2 	4F			RT	A16SW 					 
1995051900473	19950519	00473	EA 	1995	5	19	95ZZZX2377 	2	19950427	G	7414	10357281H	CAPACITOR 	BENDIX 	S4LN200 						LYC 	O360 	IO360A1A 	41514	EA 					MAG	SHORTING 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15										INVESTIGATION FOR AN INTERMITTENT DEAD MAG FOUND SPRING STRAP TOUCHING HOUSING AS P-LEAD IS PUSHED INTO COVER.											3	O			1E10				 
1995051900474	19950519	00474	SO 	1995	5	19	95ZZZX2378 	2	19950424	G	8530		CYLINDER 			CESSNA	206 	U206F 	2073333	CE 	CONT 	O520 	IO520A 	17032	SO 					BASE	MISINSTALLED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	07	7144Q					U20603075	553939			TOTAL TIME 1067.8 SMOH. TIME SINCE TOP OVERHAUL 125.0. DURING MAINTENANCE TO REPAIR BURNED VALVES UPON CYLINDER REMOVA	L, FOUND CYLINDERS GLUED ON AT BASE. (IT TOOK OVER AN HOUR USING AIR PRESSURE AND PULLING AND PRYING TO REMOVE ONE CYLI	NDER). IT SEEMS THAT A FOREIGN SUBSTANCE WAS APPLIED AROUND O-RING AT THE CYLINDER BASE. SUBMITTER BELIEVES THIS IS A 	CASE OF IMPROPER MATERIALS BEING USED.			1	H	7	1 	3O	3	O		A4CE 	E5CE				 
1995051900475	19950519	00475	SO 	1995	5	19	95ZZZX2379 	2	19950427	G	8520	633258	CRANKSHAFT 			BEECH 	35 	J35 	1151522	CE 	CONT 	O470 	IO470C 	17026	SO 					FLANGE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	8330D	1870 				D5483	8777380R			REMOVED PROPELLER TO REPLACE CRANKSHAFT SEAL. FOUND CRANKSHAFT FLANGE SEVERELY CORRODED. REMOVED ENGINE FROM SERVICE F	OR CRANKSHAFT REPLACEMENT. ENGINE HAD BEEN OVERHAULED BY AN 'IA' JUST 75 HOURS AND 3 YEARS PREVIOUS TO THIS DISCOVERY. 	 SUBMITTER BELIEVES CORROSION EXISTED AT THAT TIME.				1	L	7	1 	3O	3	O		3A15 	E273				 
1995051900476	19950519	00476	SO 	1995	5	19	95ZZZX2380 	1	19950426	G	5712	7847505	RIB 			PIPER 	PA34 	PA34200 	7103405	SO 										FS 49.25 LT WELL	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	44416	2630 				347450209				THIS RIB IS LOCATED AT STA 49.25, IN THE MAIN LANDING GEAR WELLS. FOUND 3 SENECA'S WHERE THIS RIB HAS BEEN CRACKED IN T	HE RADIUS OF THE OUTBOARD ANGLE UNDER THE DRAG BRACE SUPPORT. PIPER PA-28R HAS THIS SAME PROBLEM. SUSPECT THE CAUSE IS	 FROM HARD OR GRASS STRIP LANDING. SUBMITTER SUGGESTS THERE SHOULD BE AN AD ISSUED TO INSPECT THESE RIBS EVERY 100 HOUR	S OR REPLACE THEM WITH AN IMPROVED DESIGN RIB FROM PIPER.			1	L	7	2 	3O				A7SO 					 
1995051900477	19950519	00477	SO 	1995	5	19	95ZZZX2381 	1	19950426	G	5712	7847504	RIB 			PIPER 	PA34 	PA34200 	7103405	SO 										FS 49.25 RT WELL	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	44416	2630 				347450209				THIS RIB IS LOCATED AT STA 49.25, IN THE MAIN LANDING GEAR WELLS. FOUND 3 SENECA'S WHERE THIS RIB HAS BEEN CRACKED IN T	HE RADIUS OF THE OUTBOARD ANGLE UNDER THE DRAG BRACE SUPPORT. PIPER PA-28R HAS THIS SAME PROBLEM. SUSPECT THE CAUSE IS	 FROM HARD OR GRASS STRIP LANDING. SUBMITTER SUGGESTS THERE SHOULD BE AN AD ISSUED TO INSPECT THESE RIBS EVERY 100 HOUR	S OR REPLACE THEM WITH AN IMPROVED DESIGN RIB FROM PIPER.			1	L	7	2 	3O				A7SO 					 
1995051900479	19950519	00479	CE 	1995	5	19	95ZZZX2383 	1	19950423	G	3260	63210075	SWITCH 			CESSNA	402 	402C 	207590R	CE 										LT UPLOCK	REQ ADJ 	I				O				OTHER 				N			FALSE WARNING 			CL	CLIMB 	1			SO	17	2651Y					402C0343				PILOT REPORTED THAT WITH GEAR UP AND LOCKED, THE RED UNSAFE LIGHT REMAINED ON. GEAR CYCLED AND SAME PROBLEM. ALL OTHER	 PARAMETERS NORMAL. CYCLED GEAR ON JACKS, ADJUSTED LT UPLOCK SWITCH OUT, ONE-QUARTER TURN. OPERATED GEAR, TOTAL OF TEN	 TIMES, ALL NORMAL.				1	L	7	2 	3O				A7CE 					 
1995051900482	19950519	00482	SO 	1995	5	19	95ZZZX2387 	2	19950215	G	7414	S6RN1225	MAGNETO 	BENDIX 		BEECH 	55 	9555 	1152702	CE 	CONT 	O470 	IO470L 	17026	SO 					LT MAG	CASE CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09		1727 			A209204					MAG REMOVED DURING ANNUAL INSPECTION TO INSURE AD COMPLIANCE. FOUND CASE CRACKED FROM MATING SURFACE DRIVE END TO AN AR	EA HALF-WAY ON THE CASE. CAUSE UNKNOWN. M OR D REPORT SUBMITTED TO ADD TO DATA BASE. REPLACED MAG. POSITION OF MAGNE	TO ON ENGINE WOULD MAKE DISCOVERY OF CRACK VERY DIFFICULT UNLESS REMOVED.				1	L	7	2 	3O	3	O		3A16 	3E1				 
1995051900483	19950519	00483	GL 	1995	5	19	95ZZZX2388 	3	19950324	G	6114	C5892C93	HUB 													MCAULY	3AF32C	3AF32C93 	GL 	SOCKETS 1-3	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								78527		UPON INSPECTION, HUB WAS FOUND CRACKED IN BLADE SOCKETS NR 1 AND NR 3. HUB HAS BEEN SCRAPPED.																5	C	P22EA	 
1995051900484	19950519	00484	GL 	1995	5	19	95ZZZX2389 	2	19950427	G	8530	SA10203	CYLINDER 			CESSNA	150 	150 	2071802	CE 	AMTR 	CUSHMN	O200 	05645	GL 					NR 2 CYLINDER	CRACKED 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	07	6400T	500 				17800				ENGINE HAD MINOR OIL LEAK FOR APPROXIMATELY 100 HOURS. IN ONE WEEK, OIL LEAK BECAME SEVERE. FOUND NR 2 CYLINDER BARREL	 CRACKED ABOUT 4 INCHES FORM BASE OF CYLINDER. CYLNDER HELD 74 POUNDS OF COMPRESSION. SUBMITTER IS OF THE OPINION THE 	CRACK WAS CAUSED FROM A MANUFACTURING DEFECT.				1	H	7	1 	3O	3	O	NT	3A19 	EXPA3O				 
1995051900485	19950519	00485	SO 	1995	5	19	95ZZZX2390 	1	19950427	G	7810	646463190	TAILPIPE 			PIPER 	PA46 	PA46310P 	7104605	SO 										TURBO FLANGE	CRACKED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9106V	692 				4608026				ONE-HUNDRED HOUR INSPECTION/ANNUAL, RT TAILPIPE CRACKED AT TURBO MOUNTING FLANGE. SUSPECT CAUSE: NORMAL WEAR AND VIBRA	TION. RECOMMEND RETORQUING CLAMP, PN 646434, AT 50-HOUR INTERVAL.					1	L	7	1 	3O				A25SO 					 
1995051900486	19950519	00486	SO 	1995	5	19	95ZZZX2391 	1	19950427	G	7810	646463170	TAILPIPE 			PIPER 	PA46 	PA46310P 	7104605	SO 										WASTEGATE FLANGE	CRACKED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9106V	692 				4608026				ONE-HUNDRED HOUR INSPECTION/ANNUAL, LT TAILPIPE CRACKED AT WASTEGATE MOUNTING FLANGE. SUSPECT CAUSE NORMAL WEAR AND VIB	RATION. RECOMMEND RETORQUING CLAMP, PN 646434, AT 50-HOUR INTERVALS.					1	L	7	1 	3O				A25SO 					 
1995051900487	19950519	00487	SO 	1995	5	19	95ZZZX2392 	1	19950404	G	5711	62054001	SPAR 			PIPER 	PA28 	PA28180 	7102808	SO 										FUSE PLATE RT	CORRODED 	H	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	7667W	3643 				281645				DURING ANNUAL INSPECTION, NOTICED BULGING UNDER RIGHT REAR SPAR FUSELAGE ATTACH PLATE. SEVERAL RIVETS ALSO HAD HEADS MI	SSING. REMOVED STEEL PLATE FROM SPAR, FOUND SEVERE CORROSION OF SPAR. INSTALLED NEW SPAR. CLOSE INSPECTION OF THESE O	LDER AIRPLANES NEEDS TO BE GIVEN PARTICULARLY WHERE STEEL AND ALUMINUM ARE RIVETED TOGETHER.				1	L	7	1 	3O				2A13 					 
1995051900488	19950519	00488		1995	5	19	95ZZZX2393 	2	19950509	G	7414	10400183	CONTACT POINTS 	BENDIX 	D6RN2230 															MAGNETO	MISMANUFACTURED 	B		A	MY2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	09										CENTRAL CYLINDER SERVICE, INC., OF OMAHA, NE, REPORTED 2 CASES OF UNAIRWORTHY TELEDYNE CONTINENTAL MOTORS MAGNETO POINTS	 OBTAINED FROM AVIALL AND AMR COMBS AS FACTORY NEW REPLACEMENT PARTS. MAG POINT ASSYS ARE CURRENTLY APPROVED FOR INSTAL	LATION ON THE BENDIX D-3000 SERIES MAG, PN 10-382610-221, MODEL D6RN-2230. TCM MAG POINT, PN 10-400183, BATCH NR 9438, 	EXHIBITS IMPROPER RIVET CRIMPING FOR THE OUTBOARD POINT ASSY WHICH ALLOWS SEVERE POINT ROTATION. TCM MAG POINT, PN 10-4	00183, BATCH NR 9437, EXHIBITS GROSS MIS-ALIGNMENT OF THE POINT CONTACT ASSYS.															 
1995051900490	19950519	00490	SO 	1995	5	19	95ZZZX2395 	2	19950321	G	8530	632485	PUSH TUBE 								CONT 	O520 	GTSIO520* 	17032	SO 					SEAM	CORRODED 	B			C6YR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										PUSH TUBE WAS SENT IN FOR REPLATING. AFTER CLEANING PUSH TUBE, CORROSION WAS FOUND IN SEAM PENTRATING THROUGH THE TUBE.	 PUSH TUBES SHOULD BE MADE FROM SEAMLESS TUBING.										3	O			E7CE				 
1995051900675	19950519	00675	SW 	1995	5	19	95ZZZX2397 	1	19950501	G	5210		ROLL PINS 			BELL 	206 	206B 	1181511	SW 										CABIN DOOR	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										DURING MAJOR INSPECTIONS WHEN CABIN AND DOOR ACCESS PANELS ARE OPENED AND LATCH MECHANISMS INSPECTED, ROLL PINS ARE BEIN	G FOUND LOOSE, SPLIT, AND/OR BROKEN. SUBMITTER RECOMMENDS SAFETY WIRE THROUGH ROLL PINS AND CAUTION NOT TO RE-USE ROLL 	PINS. IF ROLL PINS DROP OUT, OCCUPANTS COULD PULL HANDLE AND IT COULD COME OFF IN THEIR HAND. ALSO, FINDING SCREWS TOO	 LONG FOR ACCESS PANELS, CHAFING LATCH CONTROL MECHANISM.			1	G	7	1 	3U				H2SW 					 
1995051900676	19950519	00676	SW 	1995	5	19	95ZZZX2398 	1	19950418	G	6322	214076333107	MOTOR 	SUNDSTRANDEM		BELL 	214 	214ST 	1182106	SW 										COOLER BLOWER	SEAL BLOWN 	E				O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	03	5748M					28102				OIL COOLER BLOWER LIGHT CAME ON. SWITCHED TO SECONDARY SYSTEM. NO TEMP LIMITS EXCEEDED. FOUND SEAL BLOWN IN HYDRAULIC	 BLOWER MOTOR. IPC 63-22-00, FIGURE 3, ITEM 50.					2	G	7	2 	4U				H10SW 					 
1995051900677	19950519	00677	NE 	1995	5	19	95ZZZX2399 	1	19950327	G	6320	S6135206147	CAMSHAFT 			SKRSKY	S61 	S61A 	814210C	NE 										M/R GEARBOX	CRACKED 	B	S	A	JYER	O				OTHER 				E			VIBRATION/BUFFET 			NR	NOT REPORTED 	1			NM	09	1048Y	205 				61161				PILOT HEARD AN UNUSUAL GROWLING NOISE FROM THE NR 1 INPUT AT REDUCED POWER. A FEW HOURS LATER, A SLIGHT VIBRATION AT RE	DUCED POWER WAS FELT IN THE AIRFRAME. THE CHIP PLUG AND SCREEN WERE CHECKED AND A FEW SMALL SLIVERS WERE FOUND ON THE C	HIP PLUG AND 12 SMALL FLAKES OF MAGNESIUM IN THE SCREEN. ON DISASSEMBLY OF GEAR BOX INPUT SECTION, NR 1 CAMSHAFT WAS FO	UND BROKEN. INPUT CAMSHAFT IS BEING SENT TO A LAB FOR FRACTURE ANALYSIS. REF: OPER CONTROL NR JYER5329.			2	G	7	2 	4U				H2EA 					 
1995051900678	19950519	00678	NE 	1995	5	19	95ZZZX2400 	1	19950504	G	5320	S61806316114	FITTING 			SKRSKY	S61 	S61A 	814210C	NE 										RT AFT FUSELAGE	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1043T	23158	10826			61083				RIGHT REAR FUSELAGE FITTING HAD A SMALL CRACK ON INSIDE OF REAR EAR. CRACK WAS FOUND BY DYE CHECK OF FITTING WHILE DOIN	G A LANDING GEAR CHANGE. RECOMMEND DYE CHECK OF FITTING ANY TIME GEAR IS REMOVED.					2	G	7	2 	4U				H2EA 					 
1995051900679	19950519	00679	WP 	1995	5	19	95ZZZX2401 	1	19950503	G	6320	369D25100505	TRANSMISSION 			HUGHES	369 	369D 	4470706	WP 										SCAVENGE OIL	PUMP DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V	5492 	1491 			490487D				DURING PRE-FLIGHT, PILOT FELT A ROUGH CLUNK IN THE ROTOR SYSTEM. AS THE ROTOR WAS TURNED, SUBSEQUENT INSPECTION FOUND T	HE GEAR OIL PUMP OF THE MAIN ROTOR TRANSMISSION REQUIRED A VERY HIGH BREAK-AWAY TORQUE TO BEGIN ROTATION AND AFTER THAT,	 IT WAS RATCHETY. UNIT REMOVED AND SENT IN FOR OVERHAUL.				1	G	7	1 	3U				H3WE 					 
1995051900680	19950519	00680	WP 	1995	5	19	95ZZZX2402 	1	19950411	G	5610	269A23457	SUPPORT 			HUGHES	269 	269C 	4470504	WP 										CANOPY	CRACKED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	07	7511E					S1693				THIS CANOPY SLAT IS A NEW DESIGN FROM SCHWEIZER. IT IS OF ALL ALUMINUM CONSTRUCTION AND REPLACES THE OLDER FIBERGLASS S	LAT. THIS NEW TYPE SLAT APPEARS TO BE SLIGHTLY WIDER THAN THE PREVIOUS TYPE. WHEN IT'S BOLTED TO THE CABIN, IT BOWS SL	IGHTLY AT THE CENTER SECTION. THE MFG WAS NOTIFIED BY US ABOUT THIS CONDITION, AND WE SUGGESTED THAT SPACERS OF VARIOUS	 THICKNESS WOULD CURE PROBLEM. THE MFG REJECTED THIS IDEA. AS A RESULT, WE HAVE FOUND THE CENTER SUPPORT RIVET HOLES E	ITHER CRACKED OR PULLED THROUGH ON SEPARATE OCCASIONS. THE FIRST SUPPORT FAILED WTIH 3-6 HRS ON IT, THE SECOND SUPPORT 	FAILED HAD 125 HRS ON IT WHEN IT WAS REPLACED.	1	G	7	1 	3O				4H12 					 
1995051900681	19950519	00681	WP 	1995	5	19	95ZZZX2403 	1	19950419	G	7120	AN637A	BOLT 			ROBSIN	R22 	R22 	7640102	WP 										TOP RT ENG MOUNT	BROKEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	8062H	1895 				1172				AFTER A NORMAL FLIGHT AND NORMAL LANDING, UPPER RIGHT ENGINE MOUNT BOLT WAS FOUND BROKEN. THE BREAK WAS ON THE SHANK AD	JACENT TO THE SHIMS BETWEEN THE ENGINE MOUNT AND THE FRAME. SLIGHT FRETTING CORROSION AND A VERY SMALL CIRCUMFERENTIAL 	SCRATCH WAS FOUND AT THE ORIGIN OF THE CRACK. SUBMITTER RECOMMENDS REPLACEMENT OF ALL 4 AN6-37A BOLTS WITH NAS6606-54 W	HEN ENGINE RE-SHIMMING IS PERFORMED. ALSO, USE OF CORROSION PREVENTIVE COMPOUND ON THE BOLT SHANK MAY HELP.			1	G	7	1 	3O				H10WE 					 
1995051900682	19950519	00682	NE 	1995	5	19	95ZZZX2404 	2	19950417	G	7323	430128701	GOVERNOR 		2860 	SNIAS 	350 	AS350D 	8680803	EU 	LYC 	LTS101	LTS101600A3 	41560	NE 					POWER TURBINE	FAILED 	D		A		A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			WP	13	138EH		513 			1403	LE434500E			DURING FLIGHT, EXPERIENCED LOW SIDE GOVERNOR FAILURE (LOW POWER). THE PILOT JUST LIFTED OFF PAD NR 1, ACFT WAS ABOUT 4 	FEET OFF DECK, PILOT MANAGED TO SET IT BACK DOWN WITHOUT ANY INCIDENT OR DAMAGE TO THE AIRCRAFT. PILOT TOOK ANOTHER SHI	P AND THE SAME PASSENGERS AND COMPLETED THE TOUR. THE MECHANIC REMOVED P.T. GOV. TSO 513.6, AND INSTALLED SERVICEABLE 	ONE AND C/W OPERATIONAL AND A MAX TOPPING CHECK FLIGHT AND PASSED CHECK FLIGHT.			1	G	7	1 	3U	3	U		H9EU 	E5NE				 
1995051900683	19950519	00683	CE 	1995	5	19	95ZZZX2405 	1	19950428	G	5740	8113507	FITTING 			CESSNA	421 	421C 	2076016	CE 										FRONT SPAR	CORRODED 	B	S	A	YXRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	421CC	4300 				421C0133				DURING MAJOR AIRFRAME REPAIR WITH WINGS OFF, INSPECTION OF THE WING ATTACH FITTINGS REVEALED BOTH LEFT AND RIGHT UPPER M	AIN SPAR FITTINGS HAD INTERGRANULAR CORROSION AT THE POINT WHERE THE FITTINGS CAME OUT OF THE FUSELAGE SPAR ASSEMBLY. T	HERE WAS NO APPARENT CONTAMINATION OF THE AREA SUCH AS PAINT STRIPPER, ETC. BOTH FITTINGS WERE REPLACED WITH NEW PARTS.				1	L	7	2 	3O				A7CE 					 
1995051900684	19950519	00684	SO 	1995	5	19	95ZZZX2406 	2	19950403	G	8530		CYLINDER 			PIPER 	PA60 	PA60601P 	7106012	NM 	CONT 	O520 	IO520* 	17032	SO 					LT ENG NR 2	HEAD SEPARATION 	B			VTMR	A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			WP	05	8244J	982 				61P0648796	L1918148A			CYLINDER HEAD SEPARATED FROM CYLINDER BARREL IN-FLIGHT. THE ENGINE KEPT RUNNING, PILOT REDUCED POWER AND LANDED ACFT WI	TH NO OTHER DAMAGE TO ENGINE OR AIRCRAFT. THE CYLINDER, HEAD, AND PISTON ARE AT SHOP FOR INSPECTION.					1	M	7	2 	3O	3	O	RT	A17WE 	E5CE				 
1995051900685	19950519	00685	SO 	1995	5	19	95ZZZX2407 	1	19950401	G	7922	75944	VALVE 			PIPER 	PA32 	PA32301T 	7103209	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			QZRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	8433A				124423	328124032				REMOVED VALVE FOR INSPECTION PER MSB518A. FOUND NUT IN QUESTION TO BE SEPARATED FROM SHAFT. NUT WAS FOUND CRIMPED AS R	EQUIRED. CRIMPING OF NUT DOES NOT PRECLUDE SEPARATION FROM SHAFT.					1	L	7	1 	3O				A3SO 					 
1995051900686	19950519	00686	EA 	1995	5	19	95ZZZX2408 	2	19950509	G	7322		ADJUST SPRING 	BENDIX 	RSA10ED1 	PIPER 	PA36 	PA36300 	7103612	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					MIXTURE ADJ	FAILED 	G				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			CE	01	57866	2791 	911 			367760033	L1621048A			MIXTURE ARM ADJUSTMENT RETAINING SPRING BROKEN DUE TO ATTACHMENT END BEING WORN. WHEN SPRING BROKE, IT ALLOWED MIXTURE 	SETTING TO CHANGE WHICH CAUSED ENGINE TO RUN ROUGH AND LOST POWER. SUBMITTER RECOMMENDED A MORE SUBSTANTIAL SPRING THAT	 IS LESS SUSCEPTIBLE TO WEAR OR TO PROVIDE A MEANS OF SAFETYTING THE ADJUSTMENT ONCE THE PROPER MIXTURE SETTING IS OBTAI	NED AND IS MADE AVAILABLE.			1	L	7	1 	3O	3	O		A10SO 	1E4				 
1995051900687	19950519	00687	SO 	1995	5	19	95ZZZX2409 	1	19950405	G	3230		SHAFT ASSY 			PIPER 	PA42 	PA421000 	7104225	SO 										FWD MLG PIVOT	FLANGE CRACKED 	H	S	A		A				UNSCHED LANDING 				J			WARNING INDICATION 			CL	CLIMB 	1			WP	05	812BJ	1720 				425527020				MLG PIVOT SHAFT ASSY CONTAINS PIVOT SHAFT AND FWD ATTACH FLANGE. FWD ATTACH FLANGE MOUNTED TO MAIN WING SPAR. THIS ATT	ACH FLANGE FOUND CRACKED AND BROKEN OUT ALLOWING PIVOT SHAFT (WHICH IS BOLTED TO IT) TO MOVE AFT TOWARD WW. PILOT REPOR	TED CLUNK NOISE AT GEAR RETRACT, ACCOMPANIED BY GEAR UNSAFE LIGHT DURING RETRACT AND EXTENSION. INVESTIGATION FND PIVOT	 SHAFT FROM FWD MAIN GEAR SIDE BRACE EXTENDED 3 INCHES INTO WW. RT MAIN GEAR WOULD HAVE JAMMED IN WELL. UPON REPLACEME	NT, FOUND PIVOT SHAFT NOT LINING UP WITH BORE AT FWD AND AFT FLANGES. POOR ASSY LOCATING AND DRILLING AT FACTORY CAUSIN	G PRE-LOAD CONDITION DURING INSTALLATION.	1	L	7	2 	4T			RT	A23SO 					 
1995051900691	19950519	00691	CE 	1995	5	19	95ZZZX2413 	1	19950508	G	5347		TRACK 			CESSNA	340 	340CESSNA 	2076404	CE 										PILOT SEAT	DAMAGED 	B	P	A	FG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										INSPECTION FOUND DAMAGED SEAT TRACKS FOR THE CREW SEATS OF A CESSNA 340. THE FRONT PORTION OF BOTH TRACKS WERE MISSING 	WHICH COULD PITCH THE PILOT INTO THE REAR SEAT. THE CO-PILOT'S SEAT TRACKS WERE ALSO FRACTURED. THIS IS AN ITEM EASILY	 MISSED UNLESS THE SEAT IS VIEWED FROM THE BOTTOM AND IS CRUCIAL TO SAFETY. THIS STYLE SEAT IS USED IN MOST CESSNA TWIN	S.			1	L	7	2 	3O				3A25 					 
1995051900692	19950519	00692	CE 	1995	5	19	95ZZZX2414 	1	19950219	G	7120	5038913315	MOUNT 			BEECH 	100 	A100 	1152915	CE 										RT ENG TOP	BROKEN 	H		A	PRIS	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	151U	9945 				B143				AFTER AN UNEVENTFUL LANDING WAS MADE AND 2 PASSENGERS WERE DE-PLANED, FLIGHT CREW NOTICED RT ENGINE APPEARED TO BE SITTI	NG A COUPLE OF INCHES LOWER THAN LT ENGINE. UPON FURTHER INVESTIGATION, DETERMINED UPPER ENGINE MOUNT HOUSING HAD BROKE	N. ENGINE IS AFFIXED TO THE FRAME USING 3 MOUNTS IN A TRIANGULAR MANNER WITH A SINGLE MOUNT LOCATED AT THE TOP CENTER A	ND ONE ON EACH SIDE IN THE LOWER AREAS. A NEW REPLACEMENT MOUNT WAS INSTALLED AND ACFT FLOWN BACK TO PAL-WAUKEE AIRPORT	. WHEN IT ARRIVED, OTHER 2 MOUNTS WERE FURTHER INSPECTED AND REPLACED SO AS TO MATCH TOP MOUNT.		1	L	7	2 	3T				A14CE 					 
1995051900693	19950519	00693		1995	5	19	95ZZZX2415 	4	19950215	G	2215	108P4	SERVO 	STEC 		CESSNA	401 	401B 	207590E	CE 											JAMMED 	H		A		K				NONE 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			SW	99	3013Q					401B0013				PITCH CONTROLS JAMMED. UPON INSPECTION, FOUND PITCH SERVO BRIDLE CABLE RETAINING BALL HAD SLIPPED OUT OF SLOT AND JAMME	D AGAINST CABLE GUARD POST AND CAPSTAN. REMOVED SERVO AND NO DAMAGE EVIDENT, HOWEVER, WAS UNABLE TO TIGHTEN SET SCREW T	IGHT ENOUGH TO RETAIN BRIDLE CABLE BALL. ORDERED NEW CAPSTAN AND BRIDLE CABLE AND SCREW. REPLACED AND RESET CLUTCH SET	TINGS, REINSTALLED, OPS CHECKED GOOD AND WAS UNABLE TO DISLODGE BRIDLE CABLE BALL. RECOMMEND CLOSE INSPECTION AT ANNUAL	 OR 100-HOUR INSPECTION.		1	L	7	2 	3O				A7CE 					 
1995051900694	19950519	00694	CE 	1995	5	19	95ZZZX2416 	1	19950401	G	5700		LIFT STRUT 			BBAVIA	11 	11CC 	9140404	CE 										WING	CORRODED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4150E					57				REPLACE STRUT. X-RAY SHOWS NUMEROUS AREAS THAT ARE CORRODED COMPLETELY THROUGH STRUT WALL. A PIN WAS PUSHED THROUGH TH	E PAINT AND SHOWED THROUGH THE STRUT WALL IN SEVERAL LOCATIONS.					1	H	7	1 	3O				A796 					 
1995051900695	19950519	00695	SW 	1995	5	19	95ZZZX2417 	1	19950501	G	2842	6102421	SENDER 			MOONEY	M20 	M20J 	5870219	SW 										RT FUEL TANK	FLOAT DETACHED 	H		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	5211Z	547 				241653				WHILE TROUBLESHOOTING AN INACCURATE FUEL QUANTITY PROBLEM, DISCOVERED THE PLASTIC FLOAT ON THE END OF THE FUEL SENDER AR	M HAD COME OFF AND WAS FLOATING IN THE FUEL TANK. THE FLOAT IS RETAINED BY A WASHER AND CRIMPING OF THE END OF THE SHAF	T. THE CRIMP WAS INADEQUATE WHICH ALLOWED WASHER AND FLOAT TO COME OFF THE SHAFT RESULTING IN AN ERRONEOUS QUANTITY REA	DING. SUBMITTER RECOMMENDS A MORE POSITIVE METHOD OF FLOAT RETENTION BE UTILIZED DURING MANUFACTURE.			1	L	7	1 	3O				2A3 					 
1995051900696	19950519	00696	SW 	1995	5	19	95ZZZX2418 	1	19950331	G	2821		GASCOLATOR 			BBAVIA	7 	7AC 	2110102	SW 										FIREWALL	BOWL FAILED 	G		A		A				UNSCHED LANDING 				O			OTHER 			NR	NOT REPORTED 	1			WP	09	1937E					7AC5504				THIS AIRCRAFT WAS INVOLVED IN A FUEL STARVATION ACCIDENT BELIEVED CAUSED BY FAILURE OF GASCOLATOR GLASS BOWL. SAFETY WI	RE AND SAFETYING DEVICE STILL ATTACHED TO ASSY. CHAMPION ACFT CORP. SERVICE HINT NR 15 RECOMMENDS GLASS BOWLS BE REPLAC	ED WITH METAL UNITS DUE TO PREVIOUS FAILURES OF GLASS BOWLS CAUSED BY VIBRATION OR OVERTORQUING THE ADJUSTMENT CLAMP. T	OTAL AIRFRAME TIME 4,399.1 HRS.			1	H	7	1 	3O				A759 					 
1995051900697	19950519	00697	CE 	1995	5	19	95ZZZX2419 	1	19950501	G	2742	NAS56138	ROLL-PIN 		07125001 	CESSNA	185 	A185F 	2072821	CE 										HORIZ STAB ACT	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	24FG					18504207				DURING ROUTINE INSPECTION, FOUND ROLL-PIN WORKED APPROXIMATELY THREE-FOURTHS OF LENGTH OUT OF RETAINING COLLAR. THIS IS	 A DIFFICULT AREA TO INSPECT. SUBMITTER STATED THIS IS NOT THE FIRST TIME THIS CONDITION WAS FOUND. SAFETY WITH .020 I	NCH WIRE SHOULD CURE THIS PROBLEM.				1	H	7	1 	3O				3A24 					 
1995051900698	19950519	00698	EA 	1995	5	19	95ZZZX2420 	2	19950324	G	8550	4013383	BAFFLE 			PIPER 	PA32 	PA32R301 	7103218	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					OIL SUMP	FAILED 	B			AMYR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	923CN	466 				3213076	L2523848A			DURING REMOVAL OF OIL PAN TO CHANGE PAN GASKET, FOUND OIL SUMP BAFFLE COMING APART WHERE VERTICAL FINS ARE ATTACHED TO H	ORIZONTAL PART, FOUND ALL RIVETS LOOSE, ONE RIVET HEAD COMPLETELY MISSING.					1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995051900699	19950519	00699		1995	5	19	95ZZZX2421 	4	19950428	G	6113	D4247	BULKHEAD 			BEECH 	23 	C23 	1151242	CE 										SPINNER	CRACKED 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	5116R	397 				M2164				DURING 100-HOUR INSPECTION, FOUND CRACK EMANATING FROM MOUNT BOLT. UPON REMOVAL OF BULKHEAD, FOUND CRACKS AT EACH BOLT 	HOLE OF SPINNER BULKHEAD. THIS REPAIR STATION HAS REPLACED NUMEROUS D42R7 BULKHEADS AT LOW INSTALL TIMES. SUBMITTER SU	GGESTED CRACKS DUE TO POOR DESIGN AND POOR MANUFACTURING.				1	L	7	1 	3O				A1CE 					 
1995051900700	19950519	00700	SO 	1995	5	19	95ZZZX2422 	1	19950428	G	5712	7847505	RIB 			PIPER 	PA28 	PA28R201 	7102816	SO 										SPAR ATTACH	CRACKED 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	47227	4813 				28R7737158				DURING 100-HOUR INSPECTION UPON REMOVAL OF 95643-07 BRACKET ASSEMBLY, FOUND CRACK IN RIB ASSY AT SPAR ATTACH POINT. SUS	PECT CRACKING DUE TO AGE AND MANY SIDE LOAD LANDINGS BY STUDENTS. SUGGEST RIB BE MANUFACTURED FROM THICKER ALUMINUM.					1	L	7	1 	3O				2A13 					 
1995051900701	19950519	00701	EA 	1995	5	19	95ZZZX2423 	2	19950425	G	8530	76220	THROUGH-BOLT 			MOONEY	M20 	M20F 	5870214	SW 	LYC 	O360 	IO360A1A 	41514	EA 					NR 1 CYLINDER	FAILED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	7112V	2763 	1788 			220047	L12C2451A			SUBJECT NR 1 CYLINDER UPPER THROUGH-BOLT FOUND BROKEN DURING PRE-FLIGHT. DETECTED AS THE MAJOR REMAINING PORTION AND HO	LD-DOWN NUT FOUND BACKED OUT OF POSITION AND LODGED AGAINST CYL FINS. INST NEW BOLT, SPACER, AND NUT. TORQUED PER LYCOM	ING S.I. 10293. BOLT, THREADED END, BROKE OFF FLUSH WITH NUT'S SEATING SURFACE. INDICATIONS WERE A CRACK ABOUT 50 PERC	ENT ACROSS THE DIAMETER HAD EXISTED FOR SOME TIME AND BOLT ULTIMATELY FAILED IN A TYPICAL TENSILE FACTURE.			1	L	7	1 	3O	3	O		2A3 	1E10				 
1995051900702	19950519	00702	CE 	1995	5	19	95ZZZX2424 	1	19950405	G	3246	07100	BEARING 	BFGOODRICH 	50300010105 	BEECH 	18 	H18 	1151012	CE 										WHEEL	FAILED 	D				O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			SO	07	123MD				17	BA701				OUTER WHEEL BEARING CAME APART ALLOWING WHEEL TO COME OFF AIRCRAFT ON TAKEOFF.						1	L	7	2 	3R				A765 					 
1995051900703	19950519	00703	CE 	1995	5	19	95ZZZX2425 	1	19950508	G	7922	53E19600	VALVE 			BEECH 	23 	B24R 	1151253	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	B			BPGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	53EM		104 			MC395				CRIMP NUT LOOSE ON SHAFT PER SB 518B (LYCOMING) DATED 3-21-95. TIME SINCE FACTORY O/H, 104 HRS. OVERHAULED BY LYCOMING	 ON 12-22-92. PLACED IN SERVICE ON 3-1-93. REPLACED VALVE WITH NEW PARTS FROM LYCOMING.					1	L	7	1 	3O				A1CE 					 
1995051900704	19950519	00704	SO 	1995	5	19	95ZZZX2426 	1	19950401	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	2NS		398 			317305077				REF. LYCOMING MANDATORY SB 518B, CRIMPED NUT WAS ABLE TO BE ROTATED FREELY .1250 INCH TO EITHER SIDE.						1	L	7	2 	3O				A20SO 					 
1995052600063	19950526	00063	EA 	1995	5	26	95ZZZX2427 	2	19950424	G	8530	78743	INTAKE PIPE 			MOONEY	M20 	M20F 	5870214	SW 	LYC 	O360 	IO360A1A 	41514	EA 					NR 3 CYLINDER	CRACKED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	7112V	1680 	678 			220047	L1262451A			REPLACED PARTS RECEIVED BACK FROM OVERHAUL AGENCY FOLLOWING PROP STRIKE DISASSEMBLY INSPECTIONS INCLUDED A PN SL-10204J 	PISTON AND SUBJECT NR 3 CYL. INTAKE PIPE. PISTON EXHIBITED EARLY STAGES OF TYPICAL DETONATION DAMAGE ON THE HEAD, ADJAC	ENT TO ITS O.D. AT THE 12 O'CLOCK POSITION AS INSTALLED. TPT 678 HRS. CAUSE APPARENTLY DUE TO EXCESSIVELY LEAN MIXTURE	S RESULTING FROM AMBIENT AIR ENTERING SUBJECT CRACKED INTAKE PIPE ADJACENT TO ITS CYLINDER-MATING END.			1	L	7	1 	3O	3	O		2A3 	1E10				 
1995052600064	19950526	00064	EA 	1995	5	26	95ZZZX2428 	2	19950424	G	8550	75167	OIL LINE 			MOONEY	M20 	M20F 	5870214	SW 	LYC 	O360 	IO360A1A 	41514	EA 					PROP GOV OIL	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	7112V	678 				220047	L12624511			INSPECTION FOLLOWING ENGINE REMOVAL REVEALED EXTREME CHAFING/WEAR DAMAGE TO PROP GOVERNOR EXTERNAL OIL LINE AT GOV. END 	APPROX 5 INCHES AWAY FROM B-NUT ATTACH. DAMAGED AREA APPROX .25 INCH BY .50 INCH & WEAR WAS NEARLY THROUGH TUBE WALL TH	ICKNESS. OIL LOSS WAS IMMINENT. AD NOTE 90-04-06 WAS ACCOMPLISHED 678 HRS PREVIOUSLY. ACFT ANNUALED 5 TIMES SINCE. A	D LYC REQUIRED CLAMPING WAS PRESENT AND INTACT. ENGINE MOUNT TUBE DAMAGED REQUIRING WELD REPAIR. EXTREME WEAR PRESENT 	INDICATES PARTS HAD BEEN IN CONSTANT CONTACT AS OPPOSED TO START-UP/SHUTDOWN MOTION.		1	L	7	1 	3O	3	O		2A3 	1E10				 
1995052600065	19950526	00065	EA 	1995	5	26	95ZZZX2429 	2	19950426	G	8530	LW12966	CYLINDER 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					NR 1	HOLED 	E				A	E			UNSCHED LANDING 	ENGINE SHUTDOWN 			E	K		VIBRATION/BUFFET 	FLUID LOSS 		AP	APPROACH 	1			SO	17	684JJ		698 			317952194	L486361A			DURING AN APPROACH TO LANDING, PILOT REPORTED A VIBRATON IN THE LEFT ENGINE AND OIL LEAKING FROM COWLING. A PRECAUTIONA	RY SHUT DOWN MADE AND PILOT MADE AN UNEVENTFUL LANDING. INSPECTION REVEALED A HOLE IN NR 1 CYLINDER UNDER THE INTAKE PU	SH ROD HOUSING. THE HOLE ALLOWED EXHAUST GASES TO BURN A HOLE IN THE PUSH ROD HOUSING ALLOWING OIL LEAKAGE, AND THE PUS	H ROD TO BREAK. SUBMITTER SUGGESTED PROBLEM MAY HAVE BEEN DUE TO A POOR WELD.			1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995052600066	19950526	00066	EA 	1995	5	26	95ZZZX2430 	2	19950320	G	7414	10682016	ROTOR GEAR 	BENDIX 	K6LN3000 	PIPER 	PA32 	PA32R300 	7103213	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					MAG	TEETH BROKEN 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	13	3844M	300 			E14907GR	32R7885016	1762248A			THREE TEETH SHEARED OFF ON RIGHT MAG SIDE. TWO TEETH SHEARED OFF ON LEFT MAG SIDE. RIGHT MAG WAS NOT ROTATING. ENGINE	 RUNNING ON LT MAG ONLY. ONE MORE TOOTH SHEARING ON LT MAG WOULD HAVE RESULTED IN ENGINE SHUT DOWN. LOOKS AS IF TEETH 	FROM RT GEAR STUCK IN DRIVE GEAR AND POSSIBLY CAUSED TEETH TO SHEAR ON LT MAG ALSO. (POOR MAG DESIGN.)				1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995052600067	19950526	00067	EA 	1995	5	26	95ZZZX2431 	2	19950322	G	8530	LW72198	PISTON 			BEECH 	23 	C23 	1151242	CE 	LYC 	O360 	O360A4K 	41514	EA 					OIL RING	DAMAGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	9226S		2904 			M1723	L2042136A			PISTON PIN CAP DEVELOPED WEAR AND WORKED OUT LARGE HOLE INSIDE OF PISTON CAUSING FAILURE OF OIL RING AND LOSS OF COMPRES	SION. CAP HAD WORN DOWN TO .25 INCH THICKNESS AND WORKED OUT HOLE REACHING PISTON OIL RING GROOVE.					1	L	7	1 	3O	3	O		A1CE 	E286				 
1995052600068	19950526	00068	EA 	1995	5	26	95ZZZX2432 	2	19950322	G	8530	LW75089	PIN PLUG 			BEECH 	23 	C23 	1151242	CE 	LYC 	O360 	O360A4K 	41514	EA 					PISTON	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	9226S		2904 			M1723	L2042136A			PISTON PIN CAP DEVELOPED WEAR AND WORKED OUT LARGE HOLE INSIDE OF PISTON CAUSING FAILURE OF OIL RING AND LOSS OF COMPRES	SION. CAP HAD WORN DOWN TO .25 INCH THICKNESS AND WORKED OUT HOLE REACHING PISTON OIL RING GROOVE.					1	L	7	1 	3O	3	O		A1CE 	E286				 
1995052600069	19950526	00069	SO 	1995	5	26	95ZZZX2433 	1	19950508	G	5740	NAS464P6LA6	BOLT 			PIPER 	PA28 	PA28R201 	7102816	SO 										LT WING ATTACH	WORN 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	173ND	5987 				2837025				LEFT WING AFT ATTACH POINT BOLT FOUND LOOSE WHEN MECHANIC WAS CHECKING TORQUE. AN96051B AND 516L WASHERS WERE WORN AND 	LOOPED. BOLT SHOWED ROTATIONAL O-RING BOLT WOULD NOT TORQUE DUE TO BOTTOM ON THREADS. INSPECTED ATTACH HOLE, OKAY. RE	PLACED ALL HARDWARE WITH NEW PARTS.				1	L	7	1 	3O				2A13 					 
1995052600070	19950526	00070	SO 	1995	5	26	95ZZZX2434 	1	19950503	G	7922	75944	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	NUT MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	4079H				12804	318152074				UPON COMPLIANCE OF LYCOMING SB 518B, FOUND NUT MISSING. THE NUT WAS LOCATED INSIDE OIL COOLER WITH THE WRENCH FLATS OF 	THE NUT COMPLETELY ROUNDED OFF. OUT OF 14 ACFT, THIS SHOP HAS INSPECTED, HAVE HAD TO REPLACE 12 BYPASS VALVES. HIGHLY 	RECOMMEND THIS SB BECOME AN AD. THERE WAS BARELY ANY INDICATION ON THE CRIMPED PART OF THE NUT.				1	L	7	2 	3O				A20SO 					 
1995052600071	19950526	00071	SO 	1995	5	26	95ZZZX2435 	2	19950130	G	8530	SA631475	PISTON 			BEECH 	35 	V35 	1151538	CE 	CONT 	O520 	IO520BA 	17032	SO 					NR 2 CYLINDER	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	07	9516Q	382 				D8064	569329			PISTON SKIRT FAILED AT LOWER RING LAND ON THRUST SIDE. DEBRIS EXTENSIVELY DAMAGED CRANKCASE, CRANKSHAFT, CAMSHAFT, RODS	, ADJACENT PISTONS AND CYLINDERS. ALSO, THE ENTIRE OIL SYSTEM WAS CONTAMINATED.					1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995052600072	19950526	00072	EA 	1995	5	26	95ZZZX2436 	2	19950430	G	8520	SL72877MJP	TAPPET 			MOONEY	M20 	M20J 	5870219	SW 	LYC 	O360 	IO360A3B6 	41514	EA 					CAM	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CE	05	4145H					240648	L2305951A			TAPPET BODIES BROKE AT THE TOP WHERE THEY RIDE ON THE CAM. PARTS OF TAPPETS THEN LODGED BETWEEN THE CAM AND CASE CAUSIN	G A CRACK IN THE CASE, ALSO, DAMAGE TO PISTONS, RODS, CRANK, AND CAM, RESULTING ENGINE FAILURE.					1	L	7	1 	3O	3	O		2A3 	1E10				 
1995052600073	19950526	00073	CE 	1995	5	26	95ZZZX2437 	3	19950424	G	6114	27820425	HUB 													BEECH	278	278* 	CE 	NR 1 SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15										UPON INSPECTION, HUB WAS FOUND CRACKED OUTSIDE BLADE SOCKET NR 1. HUB HAS BEEN SCRAPPED.																5	C	P882	 
1995052600074	19950526	00074	CE 	1995	5	26	95ZZZX2438 	1	19950501	G	5510		STABILIZER 			BEECH 	23 	C23 	1151242	CE 										TAILCONE	BIRD NEST 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	6715D					M2253				DURING PRE-FLIGHT, PILOT NOTICED TWIG STICKING OUT OF TAILCONE. MAINTENANCE PERSONNEL REMOVED TAILCONE AND FOUND ENTIRE	 HORIZONTAL STABILIZER FILLED WITH BIRD'S NEST. STABILIZER WAS PART OF STABILATOR ASSY AND OUT OF BALANCE. INSPECTED 2	 OTHER LIKE AIRCRAFT PARKED ON SAME RAMP FOUND IN SAME CONDITION. SUGGEST COVERING LIGHTENING HOLES WITH SCREENS.				1	L	7	1 	3O				A1CE 					 
1995052600075	19950526	00075	CE 	1995	5	26	95ZZZX2439 	1	19950427	G	2721	123466510	CONTROL HORN 			CESSNA	210 	T210L 	2073449	CE 										RT ELEV TAB	CRACKED 	D				O				OTHER 				F			FLT CONT AFFECTED 			CR	CRUISE 	1			WP	17	59046					21060047				ELEVATOR TRIM TAB CONTROL HORN FAILED CAUSING ELEVATOR TO FLUTTER. FLUTTER WAS STOPPED BY REDUCING POWER, LOWERING LAND	ING GEAR AND FLAPS. APPEARS CONTROL HORN HAD BEEN CRACKED PREVIOUSLY THROUGH TWO-THIRDS OF ITS LENGTH. TRIM TAB HAD A 	CONSIDERABLE AMOUNT OF CORROSION. BETTER INSPECTION OF TRIM TAB AND CONTROL HORN.				1	H	7	1 	3O				3A21 					 
1995052600076	19950526	00076	SO 	1995	5	26	95ZZZX2440 	1	19950509	G	5743	6704012	FITTING 			PIPER 	PA34 	PA34200 	7103405	SO 										L MLG FWD ATTACH	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	55777	3573 				347350244				DURING GEAR RETRACTION, FOUND LEFT MAIN GEAR FWD AND AFT ATTACH BRACKETS LOOSE IN WING. PIPER SB 956 HAD BEEN PREVIOUSL	Y COMPLIED WITH AND PART STILL CAME LOOSE. THE LOOSENESS OF THE BOLTS CAUSE ELONGATED HOLES RESULTING IN A COMPLICATED 	AND EXPENSIVE REPAIR. SUBMITTER SUGGESTS PIPER RECONDITION DESIGN OF THESE BRACKETS TO ADD MORE BOLTS.				1	L	7	2 	3O				A7SO 					 
1995052600077	19950526	00077	SO 	1995	5	26	95ZZZX2441 	1	19950509	G	5743	6704204	FITTING 			PIPER 	PA34 	PA34200 	7103405	SO 										L MLG AFT ATTACH	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	55777	3573 				347350244				DURING GEAR RETRACTION, FOUND LEFT MAIN GEAR FWD AND AFT ATTACH BRACKETS LOOSE IN WING. PIPER SB 956 HAD BEEN PREVIOUSL	Y COMPLIED WITH AND PART STILL CAME LOOSE. THE LOOSENESS OF THE BOLTS CAUSE ELONGATED HOLES RESULTING IN A COMPLICATED 	AND EXPENSIVE REPAIR. SUBMITTER SUGGESTS PIPER RECONDITION DESIGN OF THESE BRACKETS TO ADD MORE BOLTS.				1	L	7	2 	3O				A7SO 					 
1995052600078	19950526	00078	CE 	1995	5	26	95ZZZX2442 	1	19950509	G	5711	05230181	SPAR 			CESSNA	172 	172M 	2072418	CE 										LT WING	HOLES ELONGATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	80487	4215 				17266614				FOUND UPPER LIFT STRUT ATTACH BOLT HOLE ELONGATED IN SPAR. FORK AND SPEAR HOLES WERE OKAY. CONTACTED CESSNA TECH REP F	OR THEIR ADVICE ON A REPAIR. WAS TOLD BY CESSNA TECH REP AND ENGINEER TO GREASE BOLT AND LUBE PARTS WELL ACF-50, AND RE	SASSEMBLE. CONTACTED A LOCAL DER WHO DREW UP A REPAIR TO REAM BOLT HOLE TO .0156 INCH OVERSIZE AND USE CLOSE TOLERANCE 	BOLT. ALL PLAY WAS REMOVED AND STRUT NO LONGER 'SQUEAKED.'.			1	H	7	1 	3O			NT	3A12 					 
1995052600079	19950526	00079	CE 	1995	5	26	95ZZZX2443 	1	19950510	G	5210		DOOR 			CESSNA	172 	172P 	2072436	CE 										CABIN LT-RT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	345AR	1100 				17274364				BOTH CABIN DOORS CORRODED BEYOND REPAIR (CESSNA FACTORY INSULATION). COLLECTED MOISTURE AND CORRODED INSIDE OF DOOR AT T	HE BOTTOM FORWARD SIDE. NO WAY TO INSPECT AREA WITHOUT DRILLING A BIGGER HOLE. NO FACTORY DRAIN HOLES WERE IN THIS ARE	A. ACFT WAS ALWAYS HANGARED. NEVER FLEW IN THE RAIN. MOISTURE MAY HAVE BEEN CAUSE BY WASHING ACFT. NO OTHER SITES OF	 CORROSION ON THIS ACFT. SUBMITTER RECOMMENDS REMOVING ALL FACTORY INSULATION FROM ALL AREAS OF ACFT.			1	H	7	1 	3O			NT	3A12 					 
1995052600080	19950526	00080	CE 	1995	5	26	95ZZZX2444 	1	19950501	G	5520	505244203	HINGE 			BEECH 	90 	B90 	1152912	CE 										LT ELEV	CRACKED 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	984AA	9764 				LJ429				DURING INSPECTION, DISCOVERED THE LT ELEV HINGE LOWER LT (OUTBOARD) ATTACH POINT OF THE CASTING HAD CRACKED THROUGH THE 	BOLT HOLE. THIS ALLOWED THE BROKEN PIECE TO FALL OUT WHEN THE AN4 BOLT WAS REMOVED. CAUSE OF THIS PROBLEM IS UNKNOWN A	S NO OTHER DEFECTS APPEAR THAT WOULD CONTRIBUTE TO THIS DEFECT. RECOMMEND CLOSE INSPECTION WITH 10X MAGNIFYING GLASS AN	D USE OF FLUORESCENT PENETRANT TO VERIFY ANY SUSPECTED CRACK. THIS TO BE PERFORMED AT EACH 150 HR/12 MO INSPECTION.			1	L	7	2 	3T				3A20 					 
1995052600081	19950526	00081	WP 	1995	5	26	95ZZZX2445 	2	19950404	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURBINE	CRACKED 	H				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			GL	25		5283 			1233152013		P70094C			DURING INSPECTION FOR LOW POWER, FOUND PART CRACKED 12 PLACES UP TO APPROXIMATELY .5 INCH. SB 72-0840 AUTHORIZES INSTAL	LATION OF THIS PART TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST FIRST STAGE ROTOR. THIS INCREASED TENSION RESULTS I	N CRACKING AT THE SEAL PLATE EDGE DIAMETER. CRACKING RESULTS IN AIR LEAK AND SUBSEQUENT POWER LOSS. SUGGEST ALLIED SIG	NAL ENGINEERING REVIEW PART/INSTALLATION PROBLEM.								4	T			E4WE				 
1995052600082	19950526	00082	WP 	1995	5	26	95ZZZX2446 	2	19950509	G	7250	31038391	SEAL 		31070852 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURBINE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		8568 			9233151435		P70017			DURING INSPECTION FOR COMPRESSOR DAMAGE, FOUND PART CRACKED 11 PLACES. SB 72-0840 AUTHORIZES INSTALLATION OF PN 3107085	-2 TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST FIRST ROTOR ASSY. THIS PART WAS MODIFIED TO PN 3107085-2 BY INCORPOR	ATING A SHIM BETWEEN THE AIR SEAL AND CURVIC COUPLING (NOTE: LIFE LIMITED PART LOG IDENTIFICATION WAS NOT UPDATED UPON 	MODIFICATION). INCREASED TENSION ON SEAL FLANGE RESULTS IN CRACKING AT FLANGE EDGE. SUGGEST ALLIED SIGNAL ENGINEERING 	REVIEW CAUSE/RESULT OF THIS DISCREPANCY. TIME SINCE MOD: 2130 HOURS, 2132 CYCLES. NOTE: THIS IS THE FIFTH ASSEMBLY F	OUND CRACKED. CYCLES: 8915.						4	T			E4WE				 
1995052600083	19950526	00083	WP 	1995	5	26	95ZZZX2447 	2	19950508	G	7250	8683793	STATOR 		8940423 						GARRTT	TPE331	TPE3313U 	01514	WP 					3RD STAGE	FAILURE 	B			DSCR	O				OTHER 				T			ENGINE CASE PENETRATION 			CR	CRUISE 	1			GL	25			1250 		1013459365		P03209			ENGINE EXPERIENCED UNCONTAINED TURBINE SECTION FAILURE IN-FLIGHT. LOCATION OF PENETRATION THROUGH PENUM AND CONDITION O	F REMAINING COMPONENTS INDICATE FAILURE OF THE 3RD STAGE ROTOR RESULTING FROM CONTACT OF ROTOR HUB WITH 3 INCH STATOR IN	NER SHEET METAL SEAL SUPPORT. THIRD STATOR WAS DUE REPLACEMENT IN 8 CYCLES AS REQUIRED BY AD NOTE 92-26-08. CSO: 592									4	T			E4WE				 
1995052600084	19950526	00084	CE 	1995	5	26	95ZZZX2448 	1	19950503	G	5510	45AS6601015	LEADING EDGE 			BEECH 	MU300 	400BEECH 		CE 										LT STAB OTBD	BURNED 	D				K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			CE	03	8239E	784 				RK46				ON INITIAL INSPECTION, FOUND HORIZONTAL STABILIZER DE-ICE TEST WOULD NOT CYCLE FULL AMOUNT OF CYCLES AND WOULD SKIP. UP	ON FURTHER INVESTIGATION, FOUND LEFT HORIZONTAL STABILIZER BURNED ON UPPER OUTBOARD LEADING EDGE. REPLACED LEADING EDGE	 WITH NEW. OPERATION CHECKED GOOD.				2	H	7	2 	4F			RT	A16SW 					 
1995052600085	19950526	00085	CE 	1995	5	26	95ZZZX2449 	1	19950329	G	2161	9796864	VALVE 			LEAR 	55 	55LEAR 	5170702	CE 										TEMP CONTROL	FAILED 	B			CW1R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			EA	25	725K	6384 				93				TEMPERATURE CONTROL VALVE DIAPHRAGM RUPTURED CAUSING DAMAGE TO DIAPHRAGM BODY AND SEVERING ACTUATING LINKAGE. AIRCRAFT 	WAS PREPARING FOR DEPARTURE WITH NO CONTROL OF COCKPIT HEAT. HEAT WAS FULL HOT. VALVE WAS REPLACED AND A CONTROL PRESS	URE CHECK WAS C/W. INDICATIONS AND OPERATION WERE NORMAL.				2	L	7	2 	4F				A10CE 					 
1995052600086	19950526	00086	CE 	1995	5	26	95ZZZX2450 	1	19950316	G	5270	JV5	SWITCH ACTUATOR 			BEECH 	B300 	B300 	1159232	CE 										CABIN DOOR WARN	BROKEN 	B			KI2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	65CR					FL60				THE SWITCH ACTUATOR ON THE CABIN DOOR LIGHT WAS BENT BACK AND BROKEN OFF. THE CONDTION WAS DUPLICATED BY PUSHING DOOR B	UTTON AND MOVING HANDLE FURTHER INTO THE CLOSED POSITION. FOLLOWER FALLS BEHIND LOCK TAB. HANDLE IS THEN ROTATED OPEN 	FOLLOWER IS BENT. THUS, A DOOR UNSAFE LIGHT. BRACKETS IN THIS AREA ARE LIGHT WEIGHT AND MOVE AROUND.				2	L	7	2 	4T			RT	A24CE 					 
1995052600087	19950526	00087	NM 	1995	5	26	95ZZZX2451 	1	19950331	G	2761	65446461	BRACKET 			BOEING	737 	737204 	1384458	NM 										SPOILER ACTUATOR	CORRODED 	B	S	A	B5SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23						19709				UPON DISSASSEMBLY AND PAINT COAT REMOVAL, PITTING CORROSION .080 DEEP DISCOVERED IN UPPER HOLE LT BOLT (AIRCRAFT LOCATIO	N). THIS BOLT IS THE LONGEST BOLT IN THE ASSY. MOUNT ASSY AND ACTUATOR ARE MATCHED SET. SUBMITTER SUGGESTS INCLUDING 	THIS ASSY FOR CORROSION INSPECTION DURING ITS PARTICULAR PHASE INSPECTION.				2	L	7	2 	4F				A16WE 					 
1995052600088	19950526	00088	NE 	1995	5	26	95ZZZX2452 	1	19950504	G	6320	S613520614007	CAMSHAFT 			SKRSKY	S61 	S61A 	814210C	NE 										M/R GEARBOX	CRACKED 	B	S	A	JYER	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			NM	09	318Y	266 				61094				ON SHUT-DOWN, PILOTS FELT AN UNUSUAL VIBRATION AND GROWL. NR 1 CAMSHAFT FOUND CRACKED ABOUT 340 DEGREES AROUND CAM THRO	UGH OIL HOLES. SIKORSKY AIRCRAFT HAS BEEN NOTIFIED AND CAM SENT FOR FRACTURE ANALYSIS. REF: OPERATOR CONTROL NR JYER9	50504.				2	G	7	2 	4U				H2EA 					 
1995052600089	19950526	00089	SW 	1995	5	26	95ZZZX2453 	1	19950502	G	6310	222044685101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	DEFECTIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	510W	40 			A468	47133				INSPECTION FOUND 2 SHAFTS REQUIRED REPLACEMENT PER ASB 222-95-74. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600090	19950526	00090	SW 	1995	5	26	95ZZZX2454 	1	19950502	G	6310	222044685101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	DEFECTIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	510W	40 			A606	47133				INSPECTION FOUND 2 SHAFTS REQUIRED REPLACEMENT PER ASB 222-95-74. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600091	19950526	00091	SW 	1995	5	26	95ZZZX2455 	1	19950502	G	6220	222310117103	SPRING 			BELL 	222 	222U 	1182140	SW 										M/R FLAPPING	DEFECTIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	111DS	1500 			BW821A	47554				INSPECTION FOUND SPRING (2 EACH) DEFECTIVE. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600092	19950526	00092	SW 	1995	5	26	95ZZZX2456 	1	19950502	G	6220	222310117103	SPRING 			BELL 	222 	222U 	1182140	SW 										M/R FLAPPING	DEFECTIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	111DS	1500 			BW686A	47554				INSPECTION FOUND SPRING (2 EACH) DEFECTIVE. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600093	19950526	00093	SW 	1995	5	26	95ZZZX2457 	1	19950502	G	6330	222031605105	FLEXTURE 			BELL 	222 	222B 	1182124	SW 										M/R XMSN MOUNT	DEBONDED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	153H	1089 				47138				INSPECTION FOUND FLEXTURE DEBONDED. W.P.H.S. REPLACED WITH NEW FLEXTURE.						1	G	7	2 	3U				H9SW 					 
1995052600094	19950526	00094	SW 	1995	5	26	95ZZZX2458 	1	19950502	G	6510	206040369001	SHAFT 			BELL 	206 	206L4 	1182110	SW 										T/R	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	7052V		302 		BFTS340	52052				INSPECTION FOUND T/R DRIVE SHAFTS WITH CORROSION. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW 					 
1995052600095	19950526	00095	SW 	1995	5	26	95ZZZX2459 	1	19950502	G	6510	206040365125	SHAFT 			BELL 	206 	206L4 	1182110	SW 										T/R	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	7052V		302 		BT292	52052				INSPECTION FOUND T/R DRIVE SHAFTS WITH CORROSION. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW 					 
1995052600096	19950526	00096	SW 	1995	5	26	95ZZZX2460 	1	19950502	G	6510	206040365125	SHAFT 			BELL 	206 	206L4 	1182110	SW 										T/R	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	7052V		302 		BT291	52052				INSPECTION FOUND T/R DRIVE SHAFTS WITH CORROSION. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW 					 
1995052600097	19950526	00097	SW 	1995	5	26	95ZZZX2461 	1	19950502	G	6510	206040365125	SHAFT 			BELL 	206 	206L4 	1182110	SW 										T/R	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	7052V		302 		BT290	52052				INSPECTION FOUND T/R DRIVE SHAFTS WITH CORROSION. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW 					 
1995052600098	19950526	00098	SW 	1995	5	26	95ZZZX2462 	1	19950502	G	6510	206040365125	SHAFT 			BELL 	206 	206L4 	1182110	SW 										T/R	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	7052V		302 		BT289	52052				INSPECTION FOUND T/R DRIVE SHAFTS WITH CORROSION. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW 					 
1995052600099	19950526	00099	SW 	1995	5	26	95ZZZX2463 	1	19950502	G	6510	206040365125	SHAFT 			BELL 	206 	206L4 	1182110	SW 										T/R	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	7052V		302 		BT288	52052				INSPECTION FOUND T/R DRIVE SHAFTS WITH CORROSION. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW 					 
1995052600100	19950526	00100	SW 	1995	5	26	95ZZZX2464 	1	19950502	G	6310	222044645103	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	230NX	2439 			A2000028	47012				INSPECTION FOUND 2 EACH M/R SHAFTS CORRODED PER ASB222-95-74 AND ASB222-94-69. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600101	19950526	00101	SW 	1995	5	26	95ZZZX2465 	1	19950502	G	6310	222044685101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	230NX	2439 			A377	47012				INSPECTION FOUND 2 EACH M/R SHAFTS CORRODED PER ASB222-95-74 AND ASB222-94-69. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600102	19950526	00102	SW 	1995	5	26	95ZZZX2466 	1	19950502	G	6310	222044685101	SHAFT 			BELL 	222 	222U 	1182140	SW 										M/R	REQ REPLACEMENT 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	111DS	1500 			A159	47554				INSPECTION FOUND 2 EACH SHAFTS REQUIRED REPLACEMENT PER ASB 222-95-74. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600103	19950526	00103	SW 	1995	5	26	95ZZZX2467 	1	19950502	G	6310		SHAFT 			BELL 	222 	222U 	1182140	SW 										M/R	REQ REPLACEMENT 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	111DS	1500 			A173	47554				INSPECTION FOUND 2 EACH SHAFTS REQUIRED REPLACEMENT PER ASB 222-95-74. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600222	19950526	00222	WP 	1995	5	26	95ZZZX2470 	1	19950509	G	6320	369D25144	BEARING 			HUGHES	369 	369D 	4470706	WP 										M/R TRANSMISSION	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R	4926 	2026 			1159D				DURING REPAIR OF M/R TRANSMISSION AFTER THE RING GEAR HAD FAILED, THE TRANSMISSION OUTPUT SHAFT DUPLEX BEARING ASSEMBLY 	WAS FOUND WITH A 'CLICK' IN IT AS IT ROTATED. BEARING WAS REMOVED AND SENT IN FOR OVERHAUL.					1	G	7	1 	3U				H3WE 					 
1995052600223	19950526	00223	SW 	1995	5	26	95ZZZX2471 	1	19950508	G	5343	206030104023	FITTING 			BELL 	206 	206L4 	1182110	SW 										FWD CROSS-TUBE	CRACKED 	B	S	A	ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	173AL	1708 	5 			52066				DURING SERVICE CHECK, NOTED FORWARD CROSS-TUBE FITTING CRACKED. FITTING FOUND CRACKED IN THE SAME AREA AS REPORTED ON M	DR SUBMITTED ON 2-7-94. THE FITTING WAS MANUFACURED IN OCTOBER, 1992, WHICH IS DIFFERENT FROM THE PREVIOUSLY REPORTED C	RACKED FITTINGS.				1	G	7	1 	3U			NC	H2SW 					 
1995052600224	19950526	00224	GL 	1995	5	26	95ZZZX2472 	2	19950307	G	7321	25400012V	FUEL CONTROL 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					ENGINE	DEFECTIVE 	B			CZ4R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	01	133AL				323311	51133				PART WAS ZERO TSO, COULD NOT ADJUST START ADJUSTMENT FOR A COOL ENOUGH START EVEN AT LOWEST SETTINGS.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995052600226	19950526	00226	SW 	1995	5	26	95ZZZX2474 	1	19950307	G	2435	200SG11Q	STARTER GEN 			BELL 	206 	206L3 	1182108	SW 										ENGINE	DEFECTIVE 	B		A	CZ4R	O				OTHER 				R			PARTIAL RPM/PWR LOSS 			HO	HOVERING 	1			AL	01	133AL	2031 	841 		1021	51133				DURING A POWER RECOVERY AUTOROTATION WHEN THE THROTTLE WAS ROLLED BACK ON, THE ENGINE WOULD NOT RETURN TO 100 PERCENT N2	. IT WOULD ONLY RETURN TO 97 PERCENT N2. ALL THE ENGINE CONTROLS WERE REPLACED. THE HELICOPTER MANUFACTURER WAS CONSU	LTED AND THEY RECOMMENDED REPLACING THE STARTER GENERATOR. IT WAS EXPLAINED THE STARTER/GENERATOR VIBRATIONS HAVE BEEN 	FOUND IN A COUPLE OF CASES TO INTERFERE WITH THE OPERATION OF THE GOVERNOR. THE COMPONENT WAS CHANGED AND THE PROBLEM C	URED.		1	G	7	1 	3U				H2SW 					 
1995052600236	19950526	00236	SW 	1995	5	26	95ZZZX2484 	1	19950504	G	6310	222044365101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	REQ REPLACEMENT 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	40EA	166 			A394	47061				INSPECTION FOUND 2 EACH SHAFTS REQUIRED REPLACEMENT PER ASB 222-95-94. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600237	19950526	00237	SW 	1995	5	26	95ZZZX2485 	1	19950504	G	6310	222044365101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	REQ REPLACEMENT 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	40EA	166 			A400	47061				INSPECTION FOUND 2 EACH SHAFTS REQUIRED REPLACEMENT PER ASB 222-95-94. W.P.H.S. REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H9SW 					 
1995052600238	19950526	00238	SW 	1995	5	26	95ZZZX2486 	1	19950502	G	6310	222044685101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	REQ REPLACEMENT 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	37VA	299 			A401	47054				INSPECTION FOUND 2 EACH SHAFTS REQUIRED REPLACEMENT PER ASB 222-95-74. W.P.H.S. REPLACED WITH NEW SHAFTS.						1	G	7	2 	3U				H9SW 					 
1995052600239	19950526	00239	SW 	1995	5	26	95ZZZX2487 	1	19950502	G	6310	222044685101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	REQ REPLACEMENT 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	37VA	299 			A396	47054				INSPECTION FOUND 2 EACH SHAFTS REQUIRED REPLACEMENT PER ASB 222-95-74. W.P.H.S. REPLACED WITH NEW SHAFTS.						1	G	7	2 	3U				H9SW 					 
1995060200098	19950602	00098	NE 	1995	6	2	95ZZZX2523 	2	19950417	G	7323	430128901	GOVERNOR 			SNIAS 	350 	AS350D 	8680803	EU 	LYC 	LTS101	LTS101600A3 	41560	NE 					ENGINE PT	DEFECTIVE 	H				A				UNSCHED LANDING 				J	R		WARNING INDICATION 	PARTIAL RPM/PWR LOSS 		HO	HOVERING 	1			WP	13	138EH		513 			1403	LE43450CE			DURING FLIGHT, EXPERIENCED LOW SIDE GOVERNOR FAILURE (LOW POWER). THE PILOT JUST LIFTED OFF PAD NR 1. ACFT WAS ABOUT 4	 FEET OFF THE DECK, THE PILOT MANAGED TO SET IT BACK DOWN WITHOUT ANY INCIDENT OR DAMAGE TO THE AIRCRAFT. PILOT TOOK AN	OTHER SHIP AND THE SAME PASSENGERS AND COMPLETED THE TOUR. THE MECHANIC REMOVED P.T. GOVERNOR. TSO 513.0, AND INSTALLE	D SERVICEABLE GOVERNOR, ZERO TSO, AND C/W OPERATIONAL AND A MAXIMUM TOPPING CHECK FLIGHT AND PASSENGER CHECK FLIGHT.			1	G	7	1 	3U	3	U		H9EU 	E5NE				 
1995060200099	19950602	00099	NE 	1995	6	2	95ZZZX2524 	2	19950421	G	7321		FUEL CONTROL 			SNIAS 	350 	AS350D 	8680803	EU 	LYC 	LTS101	LTS101600A3 	41560	NE 					BELLOWS	AIR LEAKS 	D				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			WP	13	3608R		1312 			1265	LE435560E			DURING FINAL APPROACH, M/R RPM DROOPS. PILOT MADE SOFT LANDING ON THE RUNWAY. INSPECTED AND PNEUMATIC LEAK CHECK AND F	OUND AIR LEAKS FROM GOVERNOR BELLOWS OF THE FUEL CONTROL UNIT. REMOVED AND REPLACED WITH SERVICEABLE FCU. PERFORMED RU	N-UP LEAK CHECK AND NG TOPPING CHECK. ACFT RETURNED TO SERVICE.				1	G	7	1 	3U	3	U		H9EU 	E5NE				 
1995060200100	19950602	00100	EU 	1995	6	2	95ZZZX2525 	1	19950221	G	7714	0177555150	TACHOMETER BOX 			SNIAS 	350 	AS350B 	8680801	EU 										ENGINE RPM	SENSOR FAILED 	D				A				UNSCHED LANDING 				E	O		VIBRATION/BUFFET 	OTHER 		CR	CRUISE 	1			WP	13	6077H	66 			1917B	2693				DURING FLIGHT, ROTORCRAFT DEVELOPED FLUTTER SOUND AND HIGHER THAN NORMAL TOT. LANDING MADE AND MECHANIC FOUND TACHOMETE	R BOX TO BE DEFECTIVE.					1	G	7	1 	3U				H9EU 					 
1995060200166	19950602	00166	NE 	1995	6	2	95ZZZX2532 	2	19950410	G	7261	0292501960	SCAVENGE TUBE 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					MODULE NR 3	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	01	6088B	841 				2691	9318			A SLIGHT OIL SEEP WAS NOTED DURING A DAILY INSPECTION AND WAS CLOSELY MONITORED. THE SEALS AT BOTH ENDS OF THE TUBE WER	E REPLACED, BUT THE SEEP PERSISTED. REMOVED TUBE AND ACCOMPLISHED A DYE PENETRANT INSPECTION. A SMALL CRACK WAS FOUND 	AT THE LOWER END OF THE THREADS.				1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995060200167	19950602	00167	SW 	1995	6	2	95ZZZX2533 	1	19950502	G	6310	222044685101	SHAFT 			BELL 	222 	222B 	1182124	SW 										ENG/XMSN	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	153H	1089 			A2000029	47138				INSPECTION FOUND SHAFTS CORRODED. W.P.H.S. REPLACED WITH NEW SHAFTS.						1	G	7	2 	3U				H9SW 					 
1995060200168	19950602	00168	SW 	1995	6	2	95ZZZX2534 	1	19950502	G	6310	222044685101	SHAFT 			BELL 	222 	222B 	1182124	SW 										ENG/XMSN	CORRODED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	153H	1089 			A00000005	47138				INSPECTION FOUND SHAFTS CORRODED. W.P.H.S. REPLACED WITH NEW SHAFTS.						1	G	7	2 	3U				H9SW 					 
1995060200169	19950602	00169	WP 	1995	6	2	95ZZZX2535 	1	19950401	G	2822		WIRE 			HUGHES	369 	369E 	4470707	WP 										START PUMP	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	5144Q					0007				DURING ANNUAL INSPECTION AND SB COMPLIANCE, FOUND START PUMP WIRES (HOT & GROUND) PULLED FREE FROM THE CANNON PLUG INSID	E THE FUEL TANK ALLOWING THEM TO FLOAT IN THE FUEL CELL. A HOT LEAD SEEKING GROUND COULD HAVE HAD CATASTROPHIC CONSEQUE	NCES. SUBMITTER BELIEVES THE CAUSE TO BE MANUFACTURER'S CONCERN ABOUT KEEPING THESE WIRES AWAY FROM THE FUEL QUANTITY F	LOAT BY WRAPPING THEM AROUND THE FEED LINE FROM THE START PUMP. THESE WIRES WERE STRAPPED TOO TIGHT, AND, OVER TIME, PU	LLED FROM THE CANNON PLUG. SUBMITTER RECOMMENDS NOT WRAPPING WIRES TOO TIGHTLY AROUND THE START PUMP FEED LINE.		1	G	7	1 	3U			 	H3WE 					 
1995060200170	19950602	00170	WP 	1995	6	2	95ZZZX2536 	1	19950130	G	6330	269A5527	BUSHING 		269A55933 	HUGHES	269 	269C 	4470504	WP 										H-FRAME	WORN 	B			PN5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	9248F	2830 				390764				INSPECTION FOUND H-FRAME BUSHING WORN. NORMAL WEAR FOR TIME ON PART.						1	G	7	1 	3O				4H12 					 
1995060200171	19950602	00171	SW 	1995	6	2	95ZZZX2537 	1	19950131	G	7100	70009K000V332	HOSE ASSY 			BELL 	206 	206B 	1181511	SW 										ENGINE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	35Q					3073				INSPECTION FOUND MOISTURE IS TRAPPED BETWEEN FIRE SLEEVE AND ALUMINUM FITTINGS AND CAUSES CORROSION OF THE FITTINGS AND 	FIRE SLEEVE.					1	G	7	1 	3U				H2SW 					 
1995060200172	19950602	00172	SW 	1995	6	2	95ZZZX2538 	1	19950131	G	7100	70009H075W204	HOSE ASSY 			BELL 	206 	206B 	1181511	SW 										ENGINE	CORRODED 	B			PN5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	35Q	8338 				3073				INSPECTION FOUND MOISTURE IS TRAPPED BETWEEN FIRE SLEEVE AND ALUMINUM FITTINGS AND CAUSES CORROSION OF THE FITTING AND F	IRE SLEEVE.					1	G	7	1 	3U				H2SW 					 
1995060200173	19950602	00173	SW 	1995	6	2	95ZZZX2539 	1	19950131	G	7100	70009J000A424	HOSE ASSY 			BELL 	206 	206B 	1181511	SW 										ENGINE	CORRODED 	B			PN5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	35Q	8338 				3073				INSPECTION FOUND MOISTURE IS TRAPPED BETWEEN FIRE SLEEVE AND ALUMINUM FITTING AND CAUSES CORROSION OF THE FITTING AND FI	RE SLEEVE.					1	G	7	1 	3U				H2SW 					 
1995060200174	19950602	00174	SW 	1995	6	2	95ZZZX2540 	1	19950410	G	6230	2060400371	BEARING 			BELL 	206 	206B3 	1181506	SW 										LOWER MAST	MAKING METAL 	B			VE3D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	59578					1475				TRANSMISSION DEFECTIVE, CAUSED BY FLAKING OF METAL OF THE ROLLERS. REPLACED ROLLER BEARING WITH NEW AND FLUSHED OIL IN 	TRANS SYSTEM.					1	G	7	1 	3U				H2SW 					 
1995060200175	19950602	00175	EA 	1995	6	2	95ZZZX2541 	2	19950419	G	8530	SL74230P5	VALVE GUIDE 		LW12416 	PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					EXHAUST	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	164ER		995 			2841180				DURING CYLINDER REPAIR, THE EXHAUST GUIDE WAS FOUND CRACKED IN THE LOWER PORTION OF THE GUIDE.						1	L	7	1 	3O	3	O		2A13 	E274				 
1995060200176	19950602	00176	EA 	1995	6	2	95ZZZX2542 	2	19950419	G	8530	SL74230	VALVE GUIDE 		LW12416 	PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					EXHAUST	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	167ER		1189 			2841183				DURING CYLINDER REPAIR, THE EXHAUST GUIDE WAS FOUND CRACKED IN THE LOWER PORTION.						1	L	7	1 	3O	3	O		2A13 	E274				 
1995060200177	19950602	00177	SO 	1995	6	2	95ZZZX2543 	2	19950503	G	8530		RING 								CONT 	O520 	TSIO520UB 	17040	SO 					OIL RING	STUCK 	B			BJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15		638 					527133			ENGINE HAS BEEN RUN WITH MOBIL AV-1 ENGINE OIL. ENGINE STARTED TO BLOW OIL OUT OF BREATHER TUBE. ENGINE DISASSEMBLED A	ND INSPECTED TO DETERMINE CAUSE. FOUND ALL OIL RINGS STUCK IN PISTONS DUE TO LEAD BUILD-UP. FOUND CYLINDER WALLS WORN,	 FOUND EXCESSIVE SLUDGE BUILD-UP IN ENGINE SUMP, CRANKSHAFT AND CRANKCASE. FOUND EXCESSIVE WEAR ON MAIN BEARINGS, FOUND	 THRUST BEARINGS HAD STARTED TO FAIL. CRANKCASE FOUND CRACKED THROUGH FORWARD MAIN BEARING SADDLE. THIS ENGINE WENT IN	TO SERVICE ON 10-18-89. SUBMITTER STATED SEEING SIMILAR DAMAGE IN OTHER ENGINES THAT HAVE BEEN OPERATED ON THIS TYPE OF	 OIL. RECOMMEND DISASSEMBLY AND INSPECTION OF ANY ENGINES RUN ON THIS TYPE OF OIL TO PREVENT SUDDEN ENGINE FAILURE.						3	O			E8CE				 
1995060200179	19950602	00179	CE 	1995	6	2	95ZZZX2545 	1	19950508	G	3397		WIRE 			CESSNA	182 	182K 	2072724	CE 										COMPASS LIGHT	SHORTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	2628Q					18257828				THE WIRING TO THE COMPASS LIGHT WAS SHORTING AT THE METAL TRIM STRIP THAT IS LOCATED WHERE THE HEADLINER AND WINDSHIELD 	MEET CAUSING THE 10-AMP CABIN LIGHT CIRCUIT BREAKER TO TRIP.					1	H	7	1 	3O			NT	3A13 					 
1995060200180	19950602	00180		1995	6	2	95ZZZX2546 	1	19950504	G	7120	LM412335	MOUNT 	LORD 																ENGINE	MISMANUFACTURED 	B			ZCOR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	11										UNIT WAS MANUFACTURED WITH CENTER MOUNT HOLE OFF CENTER. SUBMITTER SUGGESTS CAUSE: MANUFACTURING DEFECT.																			 
1995060200181	19950602	00181	SO 	1995	6	2	95ZZZX2547 	2	19950509	G	8530	643766	VALVE GUIDE 								CONT 	O520 	IO520* 	17032	SO 					INTAKE	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11							807949R			SIX EACH INTAKE VALVE GUIDES OUT OF NEW LIMITS, .0005 INCH (ONE-HALF THOUSANDTHS) AND TAPERED FROM TOP TO BOTTOM.											3	O			E5CE				 
1995060200182	19950602	00182	SO 	1995	6	2	95ZZZX2548 	2	19950509	G	8530	643767	VALVE GUIDE 								CONT 	O520 	IO520* 	17032	SO 					EXHAUST	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11							807949R			SIX EACH EXHAUST VALVE GUIDES OUT OF NEW LIMITS, .0006 (SIX-TENTHS OF ONE THOUSANDTH).											3	O			E5CE				 
1995060200183	19950602	00183	SO 	1995	6	2	95ZZZX2549 	2	19950509	G	8520		CRANKSHAFT 								CONT 	O520 	IO520BA 	17032	SO 					ROD JOURNAL	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11							807040R			THREE OF THE CONNECTING ROD JOURNALS AND TWO OF THE MAIN BEARING JOURNALS ARE OUT OF NEW LIMITS, .0002 (TWO-TENTHS OF ON	E THOUSANDTH).										3	O			E5CE				 
1995060200184	19950602	00184	EU 	1995	6	2	95ZZZX2550 	1	19950310	G	2730		BELLCRANK 			GROB 	G115 	G115C 	1660303	EU 										ELEVATOR	ICE FROZEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	115BA	92 				82009				PILOT REPORTED AIRCRAFT ELEVATOR COULD NOT BE MOVED TO ELEVATOR UP (NOSE UP) POSITION. AIRCRAFT PARKED OUTSIDE IN ABOUT	 15 DEGREES FAHRENHEIT AFTER RAINSTORM. FOUND LOWER AFT FUSELAGE CAVITY WHICH LOWER ELEVATOR PASSES THROUGH, FILLED WIT	H WATER AND FROZEN. THERE IS NO WAY FOR WATER TO BE DRAINED OR DRAIN FROM THIS AREA. EVEN AFTER ICE IS THAWED, IT MAY 	REFREEZE AGAIN IN LOW TEMPERATURES.			1	L	7	1 	3O			NT	A57EU 					 
1995060200185	19950602	00185	GL 	1995	6	2	95ZZZX2551 	3	19950401	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	PROPELLER	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95604					15285935		DG092		PROPELLER TOTAL TIME: 5815.0. A CRACK WAS FOUND IN THE HUB AREA. CRACK RADIATED FROM INSIDE THE HUB THROUGH THE FACE 	OF THE HUB TO THE MOUNTING SURFACE ENDING IN THE BOLT HOLE ADJACENT TO THE NR 1 BLADE. COMPLIANCE WITH MCCAULEY SB 169C	 AND AD 89-26-10 WAS ACCOMPLISHED AT 3229.7 TOTAL WHERE NO DEFECTS WERE FOUND. A FREQUENT DYE PENETRANT INSPECTION WOUL	D BE RECOMMENDED.			1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995060200510	19950602	00510	NM 	1995	6	2	95ZZZX2606 	1	19950501	G	6710		CONTROL TUBE 			ROBSIN	R22 	R22BETA 		NM 										LT CYCLIC	EXTREME WEAR 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	942MH					1942				LEFT CYCLIC CONTROL TUBE HAS LIMITED SPACE BETWEEN TUBE OD AND FUSELAGE. DURING 100-HOUR INSPECTION, FOUND EXTREME WEAR	 IN CONTROL TUBE AT THIS POINT. ACCESS TO THIS PORTION OF TUBE IS ONLY VISIBLE AFTER REMOVAL OF MAST PYLON FAIRING. VI	SIBLE TRACES OF BLACK POWDER FLOWING ALONG THE SLIPSTREAM IN THIS AREA IS EVIDENCE OF CONTACT AND SUBSEQUENT WEAR.				1	G	7	1 	3O				H10WE 					 
1995060200511	19950602	00511	SO 	1995	6	2	95ZZZX2607 	1	19950508	G	3520	833610	PRESSURE UNIT 	SCOTTAVATION		GULSTM	G1159 	G1159C 	3986115	SO 										OXYGEN MASK	DEFECTIVE 	B	L		EC3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05										DURING PASSENGER OXYGEN SYSTEM FUNCTIONAL TEST OF A NEWLY INSTALLED SYSTEM IN A GULFSTREAM GIV, IT WAS FOUND THAT NUMERO	US PASSENGER OXYGEN MASKS HAD REDUCED OR NO FLOW. SYSTEM IS INSTALLED PER STC SA 1473S0 DURING INTERIOR OUTFITTING.					2	L	7	2 	4F			RT	A12EA 					 
1995060200512	19950602	00512	SO 	1995	6	2	95ZZZX2608 	1	19950428	G	3520	833610	PRESSURE UNIT 	SCOTTAVATION		GULSTM	G1159 	GIV 	3980115	SO 										OXYGEN ASK	DEFECTIVE 	B	L		GR4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	405GA					1245				DURING CABIN OXYGEN OPS CHECK, FLOW RATE INDICATED 2.5 TO 2.8 LPM DEPENDING ON BOX TESTED, FORWARD LAV MASKS WOULD NOT F	LOW AT ALL UNTIL 30,200 FEET WAS REVEALED ON TEST BOX.					2	L	7	2 	4F			RT	A12EA 					 
1995060200513	19950602	00513	NE 	1995	6	2	95ZZZX2609 	2	19950407	G	8520	126209	BOLT 			AYRES 	S2 	S2RNORMAL 	7630202	SO 	PWA 	R1340 	R1340AN1 	52016	NE 					CRANKSHAFT	BROKEN 	D	S			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	08	5627X					1827R	11712			ENGINE WAS DISASSEMBLED AFTER ENGINE FAILURE. THE CRANKSHAFT BOLT THAT HOLDS FRONT AND REAR SECTIONS TOGETHER WAS FOUND	 BROKEN AT THE BASE OF THE THREADS, CRANKSHAFT REAR HALF WAS ALSO BROKEN. ABOUT ONE-HALF THE RADIUS OF SPLINES WERE BRO	KEN OUT.				1	L	7	1 	3R	3	R	NC	A3SW 	5E2				 
1995060200514	19950602	00514	SO 	1995	6	2	95ZZZX2610 	1	19950517	G	5741	6676200	SPAR PLATE 			PIPER 	PA28 	PA28R201 	7102816	SO 										LT WING	HOLES WORN 	B	L		DYPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	30024					28R7837311				LEFT WING REAR SPAR BOLT FOUND LOOSE AND CHAFING AT ANNUAL INSPECTION. BOLT HOLE IN THE FUSELAGE MOUNT WORN SPANWISE .0	30 INCH OVERSIZE, WING SPAN ATTACH PLATE IN THE WING WORN SPANWISE .025 INCH OVERSIZE (HOLES ELONGATED).					1	L	7	1 	3O				2A13 					 
1995060200515	19950602	00515	SO 	1995	6	2	95ZZZX2611 	1	19950517	G	5341	6244802	FITTING 			PIPER 	PA28 	PA28R201 	7102816	SO 										FUSELAGE	WORN 	B	L		DYPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	30024					28R7837311				LEFT WING REAR SPAR BOLT FOUND LOOSE AND CHAFING AT ANNUAL INSPECTION. BOLT HOLE IN THE FUSELAGE MOUNT WORN SPANWISE .0	30 INCH OVERSIZE, WING SPAN ATTACH PLATE IN THE WING WORN SPANWISE .025 INCH OVERSIZE (HOLES ELONGATED).					1	L	7	1 	3O				2A13 					 
1995060200516	19950602	00516	SO 	1995	6	2	95ZZZX2612 	1	19950421	G	3230	2251200	STUD 			PIPER 	PA30 	PA30 	7103002	SO 										LT MLG	CRACKED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	8727Y					301880				AT AN ANNUAL INSPECTION AND C/W AD 77-13-21, PART (A), 1,000-HOUR LANDING GEAR CHECK PER PIPER SL 782-B DATED 12-1-77. L	EFT GEAR WAS DISASSEMBLED FOR INSPECTION. OWNER TOLD MECHANIC ABOUT A POSSIBLE AD COMING ABOUT ON PN 22512-00 STUDS. PE	RFORMED A LIQUID N.D.T. ON BOTH MAIN LANDING GEAR STUDS. LEFT ONE SHOWED GOOD, BUT FOUND CRACKED WITH MAGNAFLUX CHECK.				1	L	7	2 	3O				A1EA 					 
1995060200517	19950602	00517	WP 	1995	6	2	95ZZZX2613 	2	19950511	G	7261	8656645	GASKET 			CESSNA	441 	441 	2076020	CE 	GARRTT	TPE331	TPE33110 	01514	WP 					PROP PITCH	LEAKS 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	17	441JD	26 				4410336	P77715			ENGINE OIL LEAK DETERMINED TO BE PROP PITCH CONTROL GASKET. INSTALLED THREE MORE NEW GASKETS WITH SAME OIL LEAK. GASKE	TS HAVE THE WORD 'CANADA' MARKED ON THE EDGE OF THE TACH GENERATOR MOUNT FACE. GASKETS WERE INSTALLED PER GARRETT MM.					1	L	7	2 	3T	4	T	RT	A28CE 	E4WE				 
1995060200518	19950602	00518	SO 	1995	6	2	95ZZZX2614 	1	19950116	G	5751	4019017	SPAR 			PIPER 	PA31 	PA31350 	7103110	SO 										LT AIL HINGE	CRACKED 	B		A	NVMR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	63LA	10558				7552070				LEFT AILERON SPAR WAS FOUND CRACKED WHILE COMPLYING WITH SB 974 - AILERON HINGE INSPECTION AND REPLACEMENT.						1	L	7	2 	3O				A20SO 					 
1995060200519	19950602	00519	CE 	1995	6	2	95ZZZX2615 	1	19950305	G	2750	1695240249	BLOCK 			BEECH 	23 	A24R 	1151252	CE 										FLAP TUBE	RIVETS SHEARED 	D	S			O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			CE	05	101CM	4848 				MC146				THREE CR3212-5-10 CHERRY FASTENERS SHEARED AT THE ATTACHMENT POINT OF THE BLOCK AND TUBE IN THE FLAP SYSTEM. FLAPS WERE	 SELECTED ON LANDING WITH NO RESPONSE. THIS IS A HIGH-TIME TRAINING AIRCRAFT.					1	L	7	1 	3O				A1CE 					 
1995060200520	19950602	00520	CE 	1995	6	2	95ZZZX2616 	1	19950515	G	3233	508101641	ACTUATOR 			BEECH 	65 	65 	1152802	CE 										LT MLG	JAMMED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	499L					LC87				UPON TEAR-DOWN INSPECTION OF LT MLG ACTUATOR, THE FOLLOWING ITEMS WERE NOTED: 1. TOTAL ACTUATOR EXTENSION WAS 8 INCHES	 COMPARED TO TOTAL EXTENSION ON THE GOOD RT ACTUATOR OF 9.5 INCHES. 2. AFTER REMOVAL, ACTUATOR WAS FROZEN TO TURNING A	ND AFTER FREEING ALL IMPACT DAMAGE, ACTUATORS STILL FROZEN AND THEN RACTHATY IN MOVEMENT. 3. FURTHER DISASSEMBLY REVEA	LED THREAD DAMAGE TO THE UPPER THREADS OF NUT ASSY. THIS THREAD DAMAGE WOULD CAUSE THE ACTUATOR TO BIND AND NOT FULLY E	XTEND THE LT GEAR. CYCLES, 25.		1	L	7	2 	3O				3A20 					 
1995060200521	19950602	00521	CE 	1995	6	2	95ZZZX2617 	1	19950509	G	7922	75944	VALVE 			CESSNA	177 	177B 	2073708	CE 										THERMO BYPASS	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	30915	3091 				17701543				DURING AN OIL CHANGE, THE THERMOSTATIC BYPASS VALVE WAS REMOVED FROM INSPECTION PER LYCOMING MANDATORY SB 518A. THE CRI	MP NUT ON VALVE WAS FOUND LOOSE AND VALVE SEAT WORN. WHILE INSPECTING A BEECH SPORT, PIPER CHEROKEE 180 AND AN ENSTORM 	280F HELICOPTER, IT WAS FOUND THEIR VALVES HAD LOOSE CRIMP NUT AND WORN VALVE SEAT. THE DEFECTIVE VALVES WERE ALL REPLA	CED WITH SUPERIOR AIR PARTS SL 53E19600 WHICH HAS DRILLED NUT AND ROLL PIN.			1	H	7	1 	3O				A13CE 					 
1995060200522	19950602	00522	EA 	1995	6	2	95ZZZX2618 	2	19950515	G	8520	LW13781	CRANKCASE 			PIPER 	PA60 	PA60601P 	7106012	NM 	LYC 	O540 	IO540S1A5 	41532	EA 					LT HALF NR 2 CYL	CRACKED 	G	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	901RG		175 		1733	61P0495203	L838648A			FOUND ENGINE CASE CRACKED FROM NR 2 CYLINDER RETAINING STUD HOLE (LOWER, FORWARD LARGE BOLT).						1	M	7	2 	3O	3	O	RT	A17WE 	1E4				 
1995060200523	19950602	00523	CE 	1995	6	2	95ZZZX2619 	1	19950508	G	2430	S1580A1	SOLENOID 			CESSNA	210 	P210N 	2073454	CE 										BATTERY MASTER	BURNED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	4556K	1531 				21000218				DURING ANNUAL INSPECTION, OWNER COMMENTED ABOUT DIM OR FLICKERING LIGHTS AND INTERMITTENT INSTRUMENT FAILURE. DURING TR	OUBLESHOOTING PROCESS, A VOLTAGE DROP WAS FOUND ACROSS CONNECTION OF BATTERY CONTACTOR (24V IN AND 10 TO 12 OUT). CONTA	CTOR REMOVED AND CUT OPEN - REVEALED BURNED/WORN CONTACTS INSIDE CONTACTOR BODY. SUGGEST CHECK FOR VOLTAGE DROP ACROSS 	ALL CONTACTORS WITH THIS PART NUMBER.			1	H	7	1 	3O				3A21 					 
1995060200524	19950602	00524	SO 	1995	6	2	95ZZZX2620 	1	19950502	G	2510	9680609	SEAT 			PIPER 	PA28 	PA28151 	7102805	SO 										COPILOT	FRAME CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	44714	2560 				287515013				DURING ANNUAL INSPECTION, COPILOT SEAT FRAME WAS FOUND CRACKED ON BOTH SIDES WHERE BRACKETS THAT ALLOW SEAT BACK TO PIVO	T ARE ATTACHED. MAY BE CAUSED BY PILOT LEANING ON COPILOT SEAT BACK WHILE ENTERING AIRCRAFT.					1	L	7	1 	3O				2A13 					 
1995060200525	19950602	00525	SO 	1995	6	2	95ZZZX2622 	1	19950508	G	3213	6531904	HOUSING 			PIPER 	PA28 	PA28140 	7102802	SO 										LT-RT MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	444KC	7357 				28732504				DURING ANNUAL INSPECTION, FOUND BOTH MLG UPPER STRUT HOUSINGS (CYLINDERS) CRACKED AT INBD RADIUS OF TORQUE LINK BOSS. S	USPECT MOST LIKELY DUE TO HIGH TIME AND AIRCRAFT BEING USED FOR TRAINING.					1	L	7	1 	3O				2A13 					 
1995060200526	19950602	00526	CE 	1995	6	2	95ZZZX2623 	1	19950328	G	7120	07516001	MOUNT 			CESSNA	182 	182J 	2072722	CE 										FIREWALL FWD	PITTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	02	3063F	5131 				18257163				DURING ANNUAL INSPECTION, FOUND ENGINE MOUNT PITTED MORE THAN 10 PERCENT OF TUBE THICKNESS IN AREA OF CLOSE PROXIMITY TO	 THE EXHAUST SYSTEM. CESSNA PARTS MANUAL DOES NOT LIST EXHAUST DEFLECTOR, HEAT SHIELDS, FOR THIS SERIAL NUMBERED AIRCRA	FT. SUBMITTER SUGGESTS THE USE OF HEAT SHIELDS.				1	H	7	1 	3O			NT	3A13 					 
1995060200527	19950602	00527	SO 	1995	6	2	95ZZZX2624 	1	19950421	G	2430	9937705	SWITCH 			PIPER 	PA38 	PA38112 	7103812	SO 										BATTERY	LOOSE TERMINAL 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	4265E	1760 				3878A0513				LOSE TERMINAL ON BACK OF SWITCH FOUND DURING ANNUAL INSPECTION. SUSPECT INCORRECT ASSEMBLY OR MISHANDLED PART. RECOMME	ND INSPECTION EVERY 100 HOURS AND/OR ANNUAL INSPECTION(S). REPLACE PART IF NECESSARY.					1	L	7	1 	3O				A18SO 					 
1995060200528	19950602	00528	SO 	1995	6	2	95ZZZX2625 	1	19950512	G	5711		SPAR 			LUSCOM	8 	8A 	8190104	SO 										WING	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	71801	2000 			2778	3228				FOUND 3 DIME-SIZED INTERGRANULAR CORROSION SPOTS 24 INCHES INBOARD FROM ATTACH FITTING.						1	H	7	1 	3O				A694 					 
1995060200529	19950602	00529	CE 	1995	6	2	95ZZZX2626 	1	19950518	G	5711	51220414	SPAR CAP 			CESSNA	310 	310Q 	2074242	CE 										RT WING	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	7891Q	7000 				310Q0660				CORROSION OF RIGHT WING UPPER AFT INBOARD SPAR CAP ASSEMBLY. EXTENT OF CORROSION WAS PAST ALLOWABLE REPAIR LIMITS SET F	ORTH BY CESSNA AIRCRAFT COMPANY. THE SPAR IS LOCATED DIRECTLY BEHIND THE EXHAUST AUGMENTORS AND IS BEING CORRODED BY TH	E EXHAUST EMISSIONS. PERIODIC CLEANING OF THE FLAP WELL AREA AND CORROSION TREATMENT IS RECOMMENDED. SPAR CAP ASSEMBLY	 WAS REPLACED WITH A NEW UNIT FROM CESSNA.			1	L	7	2 	3O				3A10 					 
1995060200530	19950602	00530	EA 	1995	6	2	95ZZZX2627 	2	19950504	G	8530	77160	VALVE GUIDE 		LW12427 	AVIANW	SKYHWK	SKYHAWK 	0900104	NM 	LYC 	O360 	O360A4M 	41514	EA 					EXHAUST	WORN 	B			NQ2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05	3823R	207 				17255323	L3387436A			CYLINDER REMOVED DUE TO LOW COMPRESSION. FOUND .010 INCH WEAR IN EXHAUST GUIDE ALLOWING EXHAUST VALVE TO WEAR SEAT AND 	VALVE FACE. THIS WAS A FACTORY NEW ENGINE. VALVE GUIDE, PN 77160. VALVE, PN LW19001.					1	B	0	0 		3	O		A3NW 	E286				 
1995060200532	19950602	00532	CE 	1995	6	2	95ZZZX2629 	1	19950502	G	3242	RFS6B5	PAD RIVET 	GOODYEARAERO	11480083 	BEECH 	1900 	1900C 	1154161	CE 										BRAKE PAD	CRACKED 	B			NOZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23										DURING RE-PADDING OF BRAKE STATIONARY DISC, RIVETS WERE FOUND TO HAVE MULTIPLE CRACKS IN THE SHOP HEAD AND NOT SECURELY 	HOLDING PAD IN POSITION.					2	L	7	2 	4T			RT	A24CE 					 
1995060200534	19950602	00534	CE 	1995	6	2	95ZZZX2631 	1	19950428	G	2721	MS211518C	ROD END 			BEECH 	200 	200BEECH 	1152920	CE 										RUD TRIM TAB	FAILED 	D		A		A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			CL	CLIMB 	1			SW	17	87GA					BB87				SHORTLY AFTER TAKEOFF, PILOT REPORTED A VIBRATION COMING FROM THE TAIL OF THE AIRCRAFT. THE AIRCRAFT LANDED WITH NO PRO	BLEMS. MAINTENANCE PERSONNEL FOUND RUDDER TRIM TAB ROD END AT THE RUDDER TRIM TAB ACTUATOR HAD BROKEN INTO TWO PIECES C	AUSING THE TRIM TAB AND RUDDER TO FLUTTER. PART TOTAL TIME IS UNKNOWN. AIRCRAFT TOTAL TIME IS 6451.0.				1	L	7	2 	4T				A24CE 					 
1995060200535	19950602	00535	EA 	1995	6	2	95ZZZX2632 	1	19950509	G	2841	656054	GAUGE 	ROCHSTRGAUGE		SCWZER	G164T 	G164D 	3952804	EA 										FUEL QTY	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	8177K	27 				8D				LOSS OF PROPER FUEL READINGS. SUSPECT DUE TO MAGNET ON END OF GAUGE SHAFT COMING LOOSE.						1	Q	7	1 	3T				1A16 					 
1995060200537	19950602	00537		1995	6	2	95ZZZX2634 	1	19950508	G	7922	53E19600	VALVE 								LYC 	O360 	AEIO360B4A 	41514	EA 					THERMO BYPASS	NUT LOOSE 	B			CT3R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	17					55733		L1654251A			INSPECTION OF THERMOSTIC BYPASS VALVE. NUT WAS FOUND LOOSE. SERIAL NUMBER IS HIGHER THAN VALVES AFFECTED IN TEXTRON LY	COMING SB 518B.										3	O			1E10				 
1995060900069	19950609	00069		1995	6	9	95ZZZX2635 	4	19950404	G	2565	1785135	CYLINDER 	AIRCRUISERS 	A320 															SLIDE RAFT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19					1290					ON FILLING CYLINDER, A CRACK WAS SEEN ON NECK OF UNIT. THE PRESSURE WAS 2,000 PSI. UNIT WAS IMMEDIATELY DISCHARGED. U	NIT WAS SENT TO AIR CRUISERS COMPANY FOR EVALUATION. SLIDE ASSEMBLY WAS RECEIVED BY EAM IN A DEPLOYED CONDITION. GAUGE	 ON CYLINDER ASSEMBLY WAS DAMAGED DUE TO HARD CONTACT. THIS MAY HAVE ALSO CAUSED MALFUNCTION TO CYLINDER NECK.																	 
1995060900071	19950609	00071	CE 	1995	6	9	95ZZZX2637 	1	19950509	G	2721	51152121	JACKSCREW 			CESSNA	421 	421B 	2076014	CE 										RUDDER TAB	BROKEN 	D	S	A		O				OTHER 				E	F		VIBRATION/BUFFET 	FLT CONT AFFECTED 		AP	APPROACH 	1			SW	99	555MY	3334 				4210886				WHILE ON FINAL APPROACH JUST BEFORE TOUCH-DOWN, PILOT REPORTED SLIGHT OSCILLATION IN RUDDER PEDALS AND A STRANGE VIBRATI	ON TOWARD REAR OF ACFT. PRELIMINARY INVESTIGATION REVEALED RUDDER TRIM TAB HAD BECOME DISCONNECTED FROM THE ACTUATOR AT	 SOME POINT. FURTHER INVESTIGATION REVEALED RUDDER TRIM TAB ACTUATOR JACKSCREW HAD BROKEN WHERE THE THREADS BEGIN AND T	HE UNTHREADED PORTION WAS SEVERELY BENT. SUSPSECT CAUSE IS THAT REPEATED GROUND HANDLINGS WITH RUDDER GUSTLOCK INSTALLE	D PUT UNDUE FORCE AGAINST THIS PART, AS THE RUDDER GUSTLOCK ONLY ENGAGES RUDDER TAB, NOT THE RUDDER.		1	L	7	2 	3O				A7CE 					 
1995060900072	19950609	00072	CE 	1995	6	9	95ZZZX2638 	1	19950510	G	2730	1318816	ROD END 			BEECH 	33 	F33A 	1151425	CE 										ELEV PUSH/PULL	BALL LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	82964	385 				CE1761				INSPECTION FOUND ELEVATOR CONTROL TUBE BRASS INSERTS THAT HOLD IN THE BALL END ARE LOOSE AND ROTATING. THEY NEED BETTER	 ROD ENDS, AND/OR LARGE AERA WASHERS TO KEEP ENDS FROM FALLING OFF OVER BOLT AND NUT ENDS AND JAMMING THE CONTROLS.					1	L	7	1 	3O				3A15 					 
1995060900073	19950609	00073	CE 	1995	6	9	95ZZZX2639 	1	19950303	G	5320	05133111	SUPPORT ASSY 			CESSNA	172 	172E 	2072412	CE 										FIREWALL	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	3713S	3000 				17250913				SUPPORT ASSY IS A 'Y' SHAPED SUPPORT THAT TRANSFERS LOADS FROM THE CONTROL LOCK COLLAR TO THE FIREWALL. THESE LOADS ARE	 IMPOSED WHEN THE CONTROL LOCK IS INSTALLED AND THE AIRCRAFT IS PARKED DOWNWIND IN STRONG WINDS. A CLUE IS CRACKS IN T	HE FIREWALL FORWARD OF THE CONTROL YOKE FOR THE PILOT.				1	H	7	1 	3O			NT	3A12 					 
1995060900074	19950609	00074	SO 	1995	6	9	95ZZZX2640 	1	19950303	G	3213	2075208	TRUNNION 			PIPER 	PA30 	PA30 	7103002	SO 										LT MLG	CRACKED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	13	8296Y					301435				FOUND LEFT MAIN GEAR TRUNNION CRACKED FROM BEHIND BRAKE LINE CLAMP HOLE INTO CYLINDER WHERE OLEO WOULD NOT HOLD PRESSURE	. WHEN REPLACING STRUT, FOUND STRUT ON THIS TWIN COMANCHE WAS FROM A SINGLE COMANCHE (MUCH LIGHTER CONSTRUCTION). THE 	OLEO METERING PIN WAS FOUND TO COME FROM A NOSE STRUT. TWIN COMANCHE PARTS WERE INSTALLED.				1	L	7	2 	3O				A1EA 					 
1995060900075	19950609	00075	CE 	1995	6	9	95ZZZX2641 	1	19950511	G	2121	12238002013	BLOWER 			BEECH 	2000 	2000 	1152000	CE 										AFT FUSELAGE	BLADES DEFECTIVE	D				K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			GL	11	8074S	492 			17	NC33				PILOT REPORTED A VIBRATION IN FLOOR. FURTHER INVESTIGATION SHOWED AIR CONDITIONER CONDENSOR AXIAL BLOWER WAS MISSING AP	PROXIMATELY 30 PERCENT TO 35 PERCENT OF BLADES CAUSING A SEVERE IMBALANCE. CAUSE OF MISSING BLADES UNKNOWN.					1	L	7	2 	4T			RT	A38ACE 					 
1995060900076	19950609	00076	CE 	1995	6	9	95ZZZX2642 	1	19950504	G	3010	S29S7D522010	DE-ICE BOOT 	BFGOODRICH 		BEECH 	2000 	2000 	1152000	CE 										RT WING	DEFECTIVE 	B			ERY2	O				OTHER 				O			OTHER 			CR	CRUISE 	1			SO	11	5549B	310 			247KV	NC15				RIGHT FOWARD WING DE-ICE BOOT BALLOONING IN-FLIGHT. THIS UNIT WAS REMOVED AND REPLACED WITH A NEW UNIT. THIS UNIT WAS 	PREVIOUSLY INSTALLED ONE YEAR PRIOR. THIS IS A CONTINUING PROBLEM WITH THE MODEL 2000 AIRCRAFT.					1	L	7	2 	4T			RT	A38ACE 					 
1995060900077	19950609	00077	CE 	1995	6	9	95ZZZX2643 	1	19950504	G	3010	S29S7D522009	DE-ICE BOOT 	BFGOODRICH 		BEECH 	2000 	2000 	1152000	CE 										LT WING	DEFECTIVE 	B			ERY2	O				OTHER 				O			OTHER 			CR	CRUISE 	1			SO	11	5549B	596 			246DV	NC15				LEFT FORWARD WING DE-ICE BOOT BALLOONING IN-FLIGHT. THIS UNIT WAS REMOVED AND REPLACED WITH A NEW UNIT. THIS UNIT WAS 	PREVIOUSLY INSTALLED 11-4-92. THIS IS A CONTINUING PROBLEM WITH THE MODEL 2000 AIRCRAFT.					1	L	7	2 	4T			RT	A38ACE 					 
1995060900078	19950609	00078	SO 	1995	6	9	95ZZZX2644 	2	19950426	G	8520		CRANKCASE 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520N 	17032	SO 					LT SIDE ENG	CRACKED 	B			EBVR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	09	6866L	1623 				421C1077	277072R			DURING INSPECTION, FOUND CASE CRACKED THROUGH NR 5 CYLINDER STUD AT 5 O'CLOCK POSITION, APPROXIMATELY 1 INCH IN LENGTH. 	 CRACK WAS LEAKING OIL.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995060900079	19950609	00079	SO 	1995	6	9	95ZZZX2645 	2	19950426	G	8520		CRANKCASE 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520N 	17032	SO 					RT SIDE ENG	CRACKED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	6866L	1623 				421C1077	277079R			DURING INSPECTION, FOUND CASE CRACKED THROUGH NR 5 CYLINDER STUD AT 5 O'CLOCK POSITION, APPROXIMATELY 1 INCH IN LENGTH. 	 CRACK WAS LEAKING OIL.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995060900080	19950609	00080	EA 	1995	6	9	95ZZZX2646 	2	19950418	G	8500		ENGINE 			CESSNA	172 	172P 	2072436	CE 	LYC 	O320 	O320D2J 	41508	EA 					OIL SYSTEM	MAKING METAL 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	62085	2283 				17275209	L1162539A			FILTER WAS OPENED DURING AN ANNUAL INSPECTION. A HIGH AMOUNT OF METAL WAS FOUND, MOSTLY ALUMINUM WITH SOME STEEL. AIRC	RAFT WAS GROUNDED AND ENGINE SENT OUT TO OVERHAUL FACILITY FOR DISASSEMBLY.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995060900081	19950609	00081	SO 	1995	6	9	95ZZZX2647 	2	19950426	G	7414	1056513	STOP PIN 			MOONEY	M20 	M20K 	5870220	SW 	CONT 	O360 	TSIO360GB 	17025	SO 					LT MAG	DISLOCATED 	D				O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			EA	07	4086H					250462	309496			PILOT REPORTED LOW OIL PRESSURE AFTER TAKEOFF. AFTER TROUBLESHOOTING ACTUAL PRESSURE, FOUND WHAT WAS LATER TO BE DETERM	INED TO BE THE STOP PIN FROM THE LEFT MAGNETO IN THE SUCTION SCREEN CAUSING LOW FLOW TO OIL PUMP.					1	L	7	1 	3O	3	O		2A3 	E9CE				 
1995060900082	19950609	00082	SO 	1995	6	9	95ZZZX2648 	1	19950406	G	5260		STEP 			PIPER 	PA28 	PA28140 	7102802	SO 										CABIN	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	02	10GH	2021 				2820482				UPON REMOVAL OF CABIN ASSIST STEP, SEVERE CORROSION NOTED. DISSIMILAR METALS CAUSED THE PROCESS. SUBMITTER SUGGESTS RE	MOVAL OF STEPS WHEN CORROSION IS EVIDENT AT THE AFT SIDE AREAS.					1	L	7	1 	3O				2A13 					 
1995060900083	19950609	00083	SO 	1995	6	9	95ZZZX2649 	1	19950501	G	3210	20829000	SWIVEL STUD 			PIPER 	PA24 	PA24250 	7102404	SO 										LT MLG	BENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	5195P					24219				WHILE PERFORMING INSPECTION FOR AD 77-13-21, FOUND RT SWIVEL STUD BENT (POSSIBLY CRACKED TOO) AND RT SWIVEL STUD WAS THE	 INCORRECT PART (WAS LARGER STUD FOR LATER MODELS, EXPECT ORIGINAL PREVIOUSLY DAMAGED AND REPLACED WITH WHAT COULD BE FO	UND). ADVISE IN RULES DOCKET NR 93-CE-61-AD.				1	L	7	1 	3O				1A15 					 
1995060900084	19950609	00084	SO 	1995	6	9	95ZZZX2650 	1	19950501	G	3210	20829000	SWIVEL STUD 			PIPER 	PA24 	PA24250 	7102404	SO 										RT MLG	WRONG PART 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	5195P					24219				WHILE PERFORMING INSPECTION FOR AD 77-13-21, FOUND RT SWIVEL STUD BENT (POSSIBLY CRACKED TOO) AND RT SWIVEL STUD WAS THE	 INCORRECT PART (WAS LARGER STUD FOR LATER MODELS, EXPECT ORIGINAL PREVIOUSLY DAMAGED AND REPLACED WITH WHAT COULD BE FO	UND). ADVISE IN RULES DOCKET NR 93-CE-61-AD.				1	L	7	1 	3O				1A15 					 
1995060900085	19950609	00085	SO 	1995	6	9	95ZZZX2651 	1	19950508	G	3230	20846000	BUNGEE ARM 			PIPER 	PA24 	PA24250 	7102404	SO 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	5195P					24219				EARLY THIN WALL BUNGEE ARM HAD BEEN REPLACED PREVIOUSLY. INSPECTION FOUND BOTH LT AND RT ARMS CRACKED. ACFT SHOWS SIGN	 OF PREVIOUS REPAIR FOR GEAR UP LANDING. ACFT TT 3764.					1	L	7	1 	3O				1A15 					 
1995060900086	19950609	00086	SO 	1995	6	9	95ZZZX2652 	1	19950501	G	3230	20846001	BUNGEE ARM 			PIPER 	PA24 	PA24250 	7102404	SO 										RT MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	5195P					24219				UPON DOING 1,000 GEAR AD PER 77-13-21, FOUND RT BUNGEE ARM CRACKED AT RADIUS FOR RETAINER PINS. THIS IS SEEN OFTEN AND 	HAVE REPORTS OF COMPLETE FAILURE IDENTIFIED BY SEVERE SHAKING AT TAXI. THIS WAS THE EARLY THIN-WALLED BUNGEE ARMS. (PN	 20846-000 AND PN 20846-001.)				1	L	7	1 	3O				1A15 					 
1995060900087	19950609	00087	SO 	1995	6	9	95ZZZX2653 	1	19950329	G	3213	2171504	TRUNNION 			PIPER 	PA30 	PA30 	7103002	SO 										NLG	CRACKED 	B			QE5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07					261719					CUSTOMER SENT AIRCRAFT IN FOR REPAIR. DYE PENETRANT INSPECTION REVEALED CRACK 2.25 INCHES LONG PARALLEL WITH TURN-STOP 	WHICH RUNS VERTICALLY. CUSTOMER REPORTED COMPONENT CRACKED SINCE 1976 AND SEES NO HARM ON REINSTALLING ON AIRCRAFT AS I	S. CUSTOMER ALSO REPORTED RT MAIN GEAR CRACKED, BUT HE WOULD REPAINT AND REINSTALL.				1	L	7	2 	3O				A1EA 					 
1995060900088	19950609	00088		1995	6	9	95ZZZX2654 	4	19950412	G	2562	ELT61	ELT 	DORNEMARGLN 		CESSNA	172 	172N 	2072434	CE 										CABIN	INOPERATIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	7344A	2499 	300 		42861	17269044				WHILE PERFORMING OPERATIONAL CHECK REQUIRED BY FAR 91.207D, A CARRIER ONLY SIGNAL WAS GENERATED WHEN ACTIVATED EITHER BY	 MANUAL OPERATION OR BY 'G' SWITCH OPERATION.					1	H	7	1 	3O			NT	3A12 					 
1995060900089	19950609	00089	CE 	1995	6	9	95ZZZX2655 	1	19950428	G	7602	6301463AH	CONTROL ARM 			BEECH 	58 	58 	1152740	CE 										FUEL MIXTURE	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1560Y	58 				TH1717				FUEL MIXTURE CONTROL LEVER BROKEN OFF. LOOKS AS IF THE PART WHEN CASTED HAD A DEFECT.						1	L	7	2 	3O				3A16 					 
1995060900090	19950609	00090	SO 	1995	6	9	95ZZZX2656 	1	19950424	G	7120		MOUNT 			PIPER 	PA28 	PA28140 	7102802	SO 										LOWER RT ENG	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	02	10GH	2021 				2820482				FOUND LOWER RT ENGINE MOUNT LEG WORN BY EXHAUST CLAMP DUE TO CLOSE PROXIMITY. CARE IS NECESSARY WHEN POSITIONING EXHAUS	T PIPE SUPPORT CLAMP.					1	L	7	1 	3O				2A13 					 
1995060900091	19950609	00091	EA 	1995	6	9	95ZZZX2657 	2	19950421	G	8530		CYLINDER 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					CYLS 2-4	RINGS BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	3065E	4095 	725 			17271425	L405276			DURING 100-HOUR INSPECTION, COMPRESSION ON CYLINDERS 2 AND 4 LOW. REMOVED CYLINDERS. BROKEN AND MISSING PIECES OF RING	. OIL SAMPLE SENT OUT. OVERHAUL FACILITY SAYS TAPPET DAMAGE. INSPECTED SAME AND FOUND NR 1 CYLINDER EXHAUST TAPPET WI	TH HEAVY DAMAGE. ENGINE SENT OUT FOR REPAIR.				1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995060900092	19950609	00092	CE 	1995	6	9	95ZZZX2659 	1	19950417	G	2730	05130633	BRACKET 			CESSNA	172 	172 	2072402	CE 										ELEV BELLCRANK	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	3611L	2986 				17253780				DURING ANNUAL INSPECTION, PN 0513063-3 WAS FOUND CRACKED ON ALL 4 CORNERS. WAS REPLACED WITH NEW PART FROM CESSNA. THE	 NEW PART BEING MADE FROM MUCH HEAVIER MATERIAL.					1	H	7	1 	3O			NT	3A12 					 
1995060900093	19950609	00093	SO 	1995	6	9	95ZZZX2660 	2	19950130	G	8520	629680M010	COLLAR 								CONT 	O520 	IO520* 	17032	SO 					CRANKSHAFT OIL	OUT OF SPEC 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11										OIL TRANSFER COLLAR IS OUT OF SPECIFICATIONS. THIS PART WOULD HAVE CAUSED AN ENGINE FAILURE.											3	O			E5CE				 
1995060900094	19950609	00094	SO 	1995	6	9	95ZZZX2661 	2	19950407	G	8520	649141	CRANKSHAFT 								CONT 	O470 	O470R 	17026	SO 					MAIN BEARING	WORN 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11							189509			CRANKSHAFT MAIN BEARING JOURNALS OUT OF LIMITS .0005 INCH (ONE-HALF THOUSANDS.) CRANKSHAFT CONNECTING ROD JOURNALS OUT 	OF LIMITS .0002 INCH. (TWO-TENTHS OF A THOUSANDS.)										3	O			E273				 
1995060900095	19950609	00095	SO 	1995	6	9	95ZZZX2662 	2	19950130	G	8530	629325	INTAKE PIPE 								CONT 	O520 	IO520* 	17032	SO 					CYLINDER	CRACKED 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11										INDUCTION PIPE CRACKED, APPROXIMATELY 1.50 INCHES LONG.											3	O			E5CE				 
1995060900096	19950609	00096	SO 	1995	6	9	95ZZZX2663 	2	19950201	G	8530		CYLINDER 			BEECH 	35 	V35A 	1151544	CE 	CONT 	O520 	IO520BA 	17032	SO 					NR 2	CRACKED 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	7624N	2147 	521 			D8854	1218568B			CRACKED CYLINDER FROM EXHAUST PORT AROUND CYLINDER HEAD TO SPARK PLUG HOLE, THREE-FOURTHS SEPARATED FROM BARREL.						1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995060900097	19950609	00097	SO 	1995	6	9	95ZZZX2664 	2	19950216	G	8520		CRANKSHAFT 								CONT 	O520 	IO520BA 	17032	SO 					ENGINE	WORN 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11							807023R			ENGINE WAS CONTAMINATED WITH METAL. THE CRANKSHAFT HAD TO BE TURNED UNDERSIZE TO REPAIR. FACTORY TEST RUN TIME ONLY.											3	O			E5CE				 
1995060900098	19950609	00098	SO 	1995	6	9	95ZZZX2665 	2	19950306	G	8530	646286	VALVE STEM 								CONT 	O520 	IO520BB 	17032	SO 					CYLINDER	WORN 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11		333 					274831R			FOUND 5 EXHAUST VALVE STEMS WORN ONE-FOURTH THE DIAMETER OF THE VALVE STEM. THESE WERE FOUND ON AN ENGINE TEAR DOWN FOR	 PROPELLER STRIKE. THESE VALVES WOULD EVENTUALLY HAVE CAUSED ENGINE FAILURE.										3	O			E5CE				 
1995060900099	19950609	00099	SO 	1995	6	9	95ZZZX2666 	2	19950216	G	8530		CYLINDER 								CONT 	O520 	TSIO520BE 	17040	SO 					STUD HOLE	CRACKED 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11										ROCKER ARM RETAINING STUD HELICOIL IMPROPERLY INSTALLED AND THE CYLINDER WAS CRACKED OUT OF SAME HOLE.											3	O			E8CE				 
1995060900100	19950609	00100	SO 	1995	6	9	95ZZZX2667 	2	19950407	G	8530	629117	VALVE ROTOR 								CONT 	O520 	IO520BB 	17032	SO 					CYLINDER	FAILED 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11		1900 					573517			VALVE ROTOR FAILED CAUSING DAMAGE TO THE VALVE SPRING AND VALVE GUIDE.											3	O			E5CE				 
1995060900101	19950609	00101	SO 	1995	6	9	95ZZZX2668 	2	19950306	G	8530	625393	VALVE SPRING 								CONT 	O550 	IO550* 		SO 					CYLINDER	SEAT MISSING 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11		400 								LOWER VALVE SPRING SEAT MISSING.											3	O			E3SO				 
1995060900102	19950609	00102	SO 	1995	6	9	95ZZZX2671 	2	19950126	G	7414	M3525	COIL 	SLICK 	88090670 	BEECH 	58 	58 	1152740	CE 	CONT 	O520 	IO520C 	17032	SO 					MAG	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	358Y	825 				TH1557	6763A7			NO HIGH TENSION RESISTANCE. SECOND COIL REPLACED ON AIRCRAFT. THIS COIL DATE CODE 91688.						1	L	7	2 	3O	3	O		3A16 	E5CE				 
1995060900103	19950609	00103	CE 	1995	6	9	95ZZZX2672 	1	19950510	G	2130	1023800007	CABLE ASSY 			BEECH 	58 	58P 	1152744	CE 										LT PRESS CONT	STUCK 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	6UT	3734 				TJ466				AFTER PRESSURIZATION PROBLEM, PILOT PULLED BOTH SHUT-OFF HANDLES CONTROLLING VALVES AT FIREWALL. AFTER FIXING PROBLEM A	T OUTFLOW AND SAFETY VALVES, ATTEMPTED TO RESET HANDLES IN COCKPIT CAUSING INNER CONTROL TO PUSH OUT OF HOUSINGS. THESE	 CONTROLS ARE NORMALLY LEFT IN ONE POSITION ALL THE TIME. SUBMITTER SUGGESTS WORKING THESE CONTROLS OCCASIONALLY TO KEE	P THEM FREE.			1	L	7	2 	3O				A23CE 					 
1995060900104	19950609	00104	CE 	1995	6	9	95ZZZX2673 	1	19950510	G	2130	1023800009	CABLE ASSY 			BEECH 	58 	58P 	1152744	CE 										RT PRESS CONT	STUCK 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	6UT	3734 				TJ466				AFTER PRESSURIZATION PROBLEM, PILOT PULLED BOTH SHUT-OFF HANDLES CONTROLLING VALVES AT FIREWALL. AFTER FIXING PROBLEM A	T OUTFLOW AND SAFETY VALVES, ATTEMPTED TO RESET HANDLES IN COCKPIT CAUSING INNER CONTROL TO PUSH OUT OF HOUSINGS. THESE	 CONTROLS ARE NORMALLY LEFT IN ONE POSITION ALL THE TIME. SUBMITTER SUGGESTS WORKING THESE CONTROLS OCCASIONALLY TO KEE	P THEM FREE.			1	L	7	2 	3O				A23CE 					 
1995060900105	19950609	00105	EA 	1995	6	9	95ZZZX2674 	2	19950223	G	7414	10103209	COIL 	BENDIX 		PIPER 	PA28 	PA28180 	7102808	SO 	LYC 	O360 	O360A3A 	41514	EA 					MAG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	44156				A105928	7405224				THIS COIL WAS INSTALLED IN MAGNETO NOT COVERED BY AD 94-01-03 OR AD 94-01-03-R1. SUBMITTER SUGGESTS REMOVING PLASTIC FL	AG ON DATA PLATE SIDE OF ALL SUSPECT MAGS AND LOOK WITH A PEN LIGHT FOR IMPROPER COILS.					1	L	7	1 	3O	3	O		2A13 	E286				 
1995060900247	19950609	00247	SO 	1995	6	9	95ZZZX2675 	2	19950427	G	8530	646652	CYLINDER 			CESSNA	210 	P210N 	2073454	CE 	CONT 	O520 	TSIO520P 	17040	SO 					NR 5 CYL HEAD	SEPARATED 	B	P		FE6R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	07	4783K				4445	P21000314	513326			NO LOG BOOKS AVAILABLE AT TIME OF REPORT. NR 5 CYLINDER HEAD COMPLETELY SEPARATED FROM BARREL. SEPARATION OCCURRED IN 	ALUMINUM HEAD AT EXTREME TOP OF STEEL BARREL. NO DAMAGE OCCURRED IIN BARREL THREADED AREA. CYLINDER PREVIOUSLY CHROME 	PLATED AND IS MARKED 1-84 CP-81580--05, .020 INCH ON CASE END OF BARREL.				1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995060900248	19950609	00248	CE 	1995	6	9	95ZZZX2676 	1	19950429	G	3230	MS16625162	SNAP RING 		08940002 	CESSNA	421 	421B 	2076014	CE 										MLG GEARBOX	MISSING 	D	S	A		K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	19	4993J	2558 				4210034				LANDING GEAR WOULD NOT EXTEND MANUALLY. AFTER SEVERAL TURNS ON HANDCRANK, THE GEARBOX WOULD BIND UP AND NOT MOVE IN EIT	HER DIRECTION. ELECTRIC OPERATION WAS NORMAL, DISASSEMBLY OF GEARBOX FOUND SNAP RING MISSING ALLOWING WORN GEAR SHAFT T	O SHIFT UNDER LOAD AND BECOME ENGAGED TO BOTH MANUAL AND ELECTRIC DRIVES AT THE SAME TIME. WEAR ON GEARBOX COVER INDICA	TES THIS SNAP RING HAS BEEN MISSING FOR AN EXTENDED PERIOD OF TIME. REPLACEMENT OF SNAP RING AND REASSEMBLY OF GEARBOX 	ALLOWED NORMAL OPERATION.		1	L	7	2 	3O				A7CE 					 
1995060900249	19950609	00249	SO 	1995	6	9	95ZZZX2677 	1	19950508	G	2842	6810102	SENDING UNIT 	STWARNER 		PIPER 	PA28 	PA28161 	7102803	SO 										FUEL CELL FLOAT	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	2207Z	3877 				287916385				FUEL SENDING UNIT READ EMPTY WITH FUEL TANKS FULL. REMOVED FUEL CELL AND FOUND FOAM FLOAT ASSY BROKEN OFF FROM SENDING 	UNIT ARM. THIS IS THE THIRD FOAM ASSY FOUND WORN IN THIS MANNER. DUE TO THE POSSIBILITY OF INACCURATE READINGS AND THE	 INABILITY TO INSPECT THIS AREA WITHOUT THE COMPLETE REMOVAL OF THE FUEL CELL, SUBMITTER RECOMMENDS A NEW DESIGN FLOAT B	E INSTALLED WITH A METALLIC BUSHING FITTED INTO THE FOAM FLOAT TO REDUCE WEAR.			1	L	7	1 	3O				2A13 					 
1995060900250	19950609	00250	CE 	1995	6	9	95ZZZX2678 	1	19950419	G	7160	BA111	SCREEN 	BRACKETT 		CESSNA	172 	R172K 	2072431	CE 										FILTER SUPPORT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	736AT	578 				R1722379				WHILE PERFORMING AN ANNUAL INSPECTION ON AIRCRAFT MODIFIED BY BRACKETT STC SA-71GL, FILTER SUPPORT SCREEN WAS FOUND INST	ALLED WITH THE MATING FLANGE MISALIGNED CAUSING 2 CRACKS ABOUT 1 CM LONG, CREATING THE POSSIBILITY OF FOD ENTERING THE I	NDUCTION SYSTEM. THIS AREA CAN ONLY BE INSPECTED BY REMOVAL OF THE FILTER ASSY. RECOMMEND ONE-TIME INSPECTION FOR ALIG	NMENT.			1	H	7	1 	3O				3A17 					 
1995060900252	19950609	00252	EA 	1995	6	9	95ZZZX2680 	2	19950501	G	8530		VALVE 			CESSNA	172 	172I 	2072426	CE 	LYC 	O320 	O320E2D 	41508	EA 					CYL EXHAUST	BROKEN 	C				O				OTHER 				O			OTHER 			CR	CRUISE 	1			EA	09	35496		1460 			17256800	L210227A			WHILE IN CRUISE, EXHAUST VALVE BROKE APPROXIMATELY ONE-HALF WAY UP THE STEM. THE CYLINDER HEAD AND THE PISTON WERE REND	ERED UNSERVICEABLE DUE TO THEIR COMBINED EFFORT TO BREAK THE VALVE INTO SMALL ENOUGH PIECES TO BLOW THEM OUT THE EXHAUST	 SYSTEM.				1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995060900253	19950609	00253	SO 	1995	6	9	95ZZZX2681 	2	19950501	G	8520		CRANKCASE 			CESSNA	150 	150J 	2071820	CE 	CONT 	O200 	O200A 	17020	SO 					CYLINDER	STUD PULLED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	63454	4049 	306 			1077327	253496A48			WHILE RETORQUING CYLINDER HOLD-DOWN NUT, THE STUD PULLED OUT OF ITS THREADS IN THE OPPOSITE CASE HALF; THUS, THE CASE HA	S TO BE SPLIT TO REPAIR THE THREADS. THIS IS A COMMON PROBLEM AND COULD BE PREVENTED BY THE INSTALLATION OF HELICOILS E	ACH TIME THE ENGINE IS OPENED.				1	H	7	1 	3O	3	O		3A19 	E252				 
1995060900254	19950609	00254	CE 	1995	6	9	95ZZZX2682 	1	19950518	G	5711	51220411	SPAR CAP 			CESSNA	310 	310Q 	2074242	CE 										LT WING	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	7891Q	7000 				310Q0660				CORROSION LEFT WING UPPER FORWARD SPAR CAP ASSEMBLY. EXTENT OF CORROSION WAS PAST ALLOWABLE REPAIR LIMITS SET FORTH BY 	CESSNA A/C CO. THE SPAR IS BEING CORRODED BY EXHAUST EMISSIONS PENETRATING INTO THAT AREA. PERIODIC CLEANING OF THIS A	REA AND CORROSION TREATMENT IS RECOMMENDED. THE SPAR CAP WAS REPLACED WITH A NEW UNIT FROM CESSNA.				1	L	7	2 	3O				3A10 					 
1995060900255	19950609	00255	SO 	1995	6	9	95ZZZX2683 	1	19950503	G	8120	646434	CLAMP 			PIPER 	PA46 	PA46310P 	7104605	SO 	CONT 	O520 	TSIO520BE 	17040	SO 					LT TURBO EXH	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	424J					468408019	273511R			ON 5-3-95 WHILE ENGINE WAS BEING CHECKED FOR UNRELATED MATTER, MECHANIC NOTED BROKEN CLAMP WHICH HOLDS EXHAUST TO LEFT T	URBOCHARGER. IT APPEARED TO HAVE BEEN OVERTORQUED AS ENDS OF CLAMP WERE TOUCHING AND SAFETY WIRED IN THAT POSITION. ME	CHANIC THEN REMOVED AND INSPECTED SIMILAR CLAMP ON RIGHT TURBO TO EXHAUST AND FOUND IT CRACKED ALSO. SUGGEST EARLY REPL	ACEMENT. THESE APPEARED TO BE ORIGINAL EQUIPMENT.			1	L	7	1 	3O	3	O		A25SO 	E8CE				 
1995060900256	19950609	00256	CE 	1995	6	9	95ZZZX2684 	1	19950501	G	5510	12321391	BRACKET 			CESSNA	206 	U206E 	2073350	CE 										HORIZ STAB	BROKEN 	B			EVGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	9419G	434 				U2061619				OUTBOARD TAB OF BRACKET BROKE OFF AFTER ONLY 434 HOURS. THIS IS THE SECOND BROKEN BRACKET IN 2 YEARS. BROKEN AT RADIUS	 NEAR NUTPLATE AND RIVETS WHERE IT ATTACHES TO THE HORIZONTAL STAB REAR SPAR.					1	H	7	1 	3O				A4CE 					 
1995060900257	19950609	00257	CE 	1995	6	9	95ZZZX2685 	1	19950413	G	2810	052600744	TANK 			CESSNA	172 	172M 	2072418	CE 										FILLER NECK	LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	23	5402R					17263535				INVESTIGATING FUEL LEAK IN RIGHT WING TANK AREA. FOUND FUEL TANK CRACKED APPROXIMATELY ONE-QUARTER OF THE WAY AROUND BA	SE OF FILLER NECK.					1	H	7	1 	3O			NT	3A12 					 
1995060900258	19950609	00258	CE 	1995	6	9	95ZZZX2686 	1	19950509	G	5321	24131171	STIFFENER 			CESSNA	172 	172RG 	2072438	CE 										FLOORBOARD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	462VT	2850 				172RG0343				FOUND UPON PRE-PURCHASE INSPECTION, THE FLOORBOARD AND STIFFENER CRACKED BELOW BOTH INNER RUDDER TORQUE TUBE BEARINGS. T	HIS WILL, IF NOT CORRECTED, CAUSE THE RUDDER TUBE ASSEMBLY TO ROTATE FORWARD. NO REPAIRS WERE MADE AT THIS TIME. SUBMI	TTER STATED THIS IS THE 4TH RG WITH THIS SAME PROBLEM.				1	H	7	1 	3O				3A17 					 
1995060900259	19950609	00259	CE 	1995	6	9	95ZZZX2687 	1	19950512	G	7922	53E19600	VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	3829X	200 			61020	M2306				REMOVED ENGINE FOR NORMAL OVERHAUL. REMOVED THERMOSTATIC BYPASS VALVE TO INSTALL IN REPLACEMENT ENGINE. FOUND CRIMP NU	T LOOSE. THIS VALVE IS NOT SUBJECT TO THE RECURRING INSPECTION AS SHOWN IN SB518C BECAUSE OF SERIAL NUMBER. SUGGEST AL	L VALVES BE INSPECTED AT REGULAR INTERVALS AS SHOWN IN SB518C. REPAIRED VALVE PER SI 1423. CRIMP NUT LOOSE DUE TO POOR	 DESIGN.			1	L	7	1 	3O				A1CE 					 
1995060900260	19950609	00260	SO 	1995	6	9	95ZZZX2688 	1	19950512	G	7160	761038	DOOR CATCH 			PIPER 	PA31 	PA31350 	7103110	SO 										ALT AIR MAGNET	MISSING 	B			BTJR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	59982	3000 				317552071				INSPECTION FOUND ALTERNATE AIR DOOR CATCH MISSING. SUBMITTER SUGGESTS PIPER MODIFY AIRCRAFT TO SIDE MOUNTED MAGNETS.						1	L	7	2 	3O				A20SO 					 
1995060900261	19950609	00261	CE 	1995	6	9	95ZZZX2689 	1	19950219	G	3230	5041011	BELLCRANK 			CESSNA	421 	421B 	2076014	CE 										LT MLG	BROKEN 	D				O				OTHER 				O			OTHER 			CL	CLIMB 	1			NM	09	421EC					421B0135				BELLCRANK WHICH APPEARS TO ACT AS DOWNLOCK, BROKE AND THE LANDING GEAR BEGAN THE RETRACTION CYCLE, BUT JAMMED THREE-FOUR	THS OF THE WAY THROUGH THE CYCLE. THE BROKEN AREA APPEARS TO HAVE BEEN CRACKED FOR SOME TIME DUE TO DISCOLORATION OF ME	TAL.				1	L	7	2 	3O				A7CE 					 
1995060900262	19950609	00262	CE 	1995	6	9	95ZZZX2690 	1	19950518	G	3230	08421211	TUBE ASSY 			CESSNA	310 	310A 	2074204	CE 										NLG	FAILED 	E				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			WP	07	97473	3796 				35507				NLG MALFUNCTIONED AND WOULD NOT DOWNLOCK. SUBJECT TUBE FAILED IN COMPRESSION. AIR LOADS RESTRICTED GEAR FROM OBTAINING	 ADEQUATE TRAVEL TO LOCK. PILOT'S SKILLED AIRMANSHIP AT MINIMUM AIRSPEED AND MAXIMUM ANGLE OF DESCENT ALLOWED GEAR TO S	WING FORWARD AND LOCK. AN UNEVENTFUL NORMAL LANDING PERFORMED. NLG INSPECTED FOR FREEDOM OF MOVEMENT. NO ANOMALIES NO	TED. NO EVIDENCE OF PRIOR DAMAGE ON TUBE ASSY ADJACENT TO FRACTURE POINT. SUBMITTER STATED FAILURE OCCURRED MID-SPAN A	ND APPEARS TO BE FATIGUE RELATED.		1	L	7	2 	3O				3A10 					 
1995060900263	19950609	00263	CE 	1995	6	9	95ZZZX2691 	1	19950517	G	7603	12503172	BRACKET 			CESSNA	210 	210M 	2073450	CE 										THROTTLE BODY	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	9036M	1454 				21062053				THE BRACKET ON WHICH THROTTLE CONTROL AND MIXTURE CONTROL CABLES ARE ATTACHED WAS FOUND BROKEN.						1	H	7	1 	3O				3A21 					 
1995060900264	19950609	00264	CE 	1995	6	9	95ZZZX2692 	1	19950502	G	5511	11562001065	HINGE SUPPORT 			BEECH 	100 	B100 	1152919	CE 										HORIZ STAB RIB	ELONGATED HOLES 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	05	87XX	3692 				BE105				DURING 150-HOUR INSPECTION, SLIGHT MOVEMENT WAS NOTED AT RIGHT OUTBOARD ELEVATOR HINGE SUPPORT. INSPECTION OF SUPPORT F	OR HINGE IN STABILIZER SHOWED SEVERAL IRREGULARITIES IN THE COMPLETION OF AD 87-03-01R1 AND MSB 2132. ELEVATOR WAS REMO	VED AND HINGE SUPPORT REMOVED FROM STABILIZER. HOLES IN RIBS THAT ATTACH HINGE SUPPORT WERE SEVERELY ELONGATED DURING R	IVET REMOVAL REQUIRED BY THE AFOREMENTIONED AD AND SB. SUBMITTER SUGGESTS LOW QUALITY WORK HAD BEEN WELL HIDDEN UNTIL P	ARTS HAD STARTED TO 'SMOKE'. SB LIMITS HOLE SIZE TO .219 INCH MAXIMUM. ONE HOLE WAS NEARLY .50 INCH LONG. VERY DANGER	OUS.	1	L	7	2 	4T				A14CE 					 
1995060900265	19950609	00265	CE 	1995	6	9	95ZZZX2693 	1	19950509	G	3230	081300057	FORMER ASSY 			CESSNA	310 	310G 	2074218	CE 										NLG AREA	CRACKED 	G	S			O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			SO	11	2923R					310G0123				THIS AIRCRAFT INVOLVED IN INCIDENT BECAUSE NOSE GEAR WOULD NOT RETRACT, MADE A GEAR UP LANDING. THIS PART FOUND CRACKED	 APPROXIMATELY 3 INCHES IN FRONT OF BELLCRANK 0842104-2. FULL WIDTH EXCEPT LOWER LIP.					1	L	7	2 	3O				3A10 					 
1995060900266	19950609	00266	CE 	1995	6	9	95ZZZX2694 	1	19950508	G	3230	98820241	SPRING 			CESSNA	210 	P210N 	2073454	CE 										NLG DOWNLOCK	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	4556K	1531 				21000218				DURING ANNUAL INSPECTION, OWNER ASKED ABOUT THIS PART BECAUSE HE HAD READ ABOUT IT IN A CESSNA PILOT'S ASSOC NEWSLETTER.	 THE NOSE GEAR DOWNLOCK ASSY MUST BE DISASSEMBLED TO INSPECT THIS PART. GUESS WHAT? BROKEN PART FOUND. CESSNA HAS A 	NEW AND IMPROVED PART TO REPLACE THE PLASTIC ONE. SUBMITTER SUGGESTS THAT ALL RETRACT CESSNAS WITH PLASTIC PART INSTALL	ED BE INSPECTED. INADVERTENT GEAR (NOSE) RETRACTION IS POSSIBLE WITH BROKEN PART.			1	H	7	1 	3O				3A21 					 
1995060900267	19950609	00267	SO 	1995	6	9	95ZZZX2695 	1	19950427	G	2842	68101002	SENDER 			PIPER 	PA28 	PA28181 	7102807	SO 										FLOAT ARM	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	43LC	3075 				287790203				FUEL QUANTITY SENDER UNIT FLOAT SEPARATED FROM ARM RESULTING IN FUEL QUANTITY ERROR TO GAUGE. FLOAT MATERIAL WORN THROU	GH BY SHAFT OF SENDER UNIT ARM.					1	L	7	1 	3O				2A13 					 
1995060900268	19950609	00268	EA 	1995	6	9	95ZZZX2696 	2	19950503	G	7414	ES10382585	CONTACT ASSY 		1068255511 	MOONEY	M20 	M20J 	5870219	SW 	LYC 	O360 	IO360A3B6 	41514	EA 					CAM FOLLOWER	WORN 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	189ER		396 		B6208910C	24169814				MAGNETO WAS REMOVED FROM THE AIRCRAFT AFTER MAGNETO TIMING CHECK INDICATED MAGNETO INTERNAL TIMING WAS OFF BY 10 DEGREES	. MAGNETO DISASSEMBLY INSPECTION REVEALED EXCESSIVE CAM FOLLOWER WEAR. CAM FOLLOWER ALSO APPEARED MELTED. CONTINUED O	PERATION WOULD HAVE CAUSED MAGNETO TO BECOME INOPERATIVE.				1	L	7	1 	3O	3	O		2A3 	1E10				 
1995060900269	19950609	00269	CE 	1995	6	9	95ZZZX2697 	1	19950506	G	3213	05411991	AXLE 			CESSNA	172 	172M 	2072418	CE 										LT MLG	BROKEN 	G	S			O				OTHER 				O			OTHER 			LD	LANDING 	1			GL	23	9347H	2231 				17266105				ON LANDING, LEFT MAIN GEAR AXLE CRACKED. THE OUTER HALF COMPLETELY SEPARATED FROM THE INNER HALF WHICH REMAINED ON THE 	GEAR LEG. THERE WAS NO EVIDENCE OF PREVIOUS CRACKS OR HARD LANDINGS.					1	H	7	1 	3O			NT	3A12 					 
1995060900270	19950609	00270	SO 	1995	6	9	95ZZZX2698 	1	19950519	G	7922	75944	VALVE 			PIPER 	PA32 	PA32R300 	7103213	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			LQZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	38208	1998 			121370	32R7780405				RETAINER NUT WAS NOT CRIMPED PROPERLY AT MANUFACTURE CAUSING NUT TO BECOME LOOSE AND WEAR RAPIDLY. THIS PART WAS VERY C	LOSE TO FAILING AND LYC SB 518B SHOULD BECOME AN AD SO THAT THESE DEFECTIVE VALVES MUST BE LOOKED AT BEFORE SOMEBODY GET	S HURT.				1	L	7	1 	3O				A3SO 					 
1995060900271	19950609	00271	NM 	1995	6	9	95ZZZX2699 	1	19950427	G	7922	53E19600	VALVE 			PIPER 	PA60 	PA60601P 	7106012	NM 										THERMO BYPASS	LOOSE CRIMP NUT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	21D	350 			42862	61P0205018				IN COMPLIANCE WITH TEXTRON-LYCOMING SB 518B, FOUND CRIMP NUT LOOSE WITH SIDE-TO-SIDE LOAD AND WITH TWISTING LOAD. OPERA	TION AND CONDITION OF VALVE WERE NORMAL.					1	M	7	2 	3O			RT	A17WE 					 
1995060900272	19950609	00272		1995	6	9	95ZZZX2700 	1	19950502	G	7922	75944	VALVE 								LYC 	O360 	IO360A1B6 	41514	EA 					THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09					122198					REF LYC SB 518B. TWO OUT OF THREE NUTS HAVE BEEN LOOSE. ONE NUT WAS CRACKED.											3	O			1E10				 
1995060900273	19950609	00273		1995	6	9	95ZZZX2701 	1	19950502	G	7922	75944	VALVE 								LYC 	O360 	IO360A1B6 	41514	EA 					THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09					41150					REF LYC SB 518B. TWO OUT OF THREE NUTS HAVE BEEN LOOSE. ONE NUT WAS CRACKED.											3	O			1E10				 
1995060900274	19950609	00274	SW 	1995	6	9	95ZZZX2702 	1	19950515	G	7922	75944	VALVE 			MOONEY	M20 	M20J 	5870219	SW 										THERMO BYPASS	LOOSE CRIMP NUT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	201SQ	1342 			71750	240298				REMOVED VALVE FOR INSPECTION IAW LYCOMING SB 518C, AND FOUND CRIMP NUT LOOSE. INSTALLED NEW VALVE, PN 53E19600, SN 6416	9, IN ORDER TO RELIEVE FURTHER INSPECTIONS REQUIRED IF VALVE HAD BEEN REWORKED IAW LYCOMING SI 1423. SUBMITTER BELIEVES	 IT IS MORE DESIREABLE TO INSTALL A NEW VALVE THAN TO REWORK A VALVE THAT ALREADY HAS A LOOSE NUT. VALVES THAT ALREADY 	HAVE LOOSE NUTS SHOULD REQUIRE REPLACEMENT, RATHER THAN REWORK. VALVES WITH TIGHT NUTS SHOULD BE REWORKED WITH LOCTITE 	AND RETURNED TO SERVICE IF THE OWNER WOULD RATHER NOT PURCHASE A NEW VALVE.		1	L	7	1 	3O				2A3 					 
1995060900275	19950609	00275	SW 	1995	6	9	95ZZZX2703 	1	19950406	G	7603	1453011	THROTTLE ASSY 			TMPSON	NAVION	NAVION* 	6150130	SW 										CABLE END	CABLE FROZE 	D				O				OTHER 				O			OTHER 			CL	CLIMB 	1			EA	25	4230K	3301 				NAV41230				AFTER TAKEOFF ON SECOND POWER REDUCTION, THROTTLE FROZE. PRIOR TO FLIGHT, ENGINE COMPARTMENT HAD BEEN CLEANED WITH PERM	ATEX BIODEGRADABLE AEROSOL SPRAY. IT TURNED OUT TO HAVE A WATER BASE THAT LEFT DROPLETS ON THE CABLE END THAT FROZE AT 	ALTITUDE. IT THAWNED NEAR THE GROUND. THE SPRAY SHOULD NOT BE USED, ESPECIALLY AFTER CABLES HAVE BEEN LUBRICATED WITH 	LPSI OR WD-40. (SEE MARCH, 1995, ALERTS BULLETIN).			1	L	7	1 	3O				A782 					 
1995060900276	19950609	00276	SO 	1995	6	9	95ZZZX2704 	1	19950501	G	2810		OUTLET TUBE 			PIPER 	PA23 	PA23250 	7102308	SO 										FUEL TANK	STOPPED UP 	B			NW4R	O				OTHER 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			SO	15	13030					274575				LEFT ENGINE QUIT IN-FLIGHT WHILE FUEL SELECTOR WAS ON MAIN FUEL POSITION. INVESTIGATION REVEALED A BIC PEN FIRMLY LODGE	D IN FUEL TANK OUTLET TUBE. FINGER STRAINER WAS BROKEN OFF. SUSPECT THAT SOMEONE DROPPED PEN INTO TANK WHILE DIP-STICK	ING FUEL LEVEL AND NEVER CONSIDERED CONSEQUENCES.				1	L	7	2 	3O				1A10 					 
1995060900277	19950609	00277	SO 	1995	6	9	95ZZZX2705 	1	19950427	G	2820	3734332	TUBE ASSY 			PIPER 	PA34 	PA34200T 	7103406	SO 										FUEL FLOW IND	BROKEN 	B			HF5R	A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			GL	25	39592					347870395				PILOT REPORTED NR 1 ENGINE QUIT IN-FLIGHT AT 10,000 FEET JUST AS THOUGH THE MIXTURE WAS PULLED. ACFT LANDED WITHOUT PRO	BLEM. TROUBLESHOOTING FOUND COPPER TUBE FOR FUEL FLOW/PRESSURE INDICATION BROKEN COMPLETELY JUST BEHIND B-NUT AND SLEEV	E THAT ATTACHES TUBE TO ELBOW FITTING AT FUEL FLOW DIVIDER ON TOP OF ENGINE. THIS, IN TURN, CAUSED LOSS OF PRESSURE TO 	FUEL INJECTION NOZZLES. SUBMITTER RECOMMENDS USING FIRE SLEEVED HOSE OR STAINLESS STEEL LINE. TUBE ASSEMBLY WAS SUPPOR	TED AGAINST VIBRATION, ETC.		1	L	7	2 	3O				A7SO 					 
1995060900278	19950609	00278	SO 	1995	6	9	95ZZZX2706 	1	19950327	G	3246	40120	WHEEL 			PIPER 	PA34 	PA34200T 	7103406	SO 										INBD HALF	FAILED 	D				K				NONE 				O			OTHER 			LD	LANDING 	1			NM	08	9670D					347670214				PILOT REPORTED NOISE SOUNDED LIKE WHEEL BEARING WAS FAILING ON LANDING. UPON INVESTIGATION OF PROBLEM, FOUND INBOARD WH	EEL HALF HAD FAILED. A 4 INCH PART OF WHEEL HAD BROKEN AWAY FROM WHEEL AND WAS HITTING BRAKE CALIPER.					1	L	7	2 	3O				A7SO 					 
1995060900279	19950609	00279	CE 	1995	6	9	95ZZZX2707 	1	19950501	G	5531		SPAR 			CESSNA	182 	182E 	2072712	CE 										RT ELEV	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	9033Y					18254212				AT ANNUAL INSPECTION, FOUND RT ELEVATOR SPAR CRACKED WITH ONE INCH CRACK RADIATING AWAY FROM RIVET HOLE AT OUTBOARD HING	E ATTACH. POSSIBLE TAIL SECTION IMPACT WITH T-HANGAR MAY BE A CONTRIBUTING FACTOR. REPLACED ELEVATOR SPAR.					1	H	7	1 	3O			NT	3A13 					 
1995060900280	19950609	00280	CE 	1995	6	9	95ZZZX2708 	1	19950518	G	5711	51220418	SPAR CAP 			CESSNA	310 	310Q 	2074242	CE 										WING	CORRODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	7891Q	7000 				310QC0660				CORROSION OF RIGHT LOWER AFT SPAR CAP ASSY. EXTENT OF CORROSION WAS PAST ALLOWABLE REPAIR LIMITS SET FORTH BY CESSNA A/	C CO. THE SPAR IS LOCATED DIRECTLY BEHIND THE EXHAUST AUGMENTORS AND IS BEING CORRODED BY THE EXHAUST EMISSIONS. PERIO	DIC CLEANING OF THE FLAP WELL AREA AND CORROSION TREATMENT IS RECOMMENDED. SPAR CAP ASSY WAS REPLACED WITH A NEW UNIT F	ROM CESSNA.			1	L	7	2 	3O				3A10 					 
1995060900281	19950609	00281	CE 	1995	6	9	95ZZZX2709 	1	19950510	G	5312	0024400245	BULKHEAD 			BEECH 	33 	F33A 	1151425	CE 										FUSELAGE AFT	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8268T					CE1547				FOUND DURING PROGRESSIVE INSPECTION AT ATCA. THE UPPER LEFT CORNER OF THE AFT BULKHEAD CRACKED APPROXIMATELY 1 INCH ALO	NG BULKHEAD BEND. ALSO, TWO CORNER CRACKS IN THE UPPER DOUBLER AT AFT BULKHEAD.					1	L	7	1 	3O				3A15 					 
1995060900282	19950609	00282	SO 	1995	6	9	95ZZZX2710 	2	19950406	G	8530		PISTON 								CONT 	O520 	TSIO520E 	17040	SO 					NR 2 CYLINDER	BURNED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01		810 					275313R			FOUND CYLINDER NR 2 TOP SIDE PISTON BURNED, POSSIBLE DETONATION. SENT FOR EVALUATION AT TCM.											3	O			E8CE				 
1995060900283	19950609	00283	EA 	1995	6	9	95ZZZX2711 	2	19950406	G	7322		CARBURETOR 	FACET 		PIPER 	PA28 	PA28180 	7102808	SO 	LYC 	O360 	O360A3A 	41514	EA 					VENTURI	FOD 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			NE	01	9362J	3233 	1000 			283461	L987336A			OWNER REPORTS THAT ENGINE NOT GOING TO NORMAL RPM AT FULL THROTTLE. FOUND FUEL/AIR MIXTURE TO BE RICH, AFTER REMOVING C	ARBURETOR AIR BOX FOUND PIECE OF STYROFOAM PACKING SIZE OF A DIME LODGED BETWEEN VENTURI AND MAIN FUEL METERING TUBE. R	EMOVED FOD AND OPS CHECK NORMAL.				1	L	7	1 	3O	3	O		2A13 	E286				 
1995060900284	19950609	00284	EA 	1995	6	9	95ZZZX2712 	2	19950303	G	8530	69603	HOSE 			CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					INTAKE COUPLING	DEFECTIVE 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			GL	13	9526H					17266201	L4349627A			UPON INVESTIGATION OF LOWER THAN NORMAL POWER OUTPUT, FOUND INTAKE COUPLING HOSE INTERIOR (ALL 4) INTERNALLY REDUCING IN	 SIZE FROM 1.75 INCHES TO 1.25 INCHES. THIS IS A SUBSTANTIAL REDUCTION IN FLOW (NEARLY ONE-HALF VOLUME) FROM 3.06 SQUAR	E INCH TO 1.56 SQUARE INCH. THE COUPLINGS APPEAR TO HAVE SUFFERED FROM HEAT DUE TO PROXIMITY OF HOT EXHAUST. POWER RES	UMED NORMAL UPON REPLACEMENT OF NEW COUPLINGS.			1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995060900285	19950609	00285	CE 	1995	6	9	95ZZZX2713 	1	19950303	G	8011	EBB75A	BENDIX DRIVE 	PRESTOLITE 	MZ4222 	CESSNA	172 	172L 	2072432	CE 	LYC 	O320 	O320E2D 	41508	EA 					STARTER	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	7809G					17259559				THE STARTER MOTOR TURNS, BUT THE BENDIX WILL NOT ENGAGE. POSSIBLE FAULTS: 1. WORN. 2. WRONG LUBRICANT - NOT SILICON	E AS RECOMMENDED. 3. DIRT/OIL PREVENTING 'SLIDING' AS REQUIRED.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995060900286	19950609	00286	SO 	1995	6	9	95ZZZX2714 	2	19950303	G	8530	24047	VALVE GUIDE 			CESSNA	150 	150M 	2071830	CE 	CONT 	O200 	O200A 	17020	SO 					EXHAUST	FAILED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	13	714AJ		1005 			15079024	255534A48			ENGINE MAJOR OVERHAULED WITH CYLINDERS SUPPLIED BY AERO AVIATION. CYLINDERS WENT 100 HOURS AND VALVE GUIDES FAILED DUE 	TO IMPROPER INSTALLATION. THEY WERE INSTALLED SO LOOSE THAT FIRE WAS EATING AWAY AT THE OUTSIDE OF THE GUIDE WHERE IT I	S SUPPOSED TO BE A PRESS FIT IN THE CYLINDER HEAD. SN 41593, SN 41591, SN 41595 HAD GUIDES INSTALLED BY A BETTER CYLIND	ER HOUSE, THE ENGINE NOW HAS 450 HOURS SMOH, AND RUNS JUST FINE.			1	H	7	1 	3O	3	O		3A19 	E252				 
1995060900287	19950609	00287	SO 	1995	6	9	95ZZZX2715 	2	19950303	G	8550	1250922202	ADAPTER 			CESSNA	182 	182E 	2072712	CE 	CONT 	O470 	O470* 	17026	SO 					OIL FILTER	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	9390X					18253790				WHEN INSPECTING FILTER ADAPTER IAW SEB 93-1R1A, FOUND FRETTING OF THE MOUNTING THREADS. THIS RENDERED THE ADAPTER UNAIR	WORTHY. ADAPTER REPLACED WITH NEW UNIT.					1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995060900288	19950609	00288	SO 	1995	6	9	95ZZZX2716 	1	19950303	G	2820	55031	SOLENOID VALVE 	BRITTAIN 		PIPER 	PA30 	PA30 	7103002	SO 										TIP TANK	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	13	8296Y	8000 				301435				BRITTAIN WING TIP TANKS WERE A PIPER FACTORY OPTION WHEN THIS PLANE WAS NEW. THE O-RING IS INTEGRATED WITH A WASHER, SO	 IT IS SPECIAL. IT IS NOT POSSIBLE TO GET NEW PARTS, SO THE WHOLE SOLENOID WAS REPLACED BY A STC'D FUEL VALVE.					1	L	7	2 	3O				A1EA 					 
1995060900289	19950609	00289	CE 	1995	6	9	95ZZZX2717 	1	19950426	G	7160	075201610	SEAL 			CESSNA	182 	182K 	2072724	CE 										CARB AIR BOX	DETERIORATED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	3088Q	300 				18258088				FOUND SEALS DETERIORATED. AD 77-4-5 APPLIES TO THIS PROBLEM UNLIKE BRACKETT AD 95-3-2 WHICH IS RECURRING.						1	H	7	1 	3O			NT	3A13 					 
1995060900290	19950609	00290	CE 	1995	6	9	95ZZZX2718 	1	19950426	G	7160	075201611	SEAL 			CESSNA	182 	182K 	2072724	CE 										CARB AIR BOX	DETERIORATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	3088Q	300 				18258088				FOUND SEALS DETERIORATED. AD 77-4-5 APPLIES TO THIS PROBLEM UNLIKE BRACKETT AD 95-3-2 WHICH IS RECURRING.						1	H	7	1 	3O			NT	3A13 					 
1995060900291	19950609	00291	EA 	1995	6	9	95ZZZX2719 	2	19950411	G	7414	10682014	DISTRIBUTOR GEAR	BENDIX 	ES1038255514	CESSNA	172 	172 	2072402	CE 	LYC 	O320 	O320H2AD 	41508	EA 					MAG	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4669G		304 		3111753	17273295	L707476			ON TWO OCCASIONS, THE LARGE DISRIBUTOR GEAR HAS SHED GEAR TEETH DURING NORMAL OPERATIONS. THE FIRST SET OF GEARS SHED 1	1 TEETH AND THE SECOND SET SHED 2 TEETH. THE FIRST SET HAD 500 HOURS SINCE OVERHAUL AND THE SECOND SET HAD 303.5 HOURS 	SINCE OVERHAUL. INDICATIONS PRIOR TO INSPECTION WAS ENGINE MISSING, ESPECIALLY WHEN POWER REDUCED. SUSPECT QUALITY CON	TROL PROBLEM, BUT CANNOT RULE OUT MANUFACTURE DEFECT. PARTS AVAILABLE FOR INSPECTION.			1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995060900292	19950609	00292	SO 	1995	6	9	95ZZZX2720 	2	19950407	G	8530		CYLINDER 			CESSNA	340 	340A 	2076405	CE 	CONT 	O520 	TSIO520N 	17040	SO 					ENGINE	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	300JM	3527 	432 			340A0233	509401			AT OVERHAUL, 5 CYLINDERS WERE CERAMICHROME AND 1 WAS CHANNELCHROME. AT THE 100-HOUR INSPECTION. COMPRESSION WAS HIGH 60	'S ON THE CERAMICHROME, 77 ON THE CHANNELCHROME. A PRE-BUY INSPECTION WAS DONE 2 HOURS LATER AND THE COMPRESSION DROPPE	D 20 POUNDS ON THE CERAMICHROME. THIS PROBLEM IS CONSISTENT ON CERAMICHROME CYLINDERS.				1	L	7	2 	3O	3	O		3A25 	E8CE				 
1995060900293	19950609	00293	CE 	1995	6	9	95ZZZX2721 	1	19950503	G	3233	AN3167R	JAM NUT 			CESSNA	177 	177RG 	2073709	CE 										MLG ACTUATOR	LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	2072Q					177RG0472				WHILE PERFORMING GEAR SWING, FOUND MAIN GEAR ACTUATOR JAM NUT LOOSE. THIS IS THE 2ND CARDINAL RG FOUND THIS WAY. FIRST	 CARDINAL, THE ROD END HAD ROTATED OUT OF PISTON ENOUGH TO CAUSE GEAR NOT TO LOCK DOWN. THERE IS NO SAFETY ON JAM NUT T	O PREVENT BACKING OFF OF ROD. SUBMITTER RECOMMENDS CHECKING JAM NUT WHENEVER ACTUATOR IS ACCESSIBLE.				1	H	7	1 	3O				A20CE 					 
1995060900294	19950609	00294	CE 	1995	6	9	95ZZZX2722 	1	19950501	G	7160	07501337	FLAPPER VALVE 			CESSNA	182 	182K 	2072724	CE 										CARB AIR BOX	SEAL DETERIORATE	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	3088Q	4700 				18258088				FOUND FLAPPER (CARBURETOR HEAT) IN AIR BOX ASSEMBLY RUBBER BAFFLE ON EDGES COMING OFF.						1	H	7	1 	3O			NT	3A13 					 
1995060900295	19950609	00295	CE 	1995	6	9	95ZZZX2723 	1	19950316	G	7602	5038901229	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										MIXTURE CONTROL	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	18447	238 				TH883				LEFT MIXTURE CONTROL CABLE WAS FOUND BROKEN AT THREADED END AT ENGINE SHUT DOWN. SUBMITTER STATED THIS IS A CONTINUING	 PROBLEM. BEECHCRAFT HAS BEEN NOTIFIED OF PROBLEM.					1	L	7	2 	3O			 	3A16 					 
1995060900407	19950609	00407	EA 	1995	6	9	95ZZZX2724 	2	19950523	G	7414	4371	MAGNETO 	SLICK 		CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320D2G 	41508	EA 					BATTERY BOX	CHAFED 	B			SL5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	4599D	6 			95020211	17272311	L1724239A			DURING TROUBLESHOOTING OF ELECTRICAL SYSTEM, FOUND LEFT MAGNETO HARNESS CAP CHAFING AIRCRAFT BATTERY. BATTERY COULD NOT	 BE REMOVED WITHOUT ROTATING MAGNETO OUT OF THE WAY. REMOVED MAGNETO AND ROTATED DRIVE GEAR TO IMPULSE COUPLING 180 DEG	REES. REINSTALLED AND TIMED MAGNETO. REINSTALLED HARNESS CAP AND TRIMMED BATTERY BOX INSULATOR FOR APPROXIMATELY .25 I	NCH CLEARANCE BETWEEN MAGNETO AND BATTERY. IT APPEARS THAT WHENEVER BATTERY REQUIRES REMOVAL, THE MAGNETO TIMING MUST B	E DISTURBED. WHOEVER INSTALLED THE ENGINE SHOULD HAVE NOTICED THIS CHAFE IMMEDIATELY.		1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995060900408	19950609	00408	EA 	1995	6	9	95ZZZX2725 	2	19950518	G	8530		RETAIN STUD 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					NR 4 CYL ROCKER	BACKED OUT 	D				A				UNSCHED LANDING 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	CR	CRUISE 	1			NE	03	734XC	1100 				17269188	RL00595576T			AFTER APPROXIMATELY 5 MINUTES IN CRUISE FLIGHT, THE PILOT REPORT A LOSS OF ENGINE POWER AND A SEVERE ROUGHNESS AND AN AI	RPORT LANDING WAS MADE WITHOUT INCIDENT. INVESTIGATION REVEALED NR 4 CYLINDER INTAKE VALVE PUSH ROD AND SHROUD WERE BUR	NED AND LEAKING OIL. THE EXHAUST VALVE RETAIN STUD FOR THE FULCRUM AND ROCKER ARM HAD BACKED OUT APPROXIMATELY 5 THREAD	S; THUS, CREATING EXCESSIVE VALVE CLEARANCE. THE OTHER 3 CYLINDERS WERE INSPECTED AND THIS CONDITION OF THE ROCKER ASSY	 RETAIN STUD ALSO EXSISTED ON NR 2 CYLINDER.		1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995060900409	19950609	00409	SO 	1995	6	9	95ZZZX2726 	1	19950424	G	8120	LW18459	BRACKET 			PIPER 	PA31 	PA31350 	7103110	SO 										TURBO SUPPORT	BROKEN 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	27343		1796 			317752163				TURBO SUPORT ROD BRACKET BROKEN INTO TWO PIECES.						1	L	7	2 	3O				A20SO 					 
1995060900410	19950609	00410	EA 	1995	6	9	95ZZZX2727 	2	19950517	G	8530	AL19001	VALVE 								LYC 	O320 	O320D3G 	41508	EA 					EXHAUST	WORN 	B			CYKR	K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			GL	07		336 					L851039A			ENGINE RAN ROUGH AT IDLE AND LOUD MECHANICAL NOISES WERE REPORTED. VISUAL INSPECTION OF ENGINE BEFORE DISASSEMBLY SHOWE	D ZERO VALVE STEM TO ROCKER CLEARANCE. DISASSEMBLY OF CYLINDER SHOWED EXHAUST VALVE PN AL19001 WORN EXCESSIVELY IN THE 	RETAINER GROOVE. RECOMMEND REPLACEMENT OF EXHAUST VALVE.									3	O			E274				 
1995060900411	19950609	00411	EA 	1995	6	9	95ZZZX2728 	2	19950517	G	8530	AL19001	VALVE 								LYC 	O320 	O320E2D 	41508	EA 					EXHAUST	WORN 	B			CYKR	K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			GL	07		296 					L3354027A			ENGINE RAN ROUGH AT IDLE AND LOUD MECHANICAL NOISES WERE REPORTED. VISUAL INSPECTION OF ENGINE BEFORE DISASSEMBLY SHOWE	D ZERO VALVE STEM TO ROCKER CLEARANCE. DISASSEMBLY OF CYLINDER SHOWED EXHAUST VALVE PN AL19001 WORN EXCESSIVELY IN THE 	RETAINER GROOVE. RECOMMEND REPLACEMENT OF EXHAUST VALVE.									3	O			E274				 
1995060900412	19950609	00412	SO 	1995	6	9	95ZZZX2729 	2	19950530	G	8550	0024100143	PAN 			BEECH 	36 	A36 	1151604	CE 	CONT 	O520 	TSIO520UB 	17040	SO 					ENGINE	CRACKED 	B			HBKR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	11	8285C	268 				E2810				HOLE HAD BROKEN OUT IN CENTER OF PAN. PAN IS FORMED FROM .032. NOTIFIED BEECH OF PROBLEM. INSTALLED A NEW PART. BEEC	H INDICATED THEY MAY USE .061 MATERIAL SOMETIME IN THE FUTURE.					1	L	7	1 	3O	3	O		3A15 	E8CE				 
1995060900413	19950609	00413	SO 	1995	6	9	95ZZZX2730 	1	19950519	G	3232	756265	SPRING 	OZONE 	455946 	PIPER 	PA31 	PA31 	7103102	SO 										DOOR ACTUATOR	BROKEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	83RA	100 				31638				AIRCRAFT OPERATOR REPORTED A GEAR DOOR COULD POSSIBLY BE OPEN. TROUBLESHOOTING PROCEDURES IN MM FOLLOWED, BUT NO FAULT 	FOUND. GEAR WAS RETRACTED WITH MANUAL PUMP AND RT DOOR OPENED. TROUBLE WAS DETERMINED TO BE IN THE DOOR ACTUATOR. WHE	N IT WAS DISASSEMBLED, THE LOCK SPRING WAS IN 5 PIECES. THIS ACTUATOR HAD THE SEALS, SPRING, AND LOCKING BALLS REPLACED	 APPROXIMATELY 100 HOURS PRIOR. SPRING AND SEALS REPLACED, AND ADJUSTMENTS MADE. AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	3O				A20SO 					 
1995060900414	19950609	00414	SO 	1995	6	9	95ZZZX2731 	1	19950517	G	7922		VALVE 			PIPER 	PA23 	PA23250 	7102308	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			SJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	714MD					277550484				PART NAME THERMOSTATIC BYPASS VALVE. NUT LOOSE INSPECTED PER LYC SB 0A-518C, PN 75944, SN 41966. ENGINE TT, 2895.0. E	NGINE TT SMOH 1019.0 HRS. LEFT ENGINE.					1	L	7	2 	3O				1A10 					 
1995060900415	19950609	00415	SO 	1995	6	9	95ZZZX2732 	1	19950517	G	7922		VALVE 			PIPER 	PA23 	PA23250 	7102308	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			SJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	714MD					277554084				PART NAME THERMOSTATIC BYPASS VALVE. NUT LOOSE INSPECTED PER LYC SB OA-518C, PN 75944, SN 36700. ENG TT 2895.0. ENG T	T SMOH, 1019.0 HRS. RIGHT ENGINE.					1	L	7	2 	3O				1A10 					 
1995060900416	19950609	00416	EA 	1995	6	9	95ZZZX2733 	2	19950524	G	7414	M3975	COIL 	SLICK 	4330 	PIPER 	PA34 	PA34200 	7103405	SO 	LYC 	O360 	IO360C1E6 	41514	EA 					MAG IGNITION	BURNED 	B			LJ2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	55295	250 			93030004	3473350197				ENGINE FAILED TO START. PROBLEM TRACED TO A BURNED THROUGH IGNITION COIL ON THE LT MAGNETO. COIL WAS BURNED THROUGH AT	 THE FRONT OF COIL (WHERE PN IS PRINTED) AND WAS ARCING TO THE MAGNETO CASE. MAGNETO IS ONLY 2 YEARS OLD AND ONLY HAS 2	50 HOURS TIME IN SERVICE SINCE NEW MANUFACTURE.				1	L	7	2 	3O	3	O		A7SO 	1E10				 
1995060900417	19950609	00417	EA 	1995	6	9	95ZZZX2734 	2	19950418	G	8530		CYLINDER 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					NR 4	FAILED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			NE	03	8115H		800 			288016117	L941139A			PILOT DECLARED AN EMERGENCY SHORTLY AFTER TAKEOFF DUE TO ROUGH RUNNING ENGINE. FOUND NR 4 CYLINDER HAD .50 INCH DIAMETE	R PIECE OF ALUMINUM BURNED OUT NEAR EXHAUST VALVE SEAT. POSSIBLY CAUSED BY PRE-IGNITION OR DETONATION. APPROXIMATELY 3	00 HOURS PRIOR, ENGINE WAS CRACKING THE PORECELAIN IN THE SPARK PLUGS. MOST LIKELY HAPPENED DUE TO IMPROPER LEANING.				1	L	7	1 	3O	3	O		2A13 	E274				 
1995060900418	19950609	00418	CE 	1995	6	9	95ZZZX2735 	1	19950523	G	3260		WIRE 			CESSNA	172 	172RG 	2072438	CE 										NLG UP SWITCH	BROKEN 	D				O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			EA	25	9746B					172RG1009				UPON SELECTING GEAR DOWN, DOWN AND LOCKED LIGHT WOULD NOT ILLUMINATE WITH GEAR DOWN. PILOT DECLARED AN EMERGENCY AND LA	NDED UNEVENTFULLY. UPON INSPECTION, A WIRE AT NOSE GEAR UP INDICATION SWITCH WAS FOUND BROKEN. REPAIRED WIRE. PERFORM	ED RETRACTION TEST. OPS CHECKED GOOD. RECOMMENDATION - TY-WRAP BUNDLE CLEAR OF SHIMMY DAMPENER UPON RETRACTION.				1	H	7	1 	3O				3A17 					 
1995060900419	19950609	00419	EA 	1995	6	9	95ZZZX2736 	2	19950511	G	8550	61837	VALVE SLEEVE 			PIPER 	PA28 	PA28180 	7102808	SO 	LYC 	O360 	O360A3A 	41514	EA 					PRESS RELIEF VLV	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	7851W	4402 				281870	L726636A			FOUND LARGE ALUMINUM PARTS IN SUCTION SCREEN. THEY APPEARED BROKEN AND UNMARRED, I,E,; HAD NOT BEEN GROUND UP IN A GEAR	 TRAIN. FURTHER INVESTIGATION USING LYCOMING OVERHAUL MANUAL NR 60294-7, PAGE 7-2, IDENTIFIED POSS END ITEM, DISASSEMBL	ED OIL PSI RELIEF VALVE PLUG AND FOUND SLEEVE (IT-16) MISSING 2 SIDES. UPON REMOVAL OF SLEEVE, WAS ABLE TO REASSEMBLY E	NTIRE ITEM WITH PARTS FOUND IN SUCTION SCREEN. INSTALLED NEW ASSY AND RETURNED ENGINE TO SERVICE.			1	L	7	1 	3O	3	O		2A13 	E286				 
1995060900420	19950609	00420	SO 	1995	6	9	95ZZZX2737 	1	19950420	G	2810	2047F2	TANK 			MAULE 	MX7 	MXT7180 	5470206	SO 										RT MAIN INBD	LEAK 	D	L	A		K				NONE 				W	K		INADEQUATE Q C 	FLUID LOSS 		IN	INSP/MAINT 	1			EA	07	2810	492 				14058C				RIGHT MAIN FUEL TANK WAS LEAKING AT FRONT MIDDLE SEAM AREA. UPON REMOVAL OF FUEL TANK IT APPEARS THAT THE ENTIRE LEADIN	G EDGE OF FUEL TANK WAS BEAT WITH A HAMMER. TANK WAS SENT BACK TO FACTORY FOR EVALUATION AND POSSIBLE WARRANTY. TANK W	AS CONDEMNED.				1	H	7	1 	3O			NC	3A23 					 
1995060900421	19950609	00421	WP 	1995	6	9	95ZZZX2738 	1	19950330	G	2810		TANK 			DOUG 	DC3 	DC3G102A 	3021404	WP 										AUX FUEL	OUTLET PLUGGED 	D	L	A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	08	13JA					4082				FUEL STOPPED FLOWING FROM METAL AUX FUEL TANK. NUMEROUS PIECES OF WHITE PAINT-LIKE MATERIAL FOUND IN TANK; SOME 5-6 SQU	ARE INCHES. IDENTIFIED AS RANDOLPH 912 SLOSHING COMPOUND (NOT FAA APPROVED FOR AC FUEL TANKS). TWO 1-GAL CANS OF RANDO	LPH 802 ALSO FOUND ON STOCKROOM SHELF (802 IS ALSO NOT FAA APPROVED). AC HAD, 2 YRS EARLIER, ENGINE FAILURE FOR UNDETE	RMINED CAUSES. SUBMITTER RECOMMENDS AVIATION COMMUNITY BE REMINDED THESE UNAPPROVED MATERIALS ARE STILL ON THE SHELVES,	 AND AVAILABLE FOR PURCHASE. ALL TANKS IN WHICH ANY UNAPPROVED COMPOUND HAS BEEN USED SHOULD BE THOROUGHLY CHECKED FOR 	CONTAMINATION.	2	L	7	2 	4R				A618 					 
1995060900422	19950609	00422	CE 	1995	6	9	95ZZZX2739 	1	19950421	G	3260		GEAR WARN 			BEECH 	36 	A36 	1151604	CE 										MLG	MALFUNCTION 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			GL	03	4597S					E757				AIRCRAFT STARTED TO LAND UNTIL PROP, FLAPS, AND STEP CONTACTED RUNWAY. A GO AROUND WAS INITIATED, LANDING GEAR WAS SELE	CTED DOWN AND A NORMAL LANDING WAS MADE. PILOT STATED HE DID NOT HEAR A GEAR WARNING HORN. AFTER AIRCRAFT WAS FERRIED 	HOME, GEAR SYSTEM CHECKED NORMAL. TEST FLIGHT AFTER AIRCRAFT REPAIR WAS NORMAL, GEAR WARNING HORN SOUNDED AT 13 INCHES 	TO 15 INCHES MAP. RETURNED AIRCRAFT TO SERVICE.			1	L	7	1 	3O				3A15 					 
1995060900423	19950609	00423	SW 	1995	6	9	95ZZZX2740 	1	19950501	G	2731	NAS464310	BOLT 			GULSTM	112 	114 	7630314	SW 										ELEV TRIM TAB	MISINSTALLED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	03	114KS					14392				DURING ANNUAL INSPECTION, TRIM TAB ACTUATOR-TO-ROD BOLT WAS FOUND INSTALLED BACKWARDS CAUSING END OF THE BOLT TO SHEAR O	FF. THIS COULD HAVE CAUSED LOSS OF CONTROL, ELEVATOR FLUTTER, AND SUBSEQUENT LOSS OF ELEVATOR. THIS IS AN EXREMELY HAR	D BOLT TO GET IN PROPERLY AS THE BOLT HEAD IS AN INTERFRENCE FIT WITH THE HINGE BRACKET AND MIGHT CAUSE SOME CONFUSION A	S TO WHICH WAY IT GOES, HOWEVER, IF INSTALLED BACKWARDS, THE NUT/BOLT END CONTACTS THE ELEVATOR FORWARD SPAR ALLOWING TR	AVEL NOT EVEN TO NEUTRAL POSITION.		1	L	7	1 	3O				A12SO 					 
1995060900424	19950609	00424		1995	6	9	95ZZZX2741 	4	19950410	G	2211	CE2150H16FF22	COMPUTER 	CENTURY 	C2000 	MOONEY	M20 	M20J 	5870219	SW 										AUTOPILOT	MALFUNCTION 	B			JW5R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	13	210WE				2K0545	243352				AUTOPILOT CLIMBS IN ALTITUDE HOLD WHEN TRANSMITTING ON EITHER COM'S ON LOWER FREQUENCY BAND. FACTORY IS STILL WORKING O	N THE PROBLEM.					1	L	7	1 	3O				2A3 					 
1995060900425	19950609	00425	EA 	1995	6	9	95ZZZX2742 	1	19950510	G	3240	JONESNO97	RETURN SPRING 			WACO 	UPF7 	UPF7 	9601302	EA 										LT BRAKE	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	20971					5317				DURING INSPECTION FOR DAMAGE AFTER A NOSE-OVER ACCIDENT, THE LEFT BRAKE MASTER CYLINDER RETURN SPRING (5.5 INCHES LONG) 	WAS FOUND MISSING. IT WAS FOUND IN THE BELLY WITH A HOOK END MISSING. WITHOUT THIS RETURN SPRING, THE BRAKE WILL NOT R	ELEASE. ACCORDING TO THE WACO ASSOC., THIS HAS HAPPENED BEFORE. HISTORY OF THE PART IN THE 55 YEAR OLD VINTAGE AIRPLAN	E COULD NOT BE DETERMINED.			1	Q	7	1 	3R				A642 					 
1995060900426	19950609	00426	EA 	1995	6	9	95ZZZX2743 	1	19950522	G	2740	15173	JACKSCREW 			WACO 	YMF 	YMF 	9600412	EA 										STAB TRIM	JAMMED 	G		A		O				OTHER 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			GL	15	820MM	253 				F5C056				HORIZONTAL STABILIZER TRIM JAMMED IN-FLIGHT. AFTER LANDING, TRIM WAS INSPECTED. TRIM JACKSCREW WAS JAMMED IN THE BALL 	(PN 9159). REASON FOR THIS COULD NOT BE DETERMINED. JACKSCREW WAS LUBRICATED AND FUCNTIONALLY CHECKED.					1	Q	7	1 	3R				ATC542 					 
1995060900427	19950609	00427	GL 	1995	6	9	95ZZZX2744 	3	19950501	G	6114		PROPELLER 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	MOUNT HOLE	CRACKED 	B		A	PAWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	65423	3318 				1528I1544		CF075		DURING 100-HOUR INSPECTION, FOUND PROPELLER CRACKED AT MOUNTING BOLT HOLE. CRACK IS 2.50 INCHES LONG AND ON EITHER SIDE	 OF MOUNTING HOLE. MCCAULEY SB 169C COMPLETED JUNE 4, 1990. PROPELLER REPLACED WITH SERVICEABLE UNIT.					1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995060900429	19950609	00429	CE 	1995	6	9	95ZZZX2746 	1	19950509	G	2810	42621	CELL 			CESSNA	310 	310P 	2074238	CE 										AUX FUEL	LEAK 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	17	5811M					310P0111				DURING AIRCRAFT REFUELING LINE SERVICE PERSONNEL NOTIFIED THE MAINTENANCE DEPARTMENT THAT FUEL WAS LEAKING FROM THE LEFT	 AUX TANK AREA. AUX TANK WAS DEFUELED. UPON REMOVING THE FUEL CELL, IT WAS NOTED THE CELL HAD COMPLETELY SEPARATED FRO	M THE FILLER NECK. THE VENT NIPPLES BROKE OFF UPON REMOVAL OF THE CLAMPS. THE FUEL SCREEN WAS CHECKED FOR CONTAMINATIO	N (NONE FOUND) AND THE FUEL CELL WAS REPLACED WITH A NEW UNIT.			1	L	7	2 	3O				3A10 					 
1995060900430	19950609	00430	EU 	1995	6	9	95ZZZX2747 	1	19950307	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117C1 		EU 										T/R	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	393 				7505				WORN BEARING (2 EACH) IN TAIL ROTOR. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995060900431	19950609	00431		1995	6	9	95ZZZX2748 	4	19950325	G	3120	JB15307	CLOCK 			BOLKMS	117 	BK117C1 		EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	429 			7921	7505				STALLS OCCASIONALLY, DIFFICULT TO ADJUST. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995060900432	19950609	00432	EU 	1995	6	9	95ZZZX2749 	1	19950331	G	2810	1176415501	SEAL 			BOLKMS	117 	BK117C1 		EU 										FUEL CELL	O-RING LOOSE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	433 				7505				O-RING COMING UNGLUED FROM RING. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995060900433	19950609	00433		1995	6	9	95ZZZX2750 	4	19950406	G	2210	67A338	ROTARY ACTUATOR 			BELL 	222 	222 	1182122	SW 										AUTOFLT	MALFUNCTION 	B			TI1R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	05	911LW				223	47520				ACTUATOR CLUTCH RELEASE WHEN PRESSURE APPLIED WITHOUT HITTING 'FORCE TRIM RELEASE' BUTTON. REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995060900434	19950609	00434	SW 	1995	6	9	95ZZZX2751 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1084Y	446 				45433				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 445.8 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900435	19950609	00435	SW 	1995	6	9	95ZZZX2752 	1	19950522	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1084Y	446 				45433				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 445.8 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900436	19950609	00436	SW 	1995	6	9	95ZZZX2753 	1	19950522	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1081G		383 			45405				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 382.5 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900437	19950609	00437	SW 	1995	6	9	95ZZZX2754 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1081G		383 			45405				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 382.5 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900438	19950609	00438	SW 	1995	6	9	95ZZZX2755 	1	19950510	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	115AL		555 			2383				DAILY REPAIR, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPAC	ERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-101 	BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 554.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900439	19950609	00439	SW 	1995	6	9	95ZZZX2756 	1	19950510	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	115AL		555 			2383				DAILY REPAIR, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPAC	ERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-101 	BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 554.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900440	19950609	00440	SW 	1995	6	9	95ZZZX2757 	1	19950510	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A		475 			45256				DURING REPAIR, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-101	 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 475.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900441	19950609	00441	SW 	1995	6	9	95ZZZX2758 	1	19950510	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A				475	45256				DURING REPAIR, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-101	 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 475.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900442	19950609	00442	SW 	1995	6	9	95ZZZX2759 	1	19950510	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D		425 			45280				DURING REPAIR, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-101	 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 425.3 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900443	19950609	00443	SW 	1995	6	9	95ZZZX2760 	1	19950510	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D		425 			45280				DURING REPAIR, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-101	 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 425.3 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900444	19950609	00444	SW 	1995	6	9	95ZZZX2761 	1	19950510	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3185P		326 			45775				DURING REPAIR, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-101	 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 326.3 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900445	19950609	00445	SW 	1995	6	9	95ZZZX2762 	1	19950510	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3185P		326 			45775				DURING REPAIR, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-101	 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 326.3 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900446	19950609	00446	SW 	1995	6	9	95ZZZX2763 	1	19950522	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	344AL		222 			51374				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 221.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900447	19950609	00447	SW 	1995	6	9	95ZZZX2764 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	344AL		222 			51374				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 221.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900448	19950609	00448	SW 	1995	6	9	95ZZZX2765 	1	19950522	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3179S		615 			45781				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 615.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900449	19950609	00449	SW 	1995	6	9	95ZZZX2766 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3179S		615 			45781				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 615.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900450	19950609	00450	SW 	1995	6	9	95ZZZX2767 	1	19950522	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL		762 			51460				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 761.6 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900451	19950609	00451	SW 	1995	6	9	95ZZZX2768 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL		762 			51460				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 761.6 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900452	19950609	00452	SW 	1995	6	9	95ZZZX2769 	1	19950522	G	6230	206010335001	LINK ASSY 			BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	346AL		544 			51378				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 544.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900453	19950609	00453	SW 	1995	6	9	95ZZZX2770 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	346AL		544 			51378				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 544.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900454	19950609	00454	SW 	1995	6	9	95ZZZX2771 	1	19950522	G	6320	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	362AL		425 			51471				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 424.6 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900455	19950609	00455	SW 	1995	6	9	95ZZZX2772 	1	19950522	G	6320	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	362AL		425 			51471				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 424.6 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900456	19950609	00456	SW 	1995	6	9	95ZZZX2773 	1	19950522	G	6230	206010335001	LINK ASSY 			BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	363AL		255 			51472				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 255.4 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900457	19950609	00457	SW 	1995	6	9	95ZZZX2774 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	363AL		255 			51472				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 255.4 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900458	19950609	00458	SW 	1995	6	9	95ZZZX2775 	1	19950510	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	366AL		522 			51470				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 522.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900459	19950609	00459	SW 	1995	6	9	95ZZZX2776 	1	19950510	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	366AL		522 			51470				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 522.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900460	19950609	00460	SW 	1995	6	9	95ZZZX2777 	1	19950522	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5829D		534 			45270				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 534.5 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900461	19950609	00461	SW 	1995	6	9	95ZZZX2778 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5829D		534 			45270				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 534.5 HOURS.				1	G	7	1 	3U				H2SW 					 
1995060900614	19950609	00614	EU 	1995	6	9	95ZZZX2779 	1	19950511	G	6720	10531821	PC LINK 			BOLKMS	105 	BO105S 	5626006	EU 										T/R	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	107AL		50 			S772				DURING PMI INSPECTION (50-HOUR INSPECTION) FOUND T/R PC LINK CORRODED. LINK SCRAPPED DUE TO CORROSION AT BEARING HOLE.						1	G	7	2 	3U				H3EU 					 
1995060900615	19950609	00615	SW 	1995	6	9	95ZZZX2780 	1	19950509	G	5312	206032400027	BULKHEAD 			BELL 	206 	206L1 	1182107	SW 										TAILBOOM RING	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1078N	12184				45389				AFTER REMOVAL OF SHIMS IN ORDER TO COMPLY WITH TB 206L-94-169. FORWARD RING WAS FOUND CRACKED UNDER SHIM AT LT LOWER AT	TACH POINT. APPARENTLY, THIS IS A STRESS CRACK CAUSED BY WORKING RIVETS IN THE INTERCOSTAL ASSEMBLY.					1	G	7	1 	3U				H2SW 					 
1995060900616	19950609	00616	SW 	1995	6	9	95ZZZX2781 	1	19950503	G	6310	289052017	SEAL 		206040270009	BELL 	206 	206L1 	1182107	SW 										FREEWHEEL	LEAKING 	B			ALGR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	1081G	1025 			BLA005	45405				POST-FLIGHT INSPECTION FOUND FREEWHEEL FORWARD SEAL LEAKING OIL. CAUSE UNKNOWN.						1	G	7	1 	3U				H2SW 					 
1995060900617	19950609	00617	SW 	1995	6	9	95ZZZX2782 	1	19950509	G	6730	C4264211	HOUSING 		206076062003	BELL 	206 	206L1 	1182107	SW 										SERVO	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3190P	12528	3595 		86841	45779				DURING DISASSEMBLY AND INSPECTION FOR OVERHAUL, FOUND CYLINDER ID WORN PAST LIMITS. PROBABLY CAUSED BY OIL CONTAMINATIO	N AND/OR PART HAS HAD A LONG SERVICE LIFE.					1	G	7	1 	3U				H2SW 					 
1995060900618	19950609	00618	SW 	1995	6	9	95ZZZX2783 	1	19950502	G	6220	206011149105	YOKE 		206011100151	BELL 	206 	206L1 	1182107	SW 										M/R HUB	PITTED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3195P	10185	2183 		A100961	45789				DURING SCHEDULED OVERHAUL, FOUND PITTING BEYOND LIMITS IN STRAP FITTING BORE OF YOKE.						1	G	7	1 	3U				H2SW 					 
1995060900619	19950609	00619	GL 	1995	6	9	95ZZZX2784 	2	19950522	G	7230	23005250	COMPRESSOR 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					ENGINE	CONTAMINATED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	343AL	10813				51372				DURING A COMPRESSOR CHANGE FOUND WHILE POSITIONING THE COMPRESSOR ON A WORK BENCH, A SMALL WHITE HARD BEAD ROLLED OUT OF	 THE SCROLL DISCHARGE TUBE. THE COMPRESSOR SCROLL WAS BORESCOPED TO CHECK FOR ANY MORE BEADS WHICH MAY HAVE BEEN LODGED	 IN THE SCROLL. NO FURTHER BEADS WERE NOTED.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995060900620	19950609	00620	GL 	1995	6	9	95ZZZX2785 	2	19950502	G	7260	6898642	GEARSHAFT 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					GEARBOX	PITTED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	343AL	3053 				51372				UPON DISASSEMBLY AND INSPECTION, FOUND AIR OIL GEARSHAFT PITTED.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995060900621	19950609	00621	SW 	1995	6	9	95ZZZX2786 	1	19950522	G	6510	2060403651	SHAFT ASSY 		206040370011	BELL 	206 	206L3 	1182108	SW 										T/R	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	349AL	4786 			BT1266	51388				FIRST TIME DISASSEMBLY FOR INSPECTION FROM BHT, FOUND SHAFT SPLINES EXCESSIVELY CORRODED.						1	G	7	1 	3U				H2SW 					 
1995060900622	19950609	00622	SW 	1995	6	9	95ZZZX2787 	1	19950502	G	3212	30924	VALVE 			BELL 	206 	206L3 	1182108	SW 										FLOAT	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL				0637	51460				FLOAT VALVE WAS FIRED FOR 2-YEAR INSPECTION. RUBBERIZED COATING PUT ON BY MANUFACTURER WAS REMOVED AND REVEALED EXCESSI	VE CORROSION. VALVE BODY IS CORRODED BEYOND LIMITS. THE CAP IS A DISSIMILAR METAL FROM BODY. THE COATING PUT ON BY TH	E MANUFACTURER TRAPS MOISTURE CAUSING CORROSION. GROUND STRAP INSTALLED WITH INCORRECT HARDWARE MAY CAUSE CORROSION.				1	G	7	1 	3U				H2SW 					 
1995060900623	19950609	00623	SW 	1995	6	9	95ZZZX2788 	1	19950503	G	6230	206040576103	BEARING 			BELL 	206 	206L3 	1182108	SW 										MAST	PITTED 	B			ALGR	O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	03	362AL	1524 			ZV1444	51471				TRANSMISSION CHIP LIGHT IN-FLIGHT. DISASSEMBLED MAST ASSEMBLY. CLEAN AND INSPECTED BEARING SN ZV-1444. FOUND OUTER RA	CE PITTED CAUSING TRANSMISSION CHIP LIGHT.					1	G	7	1 	3U				H2SW 					 
1995060900624	19950609	00624	NE 	1995	6	9	95ZZZX2789 	1	19950510	G	6510	7636104012101	HOUSING 			SKRSKY	S76 	S76A 	8143006	NE 										T/R DRIVESHAFT	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	376AL	1982 			3438AL0028	760002				DISASSEMBLY FOR REPAIR FOUND EXCESSIVE CORROSION ON MOUNT LUGS BEYOND MANUFACTURER'S CLEAN-UP LIMITS.						1	G	7	2 	3U				H1NE 					 
1995060900625	19950609	00625	GL 	1995	6	9	95ZZZX2790 	2	19950510	G	7314	216002	DRIVE SHAFT 		6899253 	AEROSP	AS355 	AS355F1 	8680810	EU 	ALLSN 	250C 	250C20F 	03013	GL 					FUEL PUMP	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	376E	7490 	3990 		0746	5213				DURING DISASSEMBLY OF UNIT FOR OVERHAUL, FOUND EXCESSIVE PITTING AND WEAR OF EXTERNAL SPLINES ON PUMP END OF SHAFT (INSI	DE OF PUMP). POSSIBLY CAUSED BY LACK OF MOLYDEM DISULFIDE GREASE ON SPLINES.					1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1995060900626	19950609	00626	SW 	1995	6	9	95ZZZX2791 	1	19950510	G	6220	412010219101	BEARING RACE 		412010216105	BELL 	412 	412 	1182202	SW 										M/R HUB	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	397AL	1692 			RE493	36012				ON DISASSEMBLY FOR REPAIR, FOUND BEARING RACE WORN BEYOND LIMITS. BEARING PN 412010216105, SN RE493. ARM PN 4120102631	01.					1	G	7	2 	4U				H4SW 					 
1995060900627	19950609	00627	SW 	1995	6	9	95ZZZX2792 	1	19950510	G	6220	412010219101	RACE 		412010216105	BELL 	412 	412 	1182202	SW 										M/R HUB	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	397AL	1692 			RE299	36012				ON DISASSEMBLY FOR REPAIR, FOUND BEARING RACE WORN BEYOND LIMITS. BEARING PN 412010216105, SN RE299. ARM PN 4120102631	01.					1	G	7	2 	4U				H4SW 					 
1995060900628	19950609	00628	NE 	1995	6	9	95ZZZX2793 	1	19950509	G	6220	76106080001111	BUSHING 			SKRSKY	S76 	S76A 	8143006	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476AL					760003				DURING SHOP TEAR-DOWN FOR REPAIR OF DAMPER DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE - CO	NTAMINATED OIL.					1	G	7	2 	3U				H1NE 					 
1995060900629	19950609	00629	NE 	1995	6	9	95ZZZX2794 	1	19950509	G	6220	7610608002107	BUSHING 			SKRSKY	S76 	S76A 	8143006	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476AL					760003				DURING SHOP TEAR DOWN FOR REPAIR OF DAMPER DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS.						1	G	7	2 	3U				H1NE 					 
1995060900630	19950609	00630	NE 	1995	6	9	95ZZZX2795 	1	19950509	G	6220	SB5079102	BEARING 			SKRSKY	S76 	S76A 	8143006	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476AL					760003				DURING SHOP TEAR DOWN FOR REPAIR OF DAMAGE DUE TO WEAK OPERATION, FOUND WEAR BETWEEN INNER AND OUTER RACES BEYOND MFG LI	MITS.					1	G	7	2 	3U				H1NE 					 
1995060900631	19950609	00631	GL 	1995	6	9	95ZZZX2796 	2	19950502	G	7261	23030994	SCAVENGE TUBE 			SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					OIL PUMP	BRACKET BROKEN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476AL	2845 				760003	CAE89145S			DURING SUDDEN PUMP STOPPAGE INSPECTION. DISCOVERED LOWER BRACKET ON THE SCAVENGE TUBE TO BE BROKEN. NOTE: THE MOUNTIN	G NUT WAS HOLDING THE BRACKET. THE SCAVENGE TUBE WAS HELD IN BY THE TOP MOUNTING BRACKET AND THE OIL PUMP SCAVENGE BORE	.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995060900632	19950609	00632	EU 	1995	6	9	95ZZZX2797 	1	19950511	G	6321	AH43881	DISCK 			BOLKMS	105 	BO105CBS 	5626008	EU 										ROTOR BRAKE	WARPED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5412J		300 			S784				ROUTINE INSPECTION FOUND ROTOR BRAKE DISK WARPED BEYOND LIMITS. CAUSE UNKNOWN.						1	G	7	2 	3U			NC	H3EU 					 
1995060900633	19950609	00633	SW 	1995	6	9	95ZZZX2798 	1	19950502	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	MISMANUFACTURED 	B			ALGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5829D	1816 			A674	45270				DURING INSPECTION, SPAR OBSERVED DRILLED AT TIP WEIGHT INSTALLATION LOCATIONS. TIP WEIGHT BLOCK AREA, HOLES DRILLED THR	OUGH TO SPAR INNER SKIN AT TIME OF MANUFACTURE.					1	G	7	1 	3U				H2SW 					 
1995060900634	19950609	00634	SW 	1995	6	9	95ZZZX2799 	1	19950502	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5734M	1955 			A133	45449				DURING ROUTINE INSPECTION, FOUND M/R BLADE HAS EXCESSIVE LEADING EDGE CORROSION. POSSIBLE IMPROPER HEAT TREAT BY MATERI	AL OR ALLOY FORMULATION.					1	G	7	1 	3U				H2SW 					 
1995060900635	19950609	00635	SW 	1995	6	9	95ZZZX2800 	1	19950515	G	6420	206010765001	BEARING 		206011810013	BELL 	206 	206L1 	1182107	SW 										T/R BLADE ROOT	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5740L	301 			AFS6045A	45459				ROUTINE INSPECTION FOUND BEARINGS WORN BEYOND LIMITS.						1	G	7	1 	3U				H2SW 					 
1995060900636	19950609	00636	EU 	1995	6	9	95ZZZX2801 	1	19950518	G	6410	355A12003108	BLADE 			AEROSP	AS355 	AS355F 	8680806	EU 										T/R BLADE POCKET	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5787E	2823 	80 			5058				DAILY INSPECTION FOUND SPAR HAS SPANWISE CRACK LOCATED 8 MM FROM EDGE OF SPAR THAT IS INSIDE BLADE POCKET AREA. CAUSE U	NKNOWN.					1	G	7	2 	3U				H11EU 					 
1995060900637	19950609	00637	NE 	1995	6	9	95ZZZX2802 	1	19950511	G	6510	S6137643292	TUBE ASSY 			SKRSKY	S76 	S76 	8143010	NE 										T/R DRIVE	DEBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	701AL		2719 			760238				DISASSEMBLY FOR OVERHAUL FOUND T/R DRIVE TUBE DEBONDED BEYOND MANUFACTURER'S MAXIMUM ALLOWABLE LIMITS.						1	G	7	2 	3U				H1NE 					 
1995060900638	19950609	00638	NE 	1995	6	9	95ZZZX2803 	1	19950511	G	6510	7636104012101	OUTER HOUSING 			SKRSKY	S76 	S76 	8143010	NE 										T/R DRIVESHAFT	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	701AL		2719 			760238				DISASSEMBLY FOR OVERHAUL FOUND EXCESSIVE CORROSION ON MOUNT LUGS BEYOND MAXIMUM ALLOWABLE CLEAN-UP LIMITS.						1	G	7	2 	3U				H1NE 					 
1995060900639	19950609	00639	GL 	1995	6	9	95ZZZX2804 	2	19950502	G	7240	23030911	COMBUSTION CASE 		230335128 	SKRSKY	S76 	S76 	8143010	NE 	ALLSN 	250C 	250C30S 	03013	GL 					ARMPIT	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	701AL		1750 		28263	760238				THIS DEFECT WAS DISCOVERED AT 1750-HOUR OVERHAUL. OUTER COMBUSTION CASE WAS CRACKED IN ARMPIT UNDER THE SCREEN PATCH RE	INFORCEMENT AND EXTENDED ON SEAM AND INTO THE SEAM PERPENDICULAR TO THE FLANGE AND PARALLEL TO THE FLANGE. A CRACK SUCH	 AS THIS MAY CAUSE POSSIBLE POWER LOSS IN ENGINE. NO REPAIR IS PERMITTED IN THIS AREA. OUTER COMBUSTION CASE IS SCRAPP	ED. CAUSE UNKNOWN.			1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995060900640	19950609	00640	NE 	1995	6	9	95ZZZX2805 	1	19950509	G	6220	7610608002107	BUSHING 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	702AL					760243				DURING TEAR DOWN AND INSPECTION FOR REPAIR DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE - CO	NTAMINATED OIL.					1	G	7	2 	3U				H1NE 					 
1995060900641	19950609	00641	NE 	1995	6	9	95ZZZX2806 	1	19950509	G	6220	7610608001106	BUSHING 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	702AL					760243				DURING SHOP TEAR DOWN AND INSPECTION FOR REPAIR DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE	 - CONTAMINATED OIL.					1	G	7	2 	3U				H1NE 					 
1995060900642	19950609	00642	NE 	1995	6	9	95ZZZX2807 	1	19950509	G	6220	7610608002103	BUSHING 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	702AL					760243				DURING SHOP TEAR DOWN FOR REPAIR OF DAMPER DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE - CO	NTAMINATED OIL.					1	G	7	2 	3U				H1NE 					 
1995060900643	19950609	00643	NE 	1995	6	9	95ZZZX2808 	1	19950509	G	6220	7610608003103	PISTON ROD 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	703AL				00423	760266				DURING SHOP TEAR DOWN FOR REPAIR OF DAMPER ASSY DUE TO WEAK OPERATION, FOUND INBOARD PISTON ROD BUSHING SURFACE WORN PAS	T LIMITS. SUSPECT WEAR CAUSED BY HYDRAULIC OIL CONTAMINATION.					1	G	7	2 	3U				H1NE 					 
1995060900644	19950609	00644	NE 	1995	6	9	95ZZZX2809 	1	19950509	G	6220	7610608002107	BUSHING 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	703AL					760266				DURING SHOP TEAR DOWN FOR REPAIR OF DAMPER DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE - OI	L CONTAMINATION.					1	G	7	2 	3U				H1NE 					 
1995060900645	19950609	00645	NE 	1995	6	9	95ZZZX2810 	1	19950509	G	6220	7610608001111	BUSHING 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	703AL					760266				DURING SHOP TEAR DOWN FOR REPAIR OF DAMPER DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE - OI	L CONTAMINATION.					1	G	7	2 	3U				H1NE 					 
1995060900646	19950609	00646	NE 	1995	6	9	95ZZZX2811 	1	19950509	G	6220	SB5079102	BEARING 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	703AL					760266				DURING SHOP TEAR DOWN FOR REPAIR OF DAMPER DUE TO WEAK OPERATION, FOUND WEAR BETWEEN INNER AND OUTER RACES BEYOND LIMITS	. SUSPECT CAUSE - OIL CONTAMINATED.					1	G	7	2 	3U				H1NE 					 
1995060900647	19950609	00647	NE 	1995	6	9	95ZZZX2812 	1	19950510	G	6510	S6137643292	VISCOUS DAMPER 			SKRSKY	S76 	S76 	8143010	NE 										T/R DRIVE	DEBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	703AL		10 			760266				POST-FLIGHT INSPECTION FOUND DAMPER TUBE DEBONDED BEYOND LIMITS.						1	G	7	2 	3U				H1NE 					 
1995060900648	19950609	00648	NE 	1995	6	9	95ZZZX2813 	1	19950509	G	6220	7610608002103	BUSHING 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	705AL					760267				DURING SHOP TEAR DOWN AND INSPECTION FOR REPAIR DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE	 - CONTAMINATED OIL.					1	G	7	2 	3U				H1NE 					 
1995060900649	19950609	00649	NE 	1995	6	9	95ZZZX2814 	1	19950509	G	6220	7610608001106	BUSHING 			SKRSKY	S76 	S76 	8143010	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	705AL					760267				DURING SHOP TEAR DOWN AND INSPECTION FOR REPAIR DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE	 - CONTAMINATED OIL.					1	G	7	2 	3U				H1NE 					 
1995060900650	19950609	00650	NE 	1995	6	9	95ZZZX2815 	1	19950502	G	6322	10E933	SHAFT 			SKRSKY	S76 	S76A 	8143006	NE 										COOLER BLOWER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	709AL	4113 	651 			760278				DISCOVERED AT ENGINE CHANGE, OIL COOLER BLOWER SPLINES WORN EXCESSIVELY. SUSPECT CAUSE - WHEN INSTALLED ON ENGINE, SPLI	NES WERE INSTALLED WITH GREASE. THE GREASE BLOCKED ENGINE OIL PASSAGE IN GEARBOX CAUSING LOSS OF LUBRICATION ON WET SPL	INES.				1	G	7	2 	3U				H1NE 					 
1995060900651	19950609	00651	NE 	1995	6	9	95ZZZX2816 	1	19950509	G	6220	7610608002	BUSHING 			SKRSKY	S76 	S76A 	8143006	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	710AL					760279				DURING TEAR DOWN AND INSPECTION FOR REPAIR DUE TO WEAK OPERATION, FOUND BUSHING ID WORN PAST LIMITS. SUSPECT CAUSE - OI	L CONTAMINATION.					1	G	7	2 	3U				H1NE 					 
1995060900653	19950609	00653	NE 	1995	6	9	95ZZZX2818 	1	19950421	G	6220	7610608003103	ROD 			SKRSKY	S76 	S76A 	8143006	NE 										DAMPER	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	712AL		962 			760280				SHOP REPAIR OF DAMPER ASSY DUE TO LEAKING OIL. HEAVY WEAR TO ROD INNER SEAL SURFACE. ROD WORN BEYOND REPAIR LIMIT.						1	G	7	2 	3U				H1NE 					 
1995060900654	19950609	00654	NE 	1995	6	9	95ZZZX2819 	1	19950509	G	6730	30006773	GLAND 			SKRSKY	S76 	S76A 	8143006	NE 										SERVO	WORN 	B			ALGR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	741SW		1666 			760070				DURING IN-SHOP TEAR DOWN OF ACTUATOR FOR INSPECTION AND REPAIR DUE TO LEAKING, FOUND ID OF GLANDS, 2 EACH, WORN PAST LIM	ITS BY MOVEMENT OF PISTONS THROUGH GLANDS.					1	G	7	2 	3U				H1NE 					 
1995060900655	19950609	00655	NE 	1995	6	9	95ZZZX2820 	1	19950505	G	6730	30006822	SPRING 			SKRSKY	S76 	S76A 	8143006	NE 										SERVO	MISSING 	B			ALGR	K				NONE 				W	K		INADEQUATE Q C 	FLUID LOSS 		IN	INSP/MAINT 	1			SW	03	741SW					760070				SERVO ACTUATOR WAS SENT TO HYDRAULIC SHOP FOR REPAIR DUE TO LEAKING. SERVO TT 6303.5. TIME SINCE OVERHAUL: 1665.7. D	URING TEAR DOWN OF ACTUATOR FOR REPAIR, NOTED 2 SPRINGS, PN 30006822, HAD NOT BEEN INSTALLED AT OVERHAUL BY MANUFACTURER	. ABSENCE OF THESE SPRINGS WOULD DISALLOW PROPER SPRING LOADING OF THE SERVO VALVE SECONDARY SPOOL IN THE EVENT OF PRIM	ARY SPOOL JAMMING IN SYSTEMS NR 1 OR NR 2.			1	G	7	2 	3U				H1NE 					 
1995060900813	19950609	00813	EU 	1995	6	9	95ZZZX2823 	1	19950510	G	5610	1172416902	WINDOW 			BOLKMS	117 	BK117B2 	5626013	EU 										PILOT DOOR	DEPARTED 	E				O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			SW	03	132AE					7238				IN CRUISE FLIGHT, PILOT'S SLIDING WINDOW CAME OFF AND DEPARTED AIRCRAFT. CONTACTED FUSELAGE AFT OF PILOT'S DOOR. DID N	OT CONTACT ROTORS. LANDED SKY HARBOR WITHOUT INCIDENT. BK-117 IPC, FIGURE 211A, ITEM 230.					1	G	7	2 	3U			NC	H13EU 					 
1995060900814	19950609	00814	NE 	1995	6	9	95ZZZX2824 	2	19950508	G	7323	25248433	GOVERNOR 			BOLKMS	117 	BK117B2 	5626013	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 1 ENGINE	FAILED 	E				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			SW	03	136AE	1147 				7234	LE456098			WHEN ECU WAS TURNED ON AFTER TAKEOFF, NR 1 ENGINE DROPPED OFF LINE. LANDED AT AIRPORT WITHOUT INCIDENT. IPC REF: 73-2	0-00, FIGURE 2, ITEM NR 45.					1	G	7	2 	3U	3	U	NC	H13EU 	E5NE				 
1995060900816	19950609	00816	CE 	1995	6	9	95ZZZX2826 	1	19950524	G	2822	2017002	PUMP 	TRW 		RKWELL	NA265 	NA26540 	6402608	CE 										FUEL BOOST	FAILED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	310NT		227 			28277				UNIT WAS INSTALLED 12/7/94 AT AIRCRAFT TT 14,017.3 HRS. IT WAS REMOVED 5/23/95 AT AIRCRAFT TT 14,244.3 HRS WITH 227.0 HR	S TIME IN SERVICE SINCE ZERO-TIME OVERHAUL. (PUMP TBO 2,000 HRS.) UNIT REMOVAL CAUSED BOOST PUMP CIRCUIT BREAKER TO TR	IP AND WOULD NOT RESET. UNIT WAS OVERHAULED 9-9-94 BY A REPAIR STATION. SUBMITTER SUGGESTS RELIABILITY OF THESE OVERHA	ULED PUMPS HAS BEEN POOR AND LOW-TIME FAILURE SUCH AS THIS ARE QUITE COMMON IN OUR FLEET OF 17 AIRCRAFT.			2	L	7	2 	4J				A2WE 					 
1995060900817	19950609	00817	SO 	1995	6	9	95ZZZX2827 	1	19950517	G	3230	A48617	HANDLE 			GULSTM	G1159 	GIV 	3980115	SO 										GEAR CONTROL	BROKEN 	B		A	BTVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	1SL	2187 	1035 		184	1167				DURING INSPECTION OF LANDING GEAR CONTROL MODULE FOR FAA SAFETY RECOMMENDATION 94.197199, THE UPPER HALF OF THE GEAR HAN	DLE WAS FOUND BROKEN. NO OBVIOUS CAUSE WAS APPARENT. IT IS POSSIBLE THIS PART WAS DEFECTIVE AND BROKE PREMATURELY FROM	 NORMAL USE. ALL OTHER GIV SERIES AIRCRAFT (8) WERE CHECKED WITH NO DEFECTS. OPER CONTROL NR BVTR051795.				2	L	7	2 	4F			RT	A12EA 					 
1995060900818	19950609	00818	CE 	1995	6	9	95ZZZX2828 	1	19950509	G	7170	1019200931	PURGE TANK 			BEECH 	200 	B200 	1152922	CE 										NR 1 ENGINE	FAILED 	D	L	A		O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			DE	DESCENT 	1			EA	03	144C	2624 				BB1013				ACFT DESCENDING THROUGH 10,000 FEET WHEN A JET FUEL ODOR COMING THROUGH AIR VENT. SMELL DISSIPATED. THERE WAS NO SMOKE	 IN THE ACFT. ALL ENG INSTRUMENTS INDICATING NORMAL. UPON LANDING, PILOT OPENED BOTH ENG COWLINGS LOOKING FOR OBVIOUS 	FUEL LEAK. FOUND END COVER BLOWN OFF INBOARD END OF PURGE TANK, NR 1 ENG. TT ON PART IS 2624.0 HRS.				1	L	7	2 	4T				A24CE 					 
1995060900819	19950609	00819	CE 	1995	6	9	95ZZZX2829 	1	19950516	G	5210	50440014123	STRIKER PLATE 			BEECH 	200 	200BEECH 	1152920	CE 										DOOR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	22071	6760 				BB111				FOUND STRIKER PLATE CRACKED BY DOOR BAYONET ROLLER. REMOVED AND REPLACED STRIKER PLATE. SUGGEST LOOKING AT THESE EVERY	 INSPECTION, HAVE FOUND THREE OTHER CASES IN DIFFERENT POSITIONS.					1	L	7	2 	4T				A24CE 					 
1995060900820	19950609	00820	EU 	1995	6	9	95ZZZX2830 	1	19950504	G	2430		WIRE 			AMD 	FALC10	FALCON10 	2730101	EU 										BATTERY BOX	TERMINAL LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	100CK	2730 				222				WHILE PERFORMING A ROUTINE INSPECTION, FOUND WIRE TERMINAL ON WIRE NR PP19E6, ATTACHED TO TERMINAL NR 2 OF AUXILIARY BUS	 'D' RELAY 51P, WAS NOT CRIMPED ON THE WIRE PROPERLY. THIS LEAD TO INCREASED RESISTANCE AT THIS CONNECTION WITH THE TER	MINAL END AND APPROXIMATELY 4 INCHES OF THE WIRE GETTING EXTREMELY HOT AND THE INSULATION DAMAGED. THIS COULD HAVE RESU	LTED IN A FIRE IN THE TAILCONE AREA. SUBMITTER SUGGESTS TO INSPECT THESE TERMINALS FOR LOOSE ATTACHMENT AT MORE FREQUEN	T INTERVALS.		2	L	7	2 	4F				A33EU 					 
1995060900822	19950609	00822	NM 	1995	6	9	95ZZZX2832 	1	19950419	G	5313	210056153	STRINGER 			PIPER 	PA60 	PA60600 	7106001	NM 										NLG WW LT	CRACKED 	B			BONR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	60DC	4559 				600797806123				DURING AN 'ANNUAL' INSPECTION, FOUND NLG SUPPORT STRINGER CRACKED ACROSS OPENING FOR THE LT NLG DOOR ROD. LOOKING CLOSE	R, FOUND BOTH DOUBLERS CRACKED AT SAME LOCATION.					1	M	7	2 	3O			RT	A17WE 					 
1995060900823	19950609	00823	NM 	1995	6	9	95ZZZX2833 	1	19950419	G	5320	210056165	DOUBLER 			PIPER 	PA60 	PA60600 	7106001	NM 										NLG WW LT	CRACKED 	B			BONR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	60DC	4559 				600797806123				DURING AN 'ANNUAL' INSPECTION, FOUND NLG SUPPORT STRINGER CRACKED ACROSS OPENING FOR THE LT NLG DOOR ROD. LOOKING CLOSE	R, FOUND BOTH DOUBLERS CRACKED AT SAME LOCATION.					1	M	7	2 	3O			RT	A17WE 					 
1995060900824	19950609	00824	NM 	1995	6	9	95ZZZX2834 	1	19950419	G	5320	210056163	DOUBLER 			PIPER 	PA60 	PA60600 	7106001	NM 										NLG WW LT	CRACKED 	B			BONR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	60DC	4559 				600797806123				DURING AN 'ANNUAL' INSPECTION, FOUND NLG SUPPORT STRINGER CRACKED ACROSS OPENING FOR THE LT NLG DOOR ROD. LOOKING CLOSE	R, FOUND BOTH DOUBLERS CRACKED AT SAME LOCATION.					1	M	7	2 	3O			RT	A17WE 					 
1995060900827	19950609	00827	EA 	1995	6	9	95ZZZX2837 	1	19950516	G	4980	38460271	CLAMP 			CNDAIR	CL600 	CL6002B16 	1900305	EA 										APU EXHAUST	CRACKED 	B		A	JZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	449ML					5022				WHILE REMOVING THE APU FROM THE AIRCRAFT, MAINTENANCE PERSONNEL DISCOVERED THE APU EXHAUST NOZZLE CLAMP CRACKED AT THE W	ELD AREA WHERE THE SURGE VALVE EXHAUST PORT IS MOUNTED. THIS IS THE FIRST ONE FOUND CRACKED. MOST HAVE BEEN BENT IN TH	IS AREA. SUSPECT CAUSE IS DUE TO REMOVAL AND REPLACEMENT OF THE CLAMP ASSEMBLY FROM A 90 DEGREE ELBOW AND HOSE ATTACH P	OINT. THE AREA TO WORK IN IS LIMITED WHEN IN THE AIRCRAFT. ADDITIONALLY, THE ELBOW AND HOSE IT ATTACHES TO CREATES FUR	THER PROBLEMS. SUBMITTER SUGGESTS TO PREVENT RECURRENCE, A BETTER DESIGNED ATTACHMENT AT THE SURGE VALVE EXHAUST CAN BE	 DEVELOPED. OPER CONTROL NR JZBR9510212.	2	L	7	2 	4F			RT	A21EA 					 
1995060900828	19950609	00828	CE 	1995	6	9	95ZZZX2838 	1	19950512	G	2721		TRIM TAB SYS 			BEECH 	90 	F90 	1152909	CE 										RUDDER	OUT OF RIG 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	42SC					LA131				PILOT REPORTS RUDDER TRIM TAB BECOMES STUCK WHEN TRIMMED FULL RIGHT. (REPORTED ON RETURN FROM LOCAL AREA TRAINING FLIGH	T AT 14:00). T/S RUDDER TRIM TAB ACTUATOR, FOUND PEDESTAL KNOB/INDICATOR OUT OF RIG AS WELL AS RUDDER TRIM TAB ACTUATOR	/ROD ENDS, AND CABLE STOPS, CAUSING ACTUATOR TO BIND INTERNALLY AT FULL RIGHT. RIGGED TAB ACTUATOR TO CENTER POSITION, 	RIGGED ROD ENDS TO CENTER TAB, RESET CABLE STOPS TO ALLOW PROPER TAB TRAVEL TO BOTH SIDES, AND RECENTERED PEDESTAL KNOB/	INDICATOR. ALL WORK DONE IAW BEECHCRAFT F-90 MM, CH. 27-20-00, PG. 7-9.		1	L	7	2 	4T				A31CE 					 
1995060900829	19950609	00829	EA 	1995	6	9	95ZZZX2839 	2	19950505	G	7261	3004091	SCREEN 			BEECH 	200 	200BEECH 	1152920	CE 	PWA 	PT6 	PT6A41 	52043	EA 					OIL SCAV PUMP	BLOCKED 	B	L		ERY2	E				ENGINE SHUTDOWN 				J	K		WARNING INDICATION 	FLUID LOSS 		CR	CRUISE 	1			SO	11	780RC	4949 	1808 			BB780	PCE81769			PILOT REPORTED LOSS OF OIL PRESSURE DURING FLIGHT. THE ENGINE WAS SHUT DOWN AND AN UNEVENTFUL LANDING MADE. OIL WAS LE	AKING FROM THE COMPRESSOR INLET AND BLEED AIR VALVES. AFTER TROUBLESHOOTING, THE ACCESSORY GEARBOX WAS DISASSEMBLED AND	 THE INLET SCREEN FOR THE OIL SCAVAGE PUMP WAS BLOCKED WITH VARNISH COATING FROM INSIDE THE GEARBOX. ENGINE REMOVED AND	 SENT TO P AND W FOR REPAIR.			1	L	7	2 	4T	4	T		A24CE 	E4EA				 
1995060900830	19950609	00830	EA 	1995	6	9	95ZZZX2840 	1	19950501	G	2841	656054	GAUGE 	ROCHSTRGAUGE		SCWZER	G164T 	G164D 	3952804	EA 										SHAFT BUSHING	STICKING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	8177K	105 				8D				FLOAT ARM TOO STIFF BECAUSE BEARING OR BUSHING ON LOWER GAUGE SHAFT TOO TIGHT. THIS MADE THE GAUGE STICK ON SOME LEVEL 	POSITIONS - SUCH AS ONE-HALF FUEL READING WHEN FUEL TANK WAS EMPTY.					1	Q	7	1 	3T				1A16 					 
1995060900831	19950609	00831	CE 	1995	6	9	95ZZZX2841 	1	19950504	G	2460	1013644623	BOX ASSY 		A228 	BEECH 	200 	B200 	1152922	CE 										ZONE 611	DETACHED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	63791					BB1100				BOX FOUND CRACKED AT NUTPLATES AND DANGLING BY THE WIRES. THIS IS A HOT BUS AND COULD RESULT IN SEVERE DAMAGE TO THE AI	RCRAFT IF IT SHOULD COME IN CONTACT WITH THE WING STRUCTURE. SUBMITTER SUGGESTS SHOULD BE MADE STIFFER AND A BETTER MAT	ERIAL.				1	L	7	2 	4T				A24CE 					 
1995060900832	19950609	00832	SW 	1995	6	9	95ZZZX2842 	1	19950321	G	3240	103145	BOLT 	PARKERHANFIN	30107C 	GULSTM	690TP 	690A 	0141722	SW 										RT MLG	MISSING 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	09	2FOR	500 			796	11169				ON THE CLEVELAND BRAKE, 6 BOLTS ARE REMOVED EVERY 100 HOURS TO REMOVE THE WHEEL TO LUBE THE BEARINGS. ON PERFORMING 100	-HOUR INSPECTION, FOUND 2 EACH BOLTS MISSING AND 1 BOLT LOOSE. BRAKE PAD WAS RUBBING ON TIRE. SECOND SUCH INCIDENT IN 1	 MONTH. SUGGEST REPLACING BOLTS WITH SAFETY WIRE-CAPABLE BOLTS.				1	H	7	2 	3T				2A4 					 
1995060900833	19950609	00833	EA 	1995	6	9	95ZZZX2843 	1	19950512	G	2450	VS403	SENSOR 			CNDAIR	CL600 	CL6001A11 	1900302	EA 										NR 1 AC BUS	DEFECTIVE 	B			JO1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	91UC	4796 				1051				THE PILOTS REPORTED HEARING A C-CHORD CHIME AND THE NR 2 CHANNEL PITCH AND ROLL 'OFF' LIGHTS ILLUMINATED ON THE AUTOPILO	T STATUS PANEL. THE PILOT ALSO NOTED THAT THE ESSENTIAL POWER 'ALTN' LIGHT FLICKERED WHEN THIS OCCURRED. MAINTENANCE S	USPECTED THE NR 1 AC BUSS VOLTAGE/FREQUENCY SENSOR FAULTY. THE DISCREPANCY WAS CONFIRMED AND CORRECTED BY REPLACIING TH	E NR 1 AC BUSS VOLT/FREQ SENSOR.			2	L	7	2 	4F			RT	A21EA 					 
1995060900834	19950609	00834	CE 	1995	6	9	95ZZZX2844 	1	19950515	G	5320		FRAME 			CESSNA	525 	525 	2076601	CE 										COCKPIT WINDOW	DAMAGED 	B			IW1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25	800HS	394 				5250051				WHILE PERFORMING REMOVAL OF COCKPIT SIDE WINDOW (RIGHT), THE WINDSHIELD RETAINER MUST BE REMOVED. UPON REMOVAL OF SAID 	RETAINER, TWO HOLES WERE FOUND DRILLED IN THE FRAME STRUCTURE. THIS IS A CONDITION THAT IS CONSIDERED TO BE AN ISOLATED	 INCIDENT. REPAIRS WERE MADE IAW CESSNA ENGINEERING.				1	L	7	2 	4F			RT	A1WI 					 
1995061600058	19950616	00058	EU 	1995	6	16	95ZZZX2846 	1	19950501	G	3232	A223801	SWITCH 			AMD 	FALC20	FALCONF 	2720306	EU 										RT MLG DOOR CYL	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	20FM				925	321				WHILE PERFORMING GEAR DOOR ACTUATOR VOLTAGE DROP TEST IAW THE F20 MM 32-20-00, RT MLG DOOR CYLINDER SWITCH FAILED. SWIT	CH WAS REMOVED FROM THE AIRCRAFT, DISASSEMBLED FOR POSSIBLE REPAIR AND DETERMINED UNSERVICEABLE DUE TO INADEQUATE MECH S	WITCH ACTION. UPON DISASSEMBLY, MOBIL 28 GREASE DISCOVERED IN LIEU OF OVERHAUL MANUAL RECOMMENDATION OF COMPOUND S15. R	ECOMMEND REPETITIVE VOLTAGE DROP TEST IAW MM 32-20-00 TO PREVENT HARD FAILURES. USE PACKING OF SWITCH WITH COMPOUND S15	 DURING REPAIR OR OVERHAUL IAW MESSIER-BUGATTI COMPONENT MANUAL 19-09-06, PAGE 704, STEP 'B'.		2	L	7	2 	4F				A7EU 					 
1995061600059	19950616	00059	EU 	1995	6	16	95ZZZX2847 	1	19950517	G	7120		TUBE FRAME 			SLNSBY	T67 	T67M260 	8323006	EU 										ENGINE MOUNT	INCOMPLETE WELD 	B			UNER	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	03	3100X	198 				930557				AIRCRAFT STEEL TUBE ENGINE FRAME/MOUNT, PN T67G51201, CLUSTER WELD WAS NOT COMPLETELY WELDED DURING THE MANUFACTURING PR	OCESS. THE TOP/UPPER RIGHT CLUSTER WELD CONTAINED A TUBE WHICH WAS NOT COMPLETELY WELDED INTO THE CLUSTER. THE WELD BE	AD AROUND THE TUBE END WAS NOT COMPLETE AS IT ENTERED THE TUBING CLUSTER. THIS DISCREPANCY WAS FOUND DURING ROUTINE MAI	NTENANCE INSPECTION AND REPLACED WITH A NEW ENGINE FRAME ASSY.			1	L	7	1 	3O			NT	A73EU 					 
1995061600060	19950616	00060	CE 	1995	6	16	95ZZZX2848 	1	19950118	G	5311	1024302411	FRAME 			BEECH 	58 	58P 	1152744	CE 										FS 107	CRACKED 	B	S		CNZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	156Z	2000 				TJ369				AT THE 1,000-HOUR STRUCTURAL INSPECTION BEING DONE BY UNITED BEECHCRAFT ONTARIO, FINDING CRACKS IN THE FRAME AT STATION 	107.000 FRAME, PN 102-430241-1, AT THE END OF SPLICE, PN 102-430196-3. ALL THE AIRCRAFT THAT ARE BEING FOUND WITH CRACK	S ARE IN THE 300 S/N'S AND HAVE 4 MISSING RIVETS. THE AIRCRAFT WITH S/N IN THE 400 SERIES HAVE RIVETS INSTALLED AND NO 	CRACKS. THE 1,000-HOUR STRUCTURAL INSPECTION IS A REQUIRED INSPECTION BY THE U. S. FOREST SERVICE ON THEIR BARON 58P'S.			1	L	7	2 	3O				A23CE 					 
1995061600061	19950616	00061	CE 	1995	6	16	95ZZZX2849 	1	19950118	G	5311	1024302411	FRAME 			BEECH 	58 	58P 	1152744	CE 										FS 107	CRACKED 	B	S		CNZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	132Z	4000 				TJ284				AT THE 1,000-HOUR STRUCTURAL INSPECTION BEING DONE BY UNITED BEECHCRAFT ONTARIO, FINDING CRACKS IN THE FRAME AT STATION 	107.000 FRAME, PN 102-430241-1, AT THE END OF SPLICE, PN 102-430196-3. ALL THE AIRCRAFT THAT ARE BEING FOUND WITH CRACK	S ARE IN THE 300 S/N'S AND HAVE 4 MISSING RIVETS. THE AIRCRAFT WITH S/N IN THE 400 SERIES HAVE RIVETS INSTALLED AND NO 	CRACKS. THE 1,000-HOUR STRUCTURAL INSPECTION IS A REQUIRED INSPECTION BY THE U. S. FOREST SERVICE ON THEIR BARON 58P'S.			1	L	7	2 	3O				A23CE 					 
1995061600062	19950616	00062	CE 	1995	6	16	95ZZZX2850 	1	19950118	G	5311	1024302411	FRAME 			BEECH 	58 	58P 	1152744	CE 										FS 107	CRACKED 	B	S		CNZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	153Z	3128 				TJ322				AT THE 1,000-HOUR STRUCTURAL INSPECTION BEING DONE BY UNITED BEECHCRAFT ONTARIO, FINDING CRACKS IN THE FRAME AT STATION 	107.000 FRAME, PN 102-430241-1, AT THE END OF SPLICE, PN 102-430196-3. ALL THE AIRCRAFT THAT ARE BEING FOUND WITH CRACK	S ARE IN THE 300 S/N'S AND HAVE 4 MISSING RIVETS. THE AIRCRAFT WITH S/N IN THE 400 SERIES HAVE RIVETS INSTALLED AND NO 	CRACKS. THE 1,000-HOUR STRUCTURAL INSPECTION IS A REQUIRED INSPECTION BY THE U. S. FOREST SERVICE ON THEIR BARON 58P'S.			1	L	7	2 	3O				A23CE 					 
1995061600063	19950616	00063	WP 	1995	6	16	95ZZZX2851 	2	19950510	G	7250	31038391	SEAL 		31969752 						GARRTT	TPE331	TPE33112UA 	01514	WP 					TURB ROTATE AIR	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		6977 			9233151471		P70032			DURING INSPECTION FOR CAM, FOUND PART CRACKED 15 PLACES. SB 72-0840 AUTHORIZES INSTALLATION OF PN 3107085-2 TO PROVIDE 	INCREASED SEAL PLATE TENSION AGAINST THE FIRST STAGE ROTOR ASSEMBLY BY INCORPORATING A SHIM BETWEEN THE AIR SEAL AND CUR	VIC COUPLING. INCREASED TENSION ON THE SEAL FLANGE RESULTS IN CRACKING AT THE SEAL PLATE FLANGE; 3714 CYCLES, 3735:28 H	OURS IN SERVICE SINCE COMPLIANCE WITH SB 72-0840.								4	T			E4WE				 
1995061600064	19950616	00064	NE 	1995	6	16	95ZZZX2852 	2	19950530	G	7314	025323150	PUMP 	PESCO 		CESSNA	425 	425 	2076018	CE 	PWA 	PT6 	PT6A112 	52043	NE 					LT ENG FUEL	FAILED 	D				K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	09	1BM	2092 				4250042	PCE12091			FUEL PUMP ON LEFT ENGINE, SEAL LEAKED FUEL INTO FUEL CONTROL DRIVE, WASHING THE GREASE OUT OF THE DRIVE BEARING CAUSING 	BEARING FAILURE AND DRIVE COUPLING TO SHEAR.					1	L	7	2 	3T	3	T	RT	A7CE 	E4EA				 
1995061600071	19950616	00071	NM 	1995	6	16	95ZZZX2859 	1	19950501	G	3213	65B0016319	MAIN GEAR 		0066 	BOEING	747 	747* 		NM 										LT BLG	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99										THE CLEARANCE BETWEEN B.L.G. AXLE AND NUT THREADS WAS FOUND TO BE 0.009 INCH TO 0.018 INCH. THERE ARE NO REFERENCES IN 	OHM 32-10-21 ABOUT DIMENSION/WEAR LIMITS. IN REPLY TO INQUIRY FOR INFORMATION, BOEING SENT THE THREADS DATA. THE PARTS	 WERE DIMENSIONALLY INSPECTED AND FOUND UNDER THE LIMITS. THE WHOLE TRUCK WAS REPLACED. SUBMITTER RECOMMENDS INSPECTIO	N/WEAR LIMIT AND REPAIR INSTRUCTIONS OF TRUCK BEAM ASSEMBLIES' THREADS TO BE INCLUDED IN OHM.			2	L	7	4 	4F			RT	A20WE 					 
1995061600086	19950616	00086	EU 	1995	6	16	95ZZZX2875 	1	19950428	G	2740	12911100	ACTUATOR 			PILATS	PC12 	PC12 	7090550	EU 										PITCH TRIM	MOTOR FAILED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	62JT	109 			023	107				PERFORMED STABILIZER TRIM FUNCTION CHECK DURING 100-HOUR INSPECTION. ACTUATOR FAILED CHECK BECAUSE TRAVEL WAS OUT OF LI	MITS. ALSO, THE ALTERNATE TRIM WAS INOPERATIVE. THE OWNER STATED THE AUTOPILOT WOULD NOT STAY ENGAGED IN-FLIGHT. FOUN	D MOTOR USED FOR AUTOPILOTS/ALTERNATE TRIM WAS OPEN. REPLACED ACTUATOR, OPS CHECK GOOD. HIGHLY RECOMMEND THAT FUNCTION	 CHECKS BE PERFORMED PER MM. THESE ARE VERY NEW AIRCRAFT AND SHOULD BE FOLLOWED CLOSELY.			1	L	7	1 	3T			RT	A78EU 					 
1995061600087	19950616	00087	WP 	1995	6	16	95ZZZX2876 	1	19950427	G	3213	369H600142	STRUT 			HUGHES	369 	369E 	4470707	WP 										RT FWD STRUT	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	6508U	783 				0084E				CRACKED LANDING STRUT, PN 369H6001-42 MD500 IPB, FIGURE 1, ITEM 26, PAGE 4. AC TT 783.1. CRACK RUNS FROM LOWER END OR 	UPPER UPWARD UNDER FAIRING MOUNTING PLATE APPROXIMATELY 4 INCHES LONG. THERE IS NO INSPECTION REQUIREMENT TO INPSECT TH	IS AREA EXCEPT TO REMOVE THE LANDING FAIRING AT 100-HOUR INSPECTION. THIS IS A SEALED AREA, THIS CRACK WOULD NOT HAVE B	EEN FOUND HAD SEALING COMPOUND NOT BEEN REMOVED. RECOMMEND REMOVING SEALING COMPOUND AND INSPECTING FOR CRACKS EVERY 30	0 FLIGHT HOURS.		1	G	7	1 	3U				H3WE 					 
1995061600124	19950616	00124	SW 	1995	6	16	95ZZZX2877 	1	19950323	G	6410	214011801109	BLADE 			BELL 	214 	214ST 	1182106	SW 										T/R HUB	MISINSTALLED 	C				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EU	01					A117					T/R BLADES INSTALLED IMPROPERLY.						2	G	7	2 	4U				H10SW 					 
1995061600125	19950616	00125		1995	6	16	95ZZZX2878 	4	19950206	G	3416	214175278101	ALTIMETER 			BELL 	212 	212 	1181420	SW 										COCKPIT	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01					188412					ALTIMETER KOLSMAN WINDOW ADJUSTMENT VERY ROUGH.						1	G	7	1 	4U			 	H4SW 					 
1995061600126	19950616	00126	SW 	1995	6	16	95ZZZX2879 	1	19950518	G	2460		LOCK SWITCH 			BELL 	206 	206B3 	1181506	SW 										ELECT SYS	FAILED 	B			TU3R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	07	2FOR					3474				INSTALLED LOCK SWITCH. TOT LIGHT ILLUMINATED, TRIED TO RESET SWITCH, DID NOT RESET, SWITCH WOULD JUST TURN. BROKEN INT	ERNALLY.					1	G	7	1 	3U				H2SW 					 
1995061600127	19950616	00127	CE 	1995	6	16	95ZZZX2880 	1	19950421	G	7603	C2995050102	CONTROL CABLE 			CESSNA	172 	172M 	2072418	CE 										THROTTLE	FAILED 	D				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			NM	01	80347					172066538				OUTER HOUSING FAILED ALLOWING THROTTLE TO CLOSE, BUT NOT OPEN. AIRCRAFT MADE A SUCCESSFUL FORCED LANDING. NO DAMAGE OR	 INJURIES.					1	H	7	1 	3O			NT	3A12 					 
1995061600128	19950616	00128	SW 	1995	6	16	95ZZZX2881 	1	19950417	G	5711		SPAR WEB 			MOONEY	M20 	M20E 	5870212	SW 										WING CENTER SECT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	94011	1717 				915				DURING ANNUAL INSPECTION, NOTED WING CENTER SECTION MAIN SPAR WEB WAS BADLY DAMAGED DUE TO INTERGRANULAR CORROSION. THI	S DAMAGE WAS TO A DEGREE THAT SEVERAL HOLES WERE NOTED, THROUGH WHICH A PENCIL COULD BE PASSED. THERE IS NO PROCEDURE I	N THE STRUCTURAL REPAIR MANUAL THAT GIVES ANY PROCEDURE FOR REPAIRING THIS DAMAGE. FAA HAS RECOMMENDED A DESIGNATED ENG	INEER BE CONTACTED FOR OBTAINING DATA APPROVAL FOR REPAIR OF THE STRUCTURE.			1	L	7	1 	3O				2A3 					 
1995061600129	19950616	00129		1995	6	16	95ZZZX2882 	4	19950525	G	6113	D4247	BULKHEAD 			BEECH 	23 	C23 	1151242	CE 										PROP SPINNER	CRACKED 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	614PW	454 				M2364				FORWARD PROPELLER SPINNER BULKHEAD CRACKED AROUND RADIUS OF SHOULDERED WASHERS. THIS IS POOR DESIGN AS THE BULKHEAD IS 	NOT FLAT AT OUTER RADIUS OF WASHERS. THIS HAS BEEN THE TWELFTH BULKHEAD REPLACED ON THIS TYPE AIRCRAFT IN THE PAST YEAR	 AT THIS REPAIR STATION. SOME HAVE BEEN FOUND CRACKED WITH LESS THAN 100 HOURS.				1	L	7	1 	3O				A1CE 					 
1995061600130	19950616	00130	EA 	1995	6	16	95ZZZX2883 	2	19950501	G	7322	46A227	VENTURI 	FACET 	MA45 	PIPER 	PA32 	PA32260 	7103206	SO 	LYC 	O540 	O540E4B5 	41532	EA 					CARBURETOR	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	4315T				R418863	327200016	L1061440			FOUND CORROSION IS OCCURRING BELOW THE SURFACE OF THE CASTING CAUSING THE SURFACE TO BUBBLE UP, CHANGING THE SHAPE OF TH	E VENTURI. IF THIS PART IS PLATED, CAN THE PLATING BE ELIMINATED?					1	L	7	1 	3O	3	O		A3SO 	E295				 
1995061600131	19950616	00131	CE 	1995	6	16	95ZZZX2884 	1	19950517	G	3213	LM29749	BEARING 	PARKERHANFIN	40135 	CESSNA	402 	402B 	207590P	CE 										RT MLG	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	53SA					402B0591				CREW SQUAWKED, 'RIGHT BRAKE DRAGS AND NOISY'. FOUND INBOARD WHEEL BEARING DISINTEGRATED, NOTHING REMAINING EXCEPT INNER	 RACE OUTBOARD BEARING FAILED, ALL ROLLERS GONE. BOTH WHEEL HALVES 'WALLOWED OUT'. ONLY THING HOLDING WHEEL TO AXLE WA	S CLEVELAND BRAKE CALIPER. INSTALLED CUSTOMER'S SPARE WHEEL, AIRCRAFT WENT INTO INSPECTION.				1	L	7	2 	3O				A7CE 					 
1995061600133	19950616	00133	SO 	1995	6	16	95ZZZX2886 	2	19950519	G	8520		CRANKSHAFT 			BEECH 	55 	95B55 	1152706	CE 	CONT 	O520 	IO520E 	17032	SO 					FLANGE	CRACKED 	D				A				UNSCHED LANDING 				J	K		WARNING INDICATION 	FLUID LOSS 		NR	NOT REPORTED 	1			SO	09	3653A		600 			TC1309	515599R			EMERGENCY LANDING MADE DUE TO OIL LOSS AND PRESSURE LOSS. FOUND OIL LOSS AT APPROXIMATELY 1 QUART PER MINUTE AT 1,000 R	PM. REMOVED PROPELLER AND FOUND FLANGE CRACKED 50 PERCENT AROUND CIRCUMFERENCE OF FLANGE. FAILURE OF CRANKSHAFT (LOSS 	OF PROPELLER) WAS VERY LIKELY TO HAPPEN AT ANY TIME. NOTE: THIS INSTALLATION IS A COLEMILL CONVERSION. VAR CRANKSHAFT	 NOT INSTALLED.			1	L	7	2 	3O	3	O		3A16 	E5CE				 
1995061600134	19950616	00134		1995	6	16	95ZZZX2887 	4	19950424	G	6122	20749	FLYWEIGHT 	MCAULY 	C290D3T16 															GOVERNOR	BROKEN 	B			EX2R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	15					890361					SB 214 NOT C/W. FLYWEIGHT BROKE IN-FLIGHT AND DESTROYED GOVERNOR.																			 
1995061600135	19950616	00135		1995	6	16	95ZZZX2888 	1	19950510	G	3340	WRM39	MOTOR 	WHELEN 	WRML14 															BEACON	SEPARATED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	11					H9					WHILE INSTALLING NEW PART, BEACON MOTOR SEPARATED BETWEEN MOTOR AND TRANSMISSION. FOUND RIVETS NOT INSTALLED RIGHT.																			 
1995061600136	19950616	00136	SO 	1995	6	16	95ZZZX2889 	2	19950510	G	8530	649317CPA1	CYLINDER 			CESSNA	210 	210L 	2073448	CE 	CONT 	O520 	IO520L 	17032	SO 					NR 4	CRACKED 	B			AHTR	A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			GL	11	8935M					21059635	554683H			ENGINE OPERATION BECAME ROUGH IN-FLIGHT. AIRCRAFT WAS LANDED TO INVESTIGATE THE PROBLEM. FOUND CYLINDER NR 4 HAD CRACK	ED AND THE HEAD HAD SEPARATED.					1	H	7	1 	3O	3	O		3A21 	E5CE				 
1995061600137	19950616	00137	SO 	1995	6	16	95ZZZX2890 	1	19950423	G	2720	96212000	TORQUE TUBE 			PIPER 	PA34 	PA34200T 	7103406	SO 										RUDDER	HOLES ELONGATED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4490F	5470 				347670339				INSPECTION FOUND RUDDER TORQUE TUBE HOLES ARE ELONGATED WHERE TORQUE TUBE FITTING ATTACHES. NOTE: PART HAS 1584 HOURS 	ON IT SINCE STEEL FITTING WAS INSTALLED PER SB 899.					1	L	7	2 	3O				A7SO 					 
1995061600138	19950616	00138	CE 	1995	6	16	95ZZZX2891 	1	19950501	G	2751	12801111	CONTROL CABLE 			CESSNA	182 	R182 	2072734	CE 										FLAP INDICATOR	FRAYED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	9292R	588 				R18200681				FLAP INDICATOR CABLE HAS A RECURRING PROBLEM WITH THIS CABLE. FIRST ONE LASTED 1550 HRS, NR 2 1949 HRS, NR 3 APPROXIMAT	ELY 1600 HRS. IT APPEARS CABLE RUBS ON HOUSING WHERE CABLE EXITS AND ATTACHES TO FLAP CABLE BECAUSE OF ANGLE. SUGGEST:	 TAPER WASHERS TO ALIGN CABLE. SECOND M OR D SUBMITTED FOR SAME PROBLEM ON AIRCRAFT.				1	H	7	1 	3O			RT	3A13 					 
1995061600139	19950616	00139	SO 	1995	6	16	95ZZZX2892 	2	19950530	G	8520	633620	CRANKSHAFT 			CESSNA	340 	340CESSNA 	2076404	CE 	CONT 	O520 	TSIO520J 	17040	SO 					MAIN JOURNAL	BROKE 	D				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			Y			ENGINE STOPPAGE 			CR	CRUISE 	1			EA	03	7632Q	6532 	440 			3400236	218750			ENGINE FAILURE - LEVEL AT 12,000 FEET MSL CRUISE POWER. RAPID REDUCTION IN RPM, M.A.P., AND O.P., THEN PUT IN FEATHER. 	 UPON LANDING, MECHANIC DETERMINED THAT NR 1 AND NR 2 CYLINDERS PISTONS DO NOT MOVE WHEN CRANKSHAFT/PROPELLER IS ROTATED	. ALTHOUGH THE ENGINE HAS YET TO BE DISASSEMBLED, IT CAN BE ASSUMED THE CRANKSHAFT IS PROBABLY BROKEN AT A REAR MAIN JO	URNAL.			1	L	7	2 	3O	3	O		3A25 	E8CE				 
1995061600140	19950616	00140	CE 	1995	6	16	95ZZZX2893 	1	19950518	G	7603	5038901229	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										NR 2 ENG THROTT	BROKEN 	B			WC7R	O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			GL	25	4098S					TH600				5,323,8 HOBBS TIME. PILOT REPORTED NR 2 ENGINE THROTTLE CABLE BROKEN AT FUEL INJECTION SERVO, CABLE WAS REPLACED WITH A	 NEW PART.					1	L	7	2 	3O			 	3A16 					 
1995061600141	19950616	00141	SO 	1995	6	16	95ZZZX2894 	1	19950523	G	3230	7642603	DRAG BRACE 			PIPER 	PA28 	PA28RT201T 	7102817	SO 										NLG	BROKEN 	B	S	A	SL5R	O	A			OTHER 	UNSCHED LANDING 			J			WARNING INDICATION 			CR	CRUISE 	1			NE	03	3071N	3413 				28R7931060				LOUD 'BANG' HEARD DURING CRUISE FLIGHT AND RED LG WARNING LIGHT CAME ON. EXTENDED LANDING GEAR, RETURNED TO HOME AIRPOR	T AND LANDED NORMALLY. FOUND NOSE LANDING GEAR UPPER DRAG BRACE BROKEN IN HALF JUST FORWARD OF HYDRAULIC ACTUATOR ATTAC	HMENT. INSTALLED NEW PN 76426-803 LINK/BRACE ASSEMBLY AND CHECKED RIGGING. PIPER SB 724A ADDRESSES THIS SUBJECT. SUBM	ITTER SUGGESTS THAT AFTER 2,000 HOURS, THIS PART BE DYE CHECKED AND EACH 200 HOURS THEREAFTER UNTIL NEW BEEFED-UP PART I	S INSTALLED.		1	L	7	1 	3O				2A13 					 
1995061600142	19950616	00142	EU 	1995	6	16	95ZZZX2895 	1	19950519	G	5102	10108	O-RING 		10105 	COLT 	240A 	240A 	2300180	EU 										BURNER HOSE	GOUGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	2FOR									VISUAL INSPECTION REVEALED GOUGES IN SURFACE OF O-RING IN FEMALE QUICK DISCONNECT FUEL TANK TO BURNER HOSE COUPLING. CA	USE IS SUSPECTED TO BE IMPROPER ALIGNMENT OF COUPLING DURING MATING. SUBMITTER RECOMMENDS VISUAL INSPECTION DURING EVER	Y PRE-FLIGHT INSPECTION. THESE O-RINGS ARE LOCATED IN A FEMALE TEMA 3800 COUPLING PN 10105, MFG SKOVDE, SWEDEN.				1	B	0	0 					B3EU 					 
1995061600143	19950616	00143	CE 	1995	6	16	95ZZZX2896 	1	19950425	G	5343	05411956	GEAR SUPPORT 			CESSNA	172 	172P 	2072436	CE 										RT FS 56-65	SCREWS LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	52139	4946 				17274421				UPPER SCREWS ATTACHING INBOARD LANDING GEAR SUPPORT TO FLOOR FREQUENTLY FOUND LOOSE. SUBMITTER SUGGESTS THIS SHOULD BE 	INSPECTED AT INTERVALS NOT TO EXCEED 100 HOURS. AIRFAME TOTAL TIME 4946.					1	H	7	1 	3O			NT	3A12 					 
1995061600144	19950616	00144	CE 	1995	6	16	95ZZZX2897 	1	19950425	G	5343	0541A55	GEAR SUPPORT 			CESSNA	172 	172P 	2072436	CE 										LT FS 56-65	SCREWS LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	52139	4946 				17274421				UPPER SCREWS ATTACHING INBOARD LANDING GEAR SUPPORT TO FLOOR FREQUENTLY FOUND LOOSE. SUBMITTER SUGGESTS THIS SHOULD BE 	INSPECTED AT INTERVALS NOT TO EXCEED 100 HOURS. AIRFAME TOTAL TIME 4946.					1	H	7	1 	3O			NT	3A12 					 
1995061600145	19950616	00145	SO 	1995	6	16	95ZZZX2898 	1	19950530	G	3230		SCISSORS 			PIPER 	PA34 	PA34200T 	7103406	SO 										NLG	BOLT BROKE 	G				O				OTHER 				O			OTHER 			LD	LANDING 	1			GL	05	3489M					347870113				BOLT AT APEX OF SCISSORS SEIZED IN BOTH HALVES AND THEN BROKE UPON LANDING CAUSING A LOSS OF NOSE WHEEL STEERAGE. THIS 	JOINT DOES NOT HAVE GREASE FITTINGS, SO, THEREFORE, SHOULD BE OILED FREQUENTLY SO THAT THE BOLT CAN BE ROTATED EASILY.					1	L	7	2 	3O				A7SO 					 
1995061600146	19950616	00146	CE 	1995	6	16	95ZZZX2899 	1	19950526	G	3213		TRUNNION 			CESSNA	210 	P210N 	2073454	CE 										NLG	FAILED 	D				O				OTHER 				O			OTHER 			AP	APPROACH 	1			SO	03	4994K	2926 				P21000392				A LOUD BANG AND SUDDEN JAR OF THE RUDDER PEDALS WAS NOTED WHEN LANDING GEAR WAS EXTENDED FOR NORMAL LANDING. NOSE GEAR 	COLLAPSED DURING ROLL-OUT. CESSNA SEB94-19 HAD NOT BEEN COMPLIED. INSPECTION REVEALED LOWER TRUNNION FAILED AS DESCRIB	ED IN THE SB. SUBMITTER SUGGESTS POSSIBLE CONTRIBUTING FACTORS, ASIDE FROM GROUND HANDLING, MAY BE THE ADDED WEIGHT OF 	THE JAVELIH MODIFIED ENGINE STC AND NOSE FIRST LANDINGS. THIS NOSE GEAR SHOWS NO OTHER SIGNS THAT TOW LIMITS HAD BEEN E	XCEEDED.		1	H	7	1 	3O				3A21 					 
1995101900005	19951019	00005		1995	10	19	95ZZZX2900 	4	19950526	G	2216		TRIM SERVO 	KING 		PIPER 	PA31 	PA31350 	7103110	SO 										ELEV TRIM TAB	CABLE MISROUTED 	B			UFAR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	25	44AC	5199 				318052147				DURING ROUTINE INSPECTION, THE ELEVATOR TRIM TAB RIGGING WAS FOUND OUT OF LIMITS. AFTER REFERRING TO AUTOPILOT INSTALLA	TION MANUAL, IT WAS DETERMINED THE ELECTRIC TRIM SERVO HAD THE TRIM CABLE IMPROPERLY ROUTED AROUND ITS CAPSTAND AND PULL	EYS. THE ROUTING CAUSED THE TURNBUCKLES TO HAVE TO BE LOOSENED TOO EXTREME TO ALLOW PROPER CABLE TENSIONS AND THE FORWA	RD AND AFT BARREL WRAPS WOULD NOT ALIGN PER SM.			1	L	7	2 	3O				A20SO 					 
1995061600147	19950616	00147	CE 	1995	6	16	95ZZZX2901 	1	19950526	G	3213	514110314	TRUNNION 			CESSNA	402 	402C 	207590R	CE 										RT MLG	CRACKED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	2714B	16399				402C0210				PILOT REPORTED RT STRUT WAS RIDING LOW. MAINTENANCE DISCOVERED A CRACK APPROXIMATELY 4 INCHES LONG ALONG SIDE THE CAST 	MARK OR SEAM IN THE UPPER GEAR TRUNNION. DURING DISASSEMBLY, NOTED THE STRUT BARREL WAS ALSO CRACKED. PILOT REPORTED N	O UNUSUAL LANDINGS AND THE LANDING GEAR WAS INSPECTED APPROXIMATELY 4 HOURS EARLIER DURING AN ACCEPTANCE INSPECTION OF T	HE AIRPLANE. NO CRACK WAS NOTED DURING THE INSPECTION.			1	L	7	2 	3O				A7CE 					 
1995061600148	19950616	00148	CE 	1995	6	16	95ZZZX2902 	1	19950522	G	3010		ANTI-ICE SYSTEM 			BEECH 	36 	A36 	1151604	CE 										WING ANTI-ICE	CONTAMINATED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	11	3205V	85 				E2899				AEROSPACE SYSTEMS AND TECHNOLOGY, INC., TKS ANTI-ICE SYSTEM WAS INSTALLED IN THIS AIRCRAFT IAW STC SA2239C3 AND A 337 FO	RM. A BLADDER IN THE RIGHT WING HOLDS THE TKS FLUID WITH A FILLER CAP ON THE TOP WING SURFACE. THERE ARE WARNINGS ON E	ITHER SIDE OF THE FILLER CAP OF WHAT FLUID SHOULD BE PUT IN THIS OPENING AND HOW MUCH. DURING AN ANNUAL INSPECTION IT W	AS FOUND (THE TKS BLADDER) TO BE FULL WITH AUGAS. THIS IS POTENTIALLY EXTREMELY DANGEROUS AND SUGGEST LOCKING CAPS OR A	NOTHER WAY OF WARNING PLACARDS.		1	L	7	1 	3O				3A15 					 
1995061600150	19950616	00150	CE 	1995	6	16	95ZZZX2904 	1	19950125	G	2510	07006335	BELLCRANK 			CESSNA	185 	A185F 	2072821	CE 										PILOT SEAT	FAILED 	B		A	CNZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	9497N	11284				18504366				WHEN LEANING BACK TO ADJUST SEAT POSITION, BELLCRANKS (LT) AND (RT) BROKE AT SMALL ATTACHMENT HOLE ALLOWING SEAT BACK WI	TH UPPER FRAME ASSEMBLY TO FALL BACKWARDS. THE BREAK WAS CLEAN AND SHOWING NO PRIOR CRACK PROGRESSION UNTIL FAILURE. A	IRCRAFT TC 3124.				1	H	7	1 	3O				3A24 					 
1995061600151	19950616	00151	CE 	1995	6	16	95ZZZX2905 	1	19950518	G	2720	4001074	CONTROL CABLE 			CESSNA	140 	140 	2071602	CE 										RUDDER	FRAYED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	1859V	3070 				14038				BOTH RUDDER CABLES FOUND FRAYED 6-10 STRANDS AT FORWARD-MOST PULLEYS JUST AFT OF RUDDER PEDALS. TWO MONTHS PREVIOUSLY, 	SAME DEFECT FOUND IN EXACT LOCATION ON A CESSNA 120. SUBMITTER SUGGESTS 100 HR/ANNUAL INSPECTION BE REQUIRED.					1	H	7	1 	3O			NC	A768 					 
1995061600152	19950616	00152	SO 	1995	6	16	95ZZZX2906 	2	19950504	G	7310	635158S4S32	HOSE ASSY 			BEECH 	33 	F33A 	1151425	CE 	CONT 	O520 	IO520BB 	17032	SO 					FUEL INJ	LEAKING 	B		A	CGHR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	03	8132N	404 				CE1585	578743			PILOT REPORTS THE ENGINE COULD NOT BE LEANED AT ALTITUDE AND THAT IT WOULD NOT IDLE OR CONTINUE RUNNING AT SPEEDS BELOW 	800 RPM. FOUND THE FLEXIBLE FUEL LINE LEAKING THROUGH THE BRAIDED EXTERIOR ALONG ITS ENTIRE LENGTH. THIS LINE SUPPLIES	 FUEL FROM THE FUEL INJECTOR TO THE FUEL FLOW TRANSMITTER HARD LINE. IT IS ROUTED BETWEEN NR 3 AND NR 5 CYLINDERS.				1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995061600153	19950616	00153	CE 	1995	6	16	95ZZZX2907 	1	19950426	G	2820	35921176	PLUG 		35921171 	BEECH 	35 	A35 	1151504	CE 										FUEL UNIT	LEAKING 	G		A		A				UNSCHED LANDING 				Y	K		ENGINE STOPPAGE 	FLUID LOSS 		NR	NOT REPORTED 	1			SO	11	8461A					D2012				AIRCRAFT EXPERIENCED FUEL STARVATION - MADE A FORCED LANDING IN A FIELD. FOUND TWO LOOSE PLUGS PN 35-921176 (UPPER AND 	LOWER) WERE LEAKING FUEL AND SUCKING AIR. WHEN FUEL TANKS WERE SWITCHED, THE FUEL PRESSURE WOULD DROP BELOW 5 PSI AND N	EVER RECOVER. SUBMITTER SUGGESTS BRASS PLUGS BE CHECKED ON FUEL UNIT ASSEMBLY 35-921171 FOR TIGHTNESS DURING ANNUAL INS	PECTIONS.			1	L	7	1 	3O				A777 					 
1995061600218	19950616	00218	SW 	1995	6	16	95ZZZX2914 	1	19950522	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350AL		347 			51429				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 347.3 HOURS.				1	G	7	1 	3U				H2SW 					 
1995061600219	19950616	00219	SW 	1995	6	16	95ZZZX2915 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350AL		347 			51429				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 347.3 HOURS.				1	G	7	1 	3U				H2SW 					 
1995061600220	19950616	00220	SW 	1995	6	16	95ZZZX2916 	1	19950522	G	6230	206010335001	LINK ASSY 		106010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	222LM		419 			1916				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 418.5 HOURS.				1	G	7	1 	3U				H2SW 					 
1995061600221	19950616	00221	SW 	1995	6	16	95ZZZX2917 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	222LM		419 			1916				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 418.5 HOURS.				1	G	7	1 	3U				H2SW 					 
1995061600222	19950616	00222	SW 	1995	6	16	95ZZZX2918 	1	19950522	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	175AL	309 				52117				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 309.1 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1995061600223	19950616	00223	SW 	1995	6	16	95ZZZX2919 	1	19950522	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	175AL	309 				52117				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. TT ON WORN PARTS 309.1 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1995061600224	19950616	00224	EU 	1995	6	16	95ZZZX2920 	1	19950511	G	6220	704A33633109	SPHERICAL STOP 		355A31000106	AEROSP	AS355 	AS355F 	8680806	EU 										M/R HEAD	DELAMINATED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57936	509 			3084	5129				POST FLIGHT FOUND 3 EACH SPHERICAL STOPS WITH RUBBER BULGING AND DELAMINATED BEYOND LIMITS.						1	G	7	2 	3U				H11EU 					 
1995061600225	19950616	00225	EU 	1995	6	16	95ZZZX2921 	1	19950511	G	6220	704A33633109	SPHERICAL STOP 		355A31000106	AEROSP	AS355 	AS355F 	8680806	EU 										M/R HEAD	DELAMINATED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57936	509 			3081	5129				POST FLIGHT FOUND 3 EACH SPHERICAL STOPS WITH RUBBER BULGING AND DELAMINATED BEYOND LIMITS.						1	G	7	2 	3U				H11EU 					 
1995061600226	19950616	00226	EU 	1995	6	16	95ZZZX2922 	1	19950511	G	6220	704A33633109	SPHERICAL STOP 		355A31000106	AEROSP	AS355 	AS355F 	8680806	EU 										M/R HEAD	DELAMINATED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57936	509 			3080	5129				POST FLIGHT FOUND 3 EACH SPHERICAL STOPS WITH RUBBER BULGING AND DELAMINATED BEYOND LIMITS.						1	G	7	2 	3U				H11EU 					 
1995061600227	19950616	00227	NE 	1995	6	16	95ZZZX2923 	1	19950509	G	3240	9544325	PLATE 		50034261 	SKRSKY	S76 	S76A 	8143006	NE 										BRAKE ASSY	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	764AL		5222 			760027				DURING SHOP TEAR DOWN FOR REPAIR AND INSPECTION OF MAIN GEAR ASSEMBLY, FOUND BACK PLATE WORN PAST LIMITS.						1	G	7	2 	3U				H1NE 					 
1995061600228	19950616	00228	NE 	1995	6	16	95ZZZX2924 	1	19950509	G	3242	5003441	PRESSURE PLATE 		50034261 	SKRSKY	S76 	S76A 	8143006	NE 										BRAKE ASSY	WARPED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	764AL		5222 			760027				DURING SHOP TEAR DOWN FOR REPAIR AND INSPECTION OF MAIN GEAR ASSEMBLY, FOUND PLATE WARPED FROM HEAT AND CORROSION DAMAGE	.					1	G	7	2 	3U				H1NE 					 
1995061600229	19950616	00229	NE 	1995	6	16	95ZZZX2925 	1	19950509	G	6730	30006773	GLAND 			SKRSKY	S76 	S76A 	8143006	NE 										SERVO	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	764AL		2249 			760027				IN SHOP DURING INSPECTION AND REPAIR OF ACTUATOR, FOUND I.D. OF GLANDS, 2 EACH, WORN PAST LIMITS BY MOVEMENT OF PISTONS 	THROUGH GLANDS.					1	G	7	2 	3U				H1NE 					 
1995061600230	19950616	00230	NE 	1995	6	16	95ZZZX2926 	1	19950509	G	3240	5003917	ROTATING DISK 		50034261 	SKRSKY	S76 	S76A 	8143006	NE 										BRAKE ASSY	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	764AL		5222 			760027				DURING SHOP TEAR DOWN FOR REPAIR AND INSPECTION OF MAIN GEAR ASSEMBLY, FOUND DISK WORN PAST LIMITS AND DRIVE LUGS WORN P	AST LIMITS.					1	G	7	2 	3U				H1NE 					 
1995061600231	19950616	00231	NE 	1995	6	16	95ZZZX2927 	1	19950509	G	3213	1945E9	BEARING 		1945E100A 	SKRSKY	S76 	S76A 	8143006	NE 										STRUT ASSY	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	764AL		5222 			760027				DURING SHOP TEAR DOWN FOR REPAIR AND INSPECTION DUE TO WORN BUSHINGS, FOUND CORROSION DAMAGE TO BEARING SURFACE.						1	G	7	2 	3U				H1NE 					 
1995061600232	19950616	00232	NE 	1995	6	16	95ZZZX2928 	1	19950509	G	3213	1945E41	PIN 		195E100A 	SKRSKY	S76 	S76A 	8143006	NE 										STRUT ARM	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	764AL					760027				DURING SHOP TEAR DOWN FOR INSPECTION/REPAIR DUE TO WORN BUSHINGS, FOUND TORQUE ARM PIN PLATING CHIPPED OFF - CORROSION D	AMAGE.					1	G	7	2 	3U				H1NE 					 
1995061600233	19950616	00233	NE 	1995	6	16	95ZZZX2929 	1	19950509	G	3213	1945E2	CYLINDER 		1945E100A 	SKRSKY	S76 	S76A 	8143006	NE 										STRUT ASSY	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	764AL	11271	5222 		CPE0669JK	760027				DURING SHOP TEAR DOWN FOR INSPECTION/REPAIR DUE TO WORN BUSHINGS, FOUND STRUT CYLINDER I.D. WORN PAST LIMITS. SUSPECT C	AUSE - POSSIBLE OIL CONTAMINATION.					1	G	7	2 	3U				H1NE 					 
1995061600234	19950616	00234	NE 	1995	6	16	95ZZZX2930 	1	19950509	G	3213	1945E18	SCRAPER CAP 		1945E100A 	SKRSKY	S76 	S76A 	8143006	NE 										STRUT ASSY	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	764AL		5222 			760027				DURING SHOP TEAR DOWN FOR INSPECTION/REPAIR DUE TO WORN BUSHINGS, FOUND STRUT CORROSION DAMAGE BEYOND LIMITS.						1	G	7	2 	3U				H1NE 					 
1995061600235	19950616	00235	WP 	1995	6	16	95ZZZX2931 	1	19950601	G	6420	369D23040	BRACKET 			HUGHES	369 	369D 	4470706	WP 										T/R WHIP DAMPER	CHAFED 	B			EOOR	K				NONE 				E			VIBRATION/BUFFET 			NR	NOT REPORTED 	1			AL	03	8639F	6179 				1280431D				PILOT COMPLAINED ABOUT A T/R VIBRATION. FOUND T/R WHIP DAMPER BRACKET CHAFED BADLY FROM DAMPER ACTION. REPLACED PART.						1	G	7	1 	3U				H3WE 					 
1995061600236	19950616	00236		1995	6	16	95ZZZX2932 	4	19950605	G	3421	RCA26BK1	GYRO 	RCALLEN 		HUGHES	369 	369D 	4470706	WP 										COCKPIT HORIZ	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R				3000	1159D				PILOT COULD NOT ADJUST THE GYRO WITH THE CAGING KNOB. REMOVED AND REPLACED UNIT AND SENT IN FOR REPAIR.						1	G	7	1 	3U				H3WE 					 
1995061600237	19950616	00237	EU 	1995	6	16	95ZZZX2933 	1	19950510	G	3230	1541488	CONTROL TUBE 			BOLKMS	105 	BO105CBS 	5626008	EU 										MLG	CHAFED 	B			CZ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	495HL					S817				CLAMP FOR BUNGEE PN 105-4100145 WAS ADJUSTED IMPROPERLY WHICH ALLOWED IT TO CHAFE INTO PN 105-41488 CONTROL TUBE.						1	G	7	2 	3U			NC	H3EU 					 
1995061600322	19950616	00322	WP 	1995	6	16	95ZZZX2934 	1	19950501	G	7712	369H45267	TORQUE GAUGE 			HUGHES	369 	369D 	4470706	WP 										COCKPIT	FLUCTUATES 	B			EOOR	O				OTHER 				O			OTHER 			CR	CRUISE 	1			AL	03	4571V				1	4904870				TORQUE GAUGE FLUCTUATES IN-FLIGHT. REMOVED AND REPLACED GAUGE, PART SENT IN FOR REPAIR.						1	G	7	1 	3U				H3WE 					 
1995061600323	19950616	00323	NM 	1995	6	16	95ZZZX2935 	1	19950527	G	3212	A0501	FLOAT STABILIZER			ROBSIN	R22 	R22MARINER 		NM 										MOUNT TUBE	DEPARTED 	D		A		A				UNSCHED LANDING 				D			INFLIGHT SEPARATION 			NR	NOT REPORTED 	1			NE	01	544CC					1885M				RETURN FROM 1.0 HR FLIGHT, FLOAT STABILIZER LOST. DAMAGE TO HELICOPTER. REPLACED PART, PUT HELICOPTER BACK INTO SERVI	CE. NO EVIDENCE OF PROGRESSIVE CRACK OR IMPACT DAMAGE TO HELICOPTER.					1	G	7	1 	3O				H10WE 					 
1995061600324	19950616	00324	EU 	1995	6	16	95ZZZX2936 	1	19950607	G	5610	1172416386	WINDOW 			BOLKMS	117 	BK117B2 	5626013	EU 										PILOT'S SLIDER	DEPARTED 	B			BAQR	O				OTHER 				D			INFLIGHT SEPARATION 			NR	NOT REPORTED 	1			EA	03	945ME	32 				7235				RIGHT SLIDING WINDOW (PILOT'S DOOR) DEPARTED AIRCRAFT. PILOT REPORTED THE AIR TURBULENCE REMOVED THE WINDOW FROM ITS TR	ACKS. AIRCRAFT WAS GROUNDED UNTIL A REPLACEMENT WINDOW WAS AVAILABLE AND A HIDDEN DAMAGE INSPECTION WAS PERFORMED. MIN	OR ALTERATIONS TO THE DESIGN MAY BE INCORPORATED TO PREVENT THE HANDLE FROM HITTING THE SOLID WINDOW, WHICH MAY HAVE SET	 UP A CRACK IN THE HANDLE ASSY WHICH IS ALSO USED AS THE SLIDE STOP.			1	G	7	2 	3U			NC	H13EU 					 
1995061600325	19950616	00325	GL 	1995	6	16	95ZZZX2937 	1	19950526	G	7922	75944	VALVE 			ENSTRM	F28 	280F 	3300550	GL 										THERMO BYPASS	CRIMP NUT LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	199TV	3392 				1510				ENGINE WAS JUST RECENTLY OVERHAULED BY AN EASTROM DEALER IN SPRINGFIELD, MO. ON THE FIRST 50-HOUR INSPECTION, THE VERNA	THERM VALVE, PN 75944, WAS REMOVED FOR INSPECTION TO COMPLY WITH LYC SB518C. THE VALVE HAD A LOOSE CRIMP NUT AND VALVE 	CONE HAD WORN GROOVE. IT IS VERY LIKELY THIS WAS NOT REPLACED AT MAJOR OVERHAUL AND WAS THE ORIGINAL WITH 3391.5 HRS. R	ECOMMEND THAT SB518 BE AN AD SO PEOPLE COMPLY WITH IT.			1	G	7	1 	3O				H1CE 					 
1995061600326	19950616	00326	NE 	1995	6	16	95ZZZX2938 	2	19950605	G	7321		FUEL CONTROL 			CESSNA	425 	425 	2076018	CE 	PWA 	PT6 	PT6A112 	52043	NE 					ROD ENDS	REQ LUBE 	B			EIPR	O				OTHER 				O			OTHER 			DE	DESCENT 	1			WP	07	6773L					4250037	PCE12119			HOBBS 115.1. TT A/F 4861.2. ON DESCENT, LEFT ENGINE DID NOT RESPOND TO POWER REDUCTION. TROUBLESHOT, CLEANED, AND LUB	RICATED F.C.U., ROD ENDS, AND LINKGAGE. OPS CHECK OKAY. FLIGHT CHECK OKAY. ENGINE T.S.O. 1369.7.					1	L	7	2 	3T	3	T	RT	A7CE 	E4EA				 
1995061600328	19950616	00328	WP 	1995	6	16	95ZZZX2940 	2	19950605	G	7230	30720122	BLADE 			AMD 	FALC50	FALCON50MYST	2730106	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					2ND STAGE LP	SEPARATED 	D				O				OTHER 				O			OTHER 			CR	CRUISE 	1			GL	05	4350M	6299 				142	76556			SECOND STAGE L.P. BLADE SEPARATED IN STRESS RUPTURE, 4712 CYCLES. OCCURRED ON 1-31-95 IN-FLIGHT. REF: SB TFE 731-72-3	556.					2	L	7	3 	4F	4	F		A46EU 	E6WE				 
1995061600329	19950616	00329	WP 	1995	6	16	95ZZZX2941 	2	19950605	G	7230	30720122	BLADE 			AMD 	FALC50	FALCON50MYST	2730106	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					2ND STAGE LP	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	05	4350M	6352 				142	76568			OCCURRENCE 4-26-95. SECOND STAGE L.P. BLADE FAILURE IN-FLIGHT TO EWR. REF: SB TFE731-72-3556 STRESS RUPTURE.						2	L	7	3 	4F	4	F		A46EU 	E6WE				 
1995061600330	19950616	00330	SO 	1995	6	16	95ZZZX2942 	1	19950515	G	2750	MS2764120	BEARING 			LKHEED	282 	C130A 	5262502	SO 										FLAP DRIVE	CHAFED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	130SA					3035				FLAP DRIVE SHAFT BEARING WAS INSTALLED IN SUPPORT BRACKET AND SUPPORT BRACKET WAS REVERSED CAUSING SHAFT BOLT TO CUT INT	O BEARING. BEARING HAD TO BE REPLACED AND SUPPORT WAS INSTALLED IAW AIR FORCE TECH ORDER.					2	H	7	4 	4T				A31NM 					 
1995061600331	19950616	00331	SO 	1995	6	16	95ZZZX2943 	1	19950530	G	2730	8281530	CONTROL CABLE 			PIPER 	PA46 	PA46310P 	7104605	SO 										ELEV TRIM	FRAYED 	B		A	LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	4323B	2280 				468408009				DURING ANNUAL INSPECTION, FOUND ELEVATOR TRIM CABLE FRAYED AT PITCH SERVO CAPSTAN. THIS IS SECOND AIRCRAFT THAT WE KNOW	 OF WITH THIS CONDITION. RECOMMEND A MANDATORY INSPECTION FOR THIS COMPONENT. (FOR AIRCRAFT WITH HIGH TIME).					1	L	7	1 	3O			RT	A25SO 					 
1995061600332	19950616	00332	SO 	1995	6	16	95ZZZX2944 	1	19950525	G	7120		MOUNT 			PIPER 	PA32 	PA32R301T 	7103220	SO 										RT ENGINE	RUSTED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	8342F	1200 				32R8329006				DURING ANNUAL INSPECTION NOTED RUSTING OF RT ENGINE MOUNT TUBE LOCATED JUST AFT OF WASTEGATE VALVE, CLEANED, TREATED, AN	D APPLIED PROTECTIVE PAINT TO MOUNT TUBE. SUBMITTER SUGGESTS PIPER DEVELOP A HEAT SHIELD TO CORRECT THIS CONDITION.					1	L	7	1 	3O				A3SO 					 
1995061600333	19950616	00333	CE 	1995	6	16	95ZZZX2945 	1	19950530	G	8120	4706889007	CONTROLLER 			CESSNA	206 	TU206G 	2073357	CE 										TURBO	MALFUNCTION 	D				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			NM	11	9438M		682 		7D40130	U20604546				ON SECOND TAKEOFF DURING CLIMB, MAN. PRESS. DECAYED TO 27 INCHES HG. CLIMB CONTINUED AND POWER SLOWLY CAME BACK - NEXT 	TAKEOFF WAS NORMAL. REPLACED TURBO CONTROLLER AND ALL HOSES TO AND FROM WASTEGATE, ALSO, CONTROLLER DRAIN HOSE. A/C RA	N TO TEST, APPEARED NORMAL. MADE TWO TAKEOFFS, FULL POWER, NO DEFECTS NOTED - THIS IS THE THIRD CONTROLLER THIS ENG HAS	 HAD. SUBMITTER STATED NOT SURE WHAT CAUSED THE PROBLEM OR IF IT IS CURED.			1	H	7	1 	3O				A4CE 					 
1995061600334	19950616	00334	SO 	1995	6	16	95ZZZX2946 	2	19950530	G	8530	633728	INTAKE TUBE 			CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					NR 6 CYL	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	44811					421B0802	21033772H			ON 100-HOUR INSPECTION, FOUND FUEL STAIN NR 6 INT PIPE - FOUND CRACKED 60 PERCENT OF FLANGE - REPLACED WITH NEW PN 63372	8 TUBE - THIS ENG HAS 684 HRS SINCE O/H AND APPEARS TO BE A SPRAY CAN OVERHAUL.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995061600336	19950616	00336	SO 	1995	6	16	95ZZZX2948 	1	19950510	G	7922	53E19600	VALVE 			PIPER 	PA32 	PA32R301T 	7103220	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			ZYNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	3327P	879 			7596	3213013				CRIMP NUT LOOSE AND ABOUT ONE-HALF WAY OFF. FOUND WHILE COMPLYING WITH LYC SB 518C.						1	L	7	1 	3O				A3SO 					 
1995061600337	19950616	00337	SO 	1995	6	16	95ZZZX2949 	1	19950502	G	7922	75944	VALVE 			PIPER 	PA28 	PA28181 	7102807	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			ZYNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	9083K	1922 			116231	287890174				CRIMP NUT LOOSE. FOUND WHILE COMPLYING WITH LYC SB 518B.						1	L	7	1 	3O				2A13 					 
1995061600338	19950616	00338	EA 	1995	6	16	95ZZZX2950 	2	19950503	G	7414	10382585	CONTACT ASSY 		D6LN3000 	PIPER 	PA32 	PA32RT300 	7103215	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					RT MAG	TIP BROKEN 	B			CQVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	36590	28 			8325063	32R7885197	L1831648A			PILOT NOTED A DEAD MAG IN THE RIGHT POSITION. INVESTIGATION REVEALED THE POINTS NOT OPENING. CONTACT ASSEMBLY HAS TIP 	BROKEN OFF. PART TOTAL TIME 30 HRS. TCM IGNITION SB 651 COVERS THIS, BUT IS NOT WELL KNOWN. RECOMMEND ALERT BE ISSUED	.				1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995061600339	19950616	00339	SO 	1995	6	16	95ZZZX2951 	1	19950526	G	7922	75944	VALVE 			PIPER 	PA28 	PA28161 	7102803	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	47837	1418 				287816141				DURING AN ANNUAL INSPECTION, THE VERNATHERM VALVE WAS REMOVED FOR INSPECTION TO COMPLY WITH LYCOMING SB 518C. THE VALVE	 PN 75944 HAD A LOOSE CRIMP NUT AND VALVE CONE HAD A WORN GROOVE. INSTALLED NEW VALVE PN SL53E19600 WHICH HAS DRILLED N	UT AND ROLL PIN. RECOMMEND SB 518 BECOME AN AD.				1	L	7	1 	3O				2A13 					 
1995061600341	19950616	00341	CE 	1995	6	16	95ZZZX2953 	1	19950413	G	7111	0752609201	COWL FLAP 			CESSNA	182 	182E 	2072712	CE 										RT COWL	DEPARTED 	D				A				UNSCHED LANDING 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			NM	03	9232X					18253632				PILOT WAS FLYING THE AIRCRAFT EN ROUTE, 15 MINUTES INTO THE FLIGHT, A THUMP WAS HEARD, PILOT RETURNED TO THE DEPARTING A	IRPORT WITHOUT FURTHER INCIDENT. INSPECTION AND INVESTIGATION REVEALED THE RIGHT COWL FLAP HAD TOTALLY SEPARATED AND DE	PARTED THE AIRCRAFT, COWL FLAP HINGE PIN MISSING AND RIGHT COWL FLAP CABLE BROKEN AT THE THREADED PORTION OF THE COWL FL	AP. NO DAMAGE TO THE AIRCRAFT. SUBMITTER SUGGESTS CLOSER AREA TO INSPECT ANYTIME AT 100-HOUR, OIL CHANGE, OR WHENEVER 	COWLING IS REMOVED.		1	H	7	1 	3O			NT	3A13 					 
1995061600342	19950616	00342	CE 	1995	6	16	95ZZZX2954 	1	19950520	G	3230	HR8H5ES	ROD END 			CESSNA	310 	310Q 	2074242	CE 										RT MLG DOWNLOCK	BROKE 	G				K				NONE 				O			OTHER 			LD	LANDING 	1			EA	07	69743	55 				310Q0955				LOWER ROD END ON DOWNLOCK BROKE AT BASE OF SHAFT ALLOWING RIGHT MAIN LANDING GEAR TO COLLAPSE ON LANDING.						1	L	7	2 	3O				3A10 					 
1995061600343	19950616	00343	CE 	1995	6	16	95ZZZX2955 	1	19950531	G	7810	1099500001	EXHAUST STACK 			BEECH 	90 	C90A 	1152911	CE 										RT ENG RT INBD	BROKE 	B			PAIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	415P	570 				LJ1345				RIGHT ENGINE, LEFT EXHAUST STACK, ELBOW FOR HEATED LIP BROKE OFF. SECOND TIME IN 150 HOURS. PROPELLER PREVIOUSLY BALAN	CED BEFORE PROBLEMS STARTED. MINOR DAMAGE TO COWLING.					1	L	7	2 	3T			RT	3A20 					 
1995061600344	19950616	00344	EA 	1995	6	16	95ZZZX2956 	2	19950417	G	8500		ENGINE 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					PISTON	FAILED 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			EA	05	9106Y					288616001	L1401539A			ENGINE FAILED TO MAKE POWER TO MIN. STATIC R.P.M. AFTER ANNUAL. TEAR DOWN SHOWED WEAR IN CAM LOBES, ONE CYLINDER CRACKE	D, BAD LIFTERS, BAD PISTON, 685 HOURS S.M.O.H. SUBMITTER SUGGESTS BETTER Q.C.					1	L	7	1 	3O	3	O		2A13 	E274				 
1995061600345	19950616	00345	SO 	1995	6	16	95ZZZX2957 	2	19950521	G	8500		ENGINE 			GULSTM	680 	685 	0141612	SW 	CONT 	O520 	GTSIO520K 	17032	SO 					NR 2 CYL	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	333HQ					12018	605129			ENG. LOST M.P. AND OIL PRESS. FOUND COMP. TURBO DAMAGE, NR 2 CYLINDER. PISTON NOT MOVING AND LIFTERS MISSING FROM HOUS	INGS. THREE CYLINDERS FOUND VISIBLY CRACKED. OIL FOUND IN VAC. AND PRESS. PUMP LINES. 'LINES FOUND CON BACKWARDS ON V	AC-PRESS. PUMP.' 71 HRS S.M.O.H. RECENT ANNUAL S.M.O.H. SUBMITTER SUGGESTS STRICTER CONTROL ON ENG. OVERHAULERS AND MA	INT. SHOP.			1	H	7	2 	3O	3	O		2A4 	E7CE				 
1995061600346	19950616	00346	SO 	1995	6	16	95ZZZX2958 	1	19950531	G	7922	75944	VALVE 			PIPER 	PA32 	PA32RT300 	7103215	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			CQVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	36590	1288 				32R7885197				INSPECT OIL COOLER BYPASS VALVE PER LYCOMING SB 518B. FOUND LOOSE NUT. INSTALL NEW VALVE IAW SB.						1	L	7	1 	3O				A3SO 					 
1995061600347	19950616	00347	EA 	1995	6	16	95ZZZX2959 	2	19950514	G	7322	MA4SPA	CARBURETOR 	FACET 		PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E3D 	41508	EA 					VENTURI	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	1453T		200 			287225521	L3182327A			SINCE INSTALLING ONE-PIECE VENTURI, ENG. HAS PROGRESSIVELY RUN RICH - HAVE HAD CARB. APART ON 2 OCCASIONS TO CHECK FLOAT	 LEVEL, VENTURI, ACCELL. PUMP, AND NEEDLE AND SEAT FOR PERFORMANCE, MIXTURE HAS TO BE LEANED (1) KNOB. VIOLENT SHUDDER 	ON POWER REDUCTION UNLESS MIXTURE IS LEANED FIRST. SUSPECT CARB. NEEDS DIFFERENT DISCHARGE NOZZLE WITH THIS VENTURI.				1	L	7	1 	3O	3	O		2A13 	E274				 
1995061600348	19950616	00348	SO 	1995	6	16	95ZZZX2960 	1	19950531	G	7922	75944	VALVE 			PIPER 	PA28 	PA28140 	7102802	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			CQVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	5943U	2800 				2826849				INSPECT OIL COOLER BYPASS VALVE PER LYCOMING SB518B. FOUND LOOSE NUT. INSTALL NEW VALVE IAW SB.						1	L	7	1 	3O				2A13 					 
1995061600349	19950616	00349	SO 	1995	6	16	95ZZZX2961 	1	19950531	G	7922	75944	VALVE 			PIPER 	PA28 	PA28181 	7102807	SO 										THERMO BYPASS	LOOSE CRIMP NUT 	B			CQVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	3053E	1810 				287990186				INSPECT OIL COOLER BYPASS VALVE PER LYCOMING SB 518B. FOUND LOOSE NUT. INSTALL NEW VALVE IAW SB.						1	L	7	1 	3O				2A13 					 
1995061600350	19950616	00350	SO 	1995	6	16	95ZZZX2962 	1	19950601	G	2750	486597	CONTROL CABLE 			PIPER 	PA31 	PA31350 	7103110	SO 										FLAP MOTOR	FAILED 	D				O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			WP	07	6657Y	9744 				317852164				ON SHOT FINAL, PILOT LOWERED FLAPS AND EXPERIENCED A SPLIT FLAP CONDITION. PILOT RAISED FLAPS TO COUNTERACT THE CONDITI	ON. AIRCRAFT WAS LANDED SAFELY. THE RIGHT FLAP CABLE WAS FOUND TO HAVE FAILED AT THE FLAP MOTOR. THE CABLE WAS REPLAC	ED AND THE FLAPS RIGGED PER MANUAL. AIRCRAFT WAS RETURNED TO SERVICE.				1	L	7	2 	3O			 	A20SO 					 
1995061600351	19950616	00351	SW 	1995	6	16	95ZZZX2963 	1	19950428	G	7160	BA6210	AIR FILTER 	BRACKETT 		MOONEY	M20 	M20J 	5870219	SW 										AIR BOX	GASKET FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	4212H	1006 				240663				UPON INSPECTION FOR AN ANNUAL INSPECTION, FOUND AIR FILTER GASKET TORN FROM INB BOLT HOLE, UP TO CORNER AND OUTB ABOUT O	NE-HALF THE LENGTH. THIS TORN SECTION WAS STUCK TO ENGINE BAFFLE. REST OF GASKET STILL ON AIR FILTER BOX. AD 95-3-2 D	OES NOT APPLY TO THIS AIR FILTER.				1	L	7	1 	3O				2A3 					 
1995061600352	19950616	00352	SW 	1995	6	16	95ZZZX2964 	1	19950428	G	7160	BA6210	AIR FILTER 	BRACKETT 		MOONEY	M20 	M20J 	5870219	SW 										AIR BOX	GASKET FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	4264H					240689				AIR FILTER BOX WAS REMOVED TO DETERMINE IF MOONEY SB M20-250A NEEDED TO BE DONE. THE AIR FILTER BOX GASKET WAS MISSING 	ON BOTH SIDES; THE TOP AND BOTTOM WAS STILL THERE. AD 95-3-2 DOES NOT APPLY TO THIS AIR FILTER. THERE IS NO LOG BOOK E	NTRY OR 337 FOR THIS INSTALLATION.				1	L	7	1 	3O				2A3 					 
1995061600353	19950616	00353	SO 	1995	6	16	95ZZZX2965 	1	19950424	G	2750	2296602	CONTROL CABLE 			PIPER 	PA30 	PA30 	7103002	SO 										STABILIZER	FRAYED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	7171Y	5123 				30191				INSPECTION OF STABILIZER UPPER CABLE FOUND APPROXIMATELY 8 CABLE STRANDS BROKEN AT EYE FORMED BY THIMBLE. CABLE APPEARE	D TO BE IN GOOD CONDITION; OTHERWISE, NO APPARENT CAUSE NOTED.					1	L	7	2 	3O			 	A1EA 					 
1995061600354	19950616	00354	EA 	1995	6	16	95ZZZX2966 	2	19950606	G	8550		ENGINE 			CESSNA	210 	P210N 	2073454	CE 	LYC 	O540 	TIO540V2AD 	41532	EA 					OIL PAN	OIL SLUDGE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	4994K	800 				P21000392	L861661A			DURING TEAR DOWN INSPECTION OF ENGINE AFTER PROP STRIKE, THICK OIL SLUDGE DEPOSITS WERE FOUND IN THE CRANKSHAFT AND THE 	OIL PAN. TWO ACCESSORY HOUSING GEARS HAD TO BE REPLACED DUE TO PITTING AND WEAR. RECORDS SHOW THE ENGINE HAD BEEN RUN 	USING MOBILE AV-1 OIL FROM 05-02-88 THROUGH 03-25-93 FOR A TOTAL OF 592.6 HOURS. THE SOLID FILM IN THE CRANKSHAFT AND O	IL PAN MEASURED .1250 INCH THICK.			1	H	7	1 	3O	3	O		3A21 	E14EA				 
1995061600355	19950616	00355	SO 	1995	6	16	95ZZZX2967 	1	19950501	G	3211	6704212	FITTING ASSY 			PIPER 	PA34 	PA34200T 	7103406	SO 										RT AFT GEAR WELL	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	2119D	8214 				347970026				UPON REPLACEMENT OF TRUNNIONS PER SB 787B, FOUND RIGHT AFT FITTING ASSY CRACKED IN UPPER LEFT QUADRANT.						1	L	7	2 	3O				A7SO 					 
1995061600356	19950616	00356	SW 	1995	6	16	95ZZZX2968 	1	19950502	G	8120	600064000	INLET DUCT 	ROTOMASTER 	325E101 	MOONEY	M20 	M20C 	5870208	SW 										TURBO	WIRE BROKE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	7765M	185 	46 		19370	200018				SUSPECT HARDENED WIRE FROM INLET DUCT BROKE LOOSE AND ENTERED TURBO IMPELLER. SUGGEST WIRE SUPPORTING STRUCTURE BE MOLD	ED INTO PART TO PREVENT RUST AND BREAKING LOOSE.					1	L	7	1 	3O				2A3 					 
1995061600357	19950616	00357	EA 	1995	6	16	95ZZZX2969 	2	19950518	G	8550		DIVERSION PLATE 			BBAVIA	7 	7KCAB 	21101P3	CE 	LYC 	O320 	IO320E2A 	41508	EA 					OIL PAN	BROKEN 	G	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	5163T	1939 				11	L277655A			AFTER REMOVAL OF OIL PAN AND ACCESSORY SECTION TO COMPLY WITH 'AD' OF OIL PUMP ASSY, FOUND INVERTED FLIGHT OIL DIVERATIN	G PAN (PART UNK) CRACKED AND BROKEN FROM FLEX STRESS, SEVERAL PIECES BROKEN WERE FOUND LAYING IN OIL PAN. THIS SYSTEM I	NSTALLED AT CHAMP FACTORY AS ORIGINAL EQUIP. FOR INVERTED FLIGHT OIL SYSTEM. DATE OF A/C MFG 1-7-67.				1	H	7	1 	3O	3	O		A759 	1E12				 
1995061600359	19950616	00359	SW 	1995	6	16	95ZZZX2971 	1	19950205	G	6220	204010937009	DAMPER 			BELL 	212 	212 	1181420	SW 										M/R	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	748H		307 		H1083	35060				DAMPER TIMING IS TOO FAST.						1	G	7	1 	4U				H4SW 					 
1995061600360	19950616	00360	SW 	1995	6	16	95ZZZX2972 	1	19950222	G	7722	3030083A	TRIM COMPENSATOR			BELL 	212 	212 	1181420	SW 										ENG TIT	INOPERATIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	748H	1620 			5Y872	35060				TRIM COMPENSATOR INOPERATIVE - GIVES NO TRIM ACTION.						1	G	7	1 	4U				H4SW 					 
1995061600361	19950616	00361		1995	6	16	95ZZZX2973 	4	19950306	G	3455	DF88A	AMPLIFIER 			BELL 	214 	214ST 	1182106	SW 										ADF	INOPERATIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	746H	1044 			9316720	28200				AMPLIFIER FAILED. DF 88 DOES NOT POINT. NOTE: UNIT ORIGINALLY RECEIVED WITH NEW ACFT FROM BELL/USA.						2	G	7	2 	4U				H10SW 					 
1995061600362	19950616	00362		1995	6	16	95ZZZX2974 	4	19950313	G	2330	M4000	PA SYSTEM 			BELL 	214 	214ST 	1182106	SW 										CABIN	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	746H	1069 			9307096	28200				PA SYSTEM DEFECTIVE. BRIEFING CANNOT BE SELECTED OR TURNED OFF.						2	G	7	2 	4U				H10SW 					 
1995061600363	19950616	00363	SW 	1995	6	16	95ZZZX2975 	1	19950116	G	6200	214010558101	LINK ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R	BEARING WORN 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	746H		249 		A1900037	28200				LINK ASSY, BOTH RUBBER BEARINGS WORN.						2	G	7	2 	4U				H10SW 					 
1995061600472	19950616	00472	EU 	1995	6	16	95ZZZX2996 	1	19950221	G	3222	5322012036	TRUNNION 			PILATS	PC12 	PC12 	7090550	EU 										NLG	CRACKED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	62JT	42 				107				DURING C/W PILATUS SB PC-12 32-001, FOUND NOSE TRUNNION CRACKED ON AFT LEFT SIDE. SUSPECT CAUSED BY DESIGN OF PART. NO	SE GEAR DID NOT APPEAR TO BE OVERSTRESSED IN ANY WAY. SUBMITTER SUGGESTS THIS PROBLEM WILL CONTINUE TO OCCUR UNTIL TRUN	NION IS REDESIGNED.				1	L	7	1 	3T			RT	A78EU 					 
1995061600473	19950616	00473	CE 	1995	6	16	95ZZZX2997 	1	19950606	G	3246		BEARING CUP 			BEECH 	200 	200BEECH 	1152920	CE 										NR 3 MLG	WRONG PART 	B		A	MJ7R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	05	103TF	150 				BB649				DURING REPLACEMENT OF BRAKE ASSY, BEARINGS ON NR 3 MAIN WHEEL ASSY WOULD NOT REASSEMBLE CORRECTLY. DURING INVESTIGATION	, FOUND INCORRECT BEARING CUPS WERE INSTALLED NOT ALLOWING THE BEARING TO SEAT IN THE CUPS PROPERLY. TIMKEN BEARING PN	 13600LA WAS INSTALLED WITH TYSON 1362XL CUP ON INBOARD WHEEL HALF AND SKF 13621XL ON OUTBOARD WHEEL HALF. WARNING GIVE	N ON TIMKEN BEARING PACKAGE WARNS AGAINST THIS PRACTICE.			1	L	7	2 	4T				A24CE 					 
1995061600474	19950616	00474	EA 	1995	6	16	95ZZZX2998 	1	19950502	G	7921		COOLER 			SCWZER	G164 	G164B 	3952802	EA 										ENG OIL	SEAM SPLIT 	C		A	HTFG	O	A			OTHER 	UNSCHED LANDING 			K	J		FLUID LOSS 	WARNING INDICATION 		CL	CLIMB 	1			GL	09	8499K	5000 				720B				OIL COOLER SPLIT THE SEAM WELD ON TAKEOFF. PILOT NOTED LOSS OF TORQUE PSI IMMEDIATELY FOLLOWED BY ILLUMINATION OF LOW O	IL PSI LIGHT. PILOT DUMPED LOAD AND MADE AN EMERGENCY LANDING. NEW OIL COOLER INSTALLED AND SPLIT THE SEAM WELD DURING	 START. SUSPECTED AEROQUIP QUICK COUPLER ON OIL COOLER RESTRICTING FLOW CAUSING EXCESSIVE PRESSURE IN COOLER. SUBMITTE	R SUGGESTS REMOVING QUICK COUPLERS.			1	Q	7	1 	3R				1A16 					 
1995061600475	19950616	00475	CE 	1995	6	16	95ZZZX2999 	1	19950523	G	2197		WIRE 			CESSNA	414 	414A 	2075907	CE 										AC BLOWER	CHAFED 	D		A		A				UNSCHED LANDING 				B			SMOKE/FUMES/ODORS/SPARKS 			CL	CLIMB 	1			SW	99	58H					414A0314				JUST AFTER TAKEOFF, PILOT NOTICED BURNING SMELL FROM UNDER SEAT (PILOTS). RETURNED AIRCRAFT BACK TO BASE WITHOUT FURTHE	R INCIDENT. MECHANIC FOUND CHAFED WIRE GOING TO AIR COND. BLOWER MOTOR. REPAIRED WIRE AND OPS CHECKED GOOD.					1	L	7	2 	3O			 	A7CE 					 
1995061600476	19950616	00476	CE 	1995	6	16	95ZZZX3000 	1	19950601	G	2913	HYH5001	GEAR PUMP 	PRESTOLITE 		BEECH 	23 	C24R 	1151254	CE 										MLG	MOTOR FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	123TH	3270 			0021004	MC699				FAILURE OF THE ELECTRIC MOTOR ON THE GEAR PUMP.						1	L	7	1 	3O				A1CE 					 
1995061600477	19950616	00477		1995	6	16	95ZZZX3001 	4	19950520	G	3416	D120P2T	ENCODER 	TRANSCAL 		CESSNA	172 	172 	2072402	CE 										ALTIMETER	DEFECTIVE 	B			EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	12885				61335	17262342				THERE WAS ZERO BACKLASH IN THE ENCODER MODULE GEAR MESH. THE O/H MANUAL CALLS OUT ONE-QUARTER TO ONE-HALF TOOTH WIDTH B	LACKLASH IN THIS MESH. WHEN THE BACKLA SH IS ZERO, A VERY SLIGHT CHANGE IN TEMPERATURE CAN CAUSE THE ENCODER TO HANG UP	.				1	H	7	1 	3O			NT	3A12 					 
1995061600478	19950616	00478	SO 	1995	6	16	95ZZZX3002 	2	19950515	G	8520		ROD 			CESSNA	414 	414A 	2075907	CE 	CONT 	O520 	TSIO520NB 	17040	SO 					ENGINE	FAILED 	E			EAVV	A				UNSCHED LANDING 				O			OTHER 			NR	NOT REPORTED 	1			GL	09	36934	820 				414A0486	276819R			ENGINE CAME APART IN-FLIGHT. SUSPECT CONNECTING ROD OR COUNTERWEIGHT FAILURE. DATE 5-15-95.						1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995061600479	19950616	00479	CE 	1995	6	16	95ZZZX3003 	1	19950605	G	3250	0510105199	CONTROL CABLE 			CESSNA	185 	185 	2072802	CE 										TAILWHL STEERING	FRAYED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	186D					1850127				TAILWHEEL STEERING CABLE FRAYED IN AREA CONTACTING PULLEY. APPEARS TO BE 'NORMAL' WEAR. CABLE MUST BE REMOVED TO INSPE	CT. APPLICABLE TO LATER MODEL 180'S AND ALL 185'S.					1	H	7	1 	3O			NC	3A24 					 
1995061600480	19950616	00480	CE 	1995	6	16	95ZZZX3004 	1	19950605	G	3250	0510105196	CONTROL CABLE 			CESSNA	185 	185 	2072802	CE 										TAILWHL STEERING	FRAYED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	186D					1850127				TAILWHEEL STEERING CABLE FRAYED IN AREA CONTACTING PULLEY. APPEARS TO BE 'NORMAL' WEAR. CABLE MUST BE REMOVED TO INSPE	CT. APPLICABLE TO LATER MODEL 180'S AND ALL 185'S.					1	H	7	1 	3O			NC	3A24 					 
1995061600481	19950616	00481		1995	6	16	95ZZZX3005 	4	19950520	G	3416	3431	CASTING 	UNITEDINST 	5934P 	CESSNA	172 	172 	2072402	CE 										ALTIMETER	CREEP 	B	L		EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	12885				C3909	17262342				TWO OF THE CRITICAL MECHANISM SHAFT END-SHAKES OUT OF THE O/H MANUAL SPECIFICTION. (SPEC. ON END-SHAKE .002 INCH TO .00	3 INCH). ONE SHAFT END-SHAKE MEASURED .0005 INCH AND THE OTHER MEASURED .001 INCH.					1	H	7	1 	3O			NT	3A12 					 
1995061600482	19950616	00482	EA 	1995	6	16	95ZZZX3006 	2	19950529	G	8520	149518	BEARING 								WRIGHT	R1820 	R182080 	67020	EA 					MASTER ROD	FAILED 	B			EJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11							473912			MASTER ROD BEARING FAILED AND SEIZED TO CRANKSHAFT ROD JOURNAL ON GROUND AFTER START-UP. LACK OF PROPER LUBRICATION. S	USPECT CAUSED FROM NOT PROPERLY PRE-OILING DURING START-UP. SUBMITTER SUGGESTS THIS ENGINE IS EXTREMELY SENSITIVE TO OI	L STARVATION AT START-UP, ESPECIALLY AFTER SITTING.									4	R			E259				 
1995061600483	19950616	00483		1995	6	16	95ZZZX3007 	4	19950521	G	3416	3431	CASTING 	UNITEDINST 	5934P1 	CESSNA	182 	R182 	2072734	CE 										ALTIMETER	CREEP 	B	L		EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5425S				T4107	R18201570				THE END SHAKES ON ALL 3 OF THE CRITICAL MECHANISM SHAFTS WERE UNDER THE O/H MANUAL TOLERANCE. THEY MEASURED .0002 INCH,	 .0009 INCH, AND .0009 INCH. THE .0002 INCH END SHAKE WAS ON THE WHEEL ASSY SHAFT.					1	H	7	1 	3O			RT	3A13 					 
1995061600484	19950616	00484	CE 	1995	6	16	95ZZZX3008 	1	19950525	G	3230	6NBC914Y5	BEARING 			BEECH 	60 	B60 	1153605	CE 										RT UPLOCK	SEIZED 	B			GMZR	O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			AP	APPROACH 	1			SW	01	6693A	3354 				P527				ON APPROACH FOR LANDING, LANDING GEAR WOULD NOT EXTEND ELECTRICALLY AND AN ODOR WAS NOTICED IN THE COCKPIT. THE GEAR WA	S EXTENDED MANUALLY, BUT A LOUD POPPING NOISE WAS HEARD UPON EXTENSION. INSPECTION OF THE GEAR AFTER LANDING FOUND RT U	PLOCK ROLLER SEIZED. THIS ROLLER WOULD NOT DISENGAGE FROM PN 35-845077-22 RT UPLOCK BLOCK; THUS, ALLOWING GEAR MOTOR TO	 BURN OUT AND BEND THE RT GEAR RETRACT ROD PN 60-810057-617. THE MM CALLS OUT AN INSPECTION AND LUBRICATION OF THIS ROL	LER EACH 100 HOURS OF OPERATION.		1	L	7	2 	3O				A12CE 					 
1995061600489	19950616	00489	SO 	1995	6	16	95ZZZX3013 	1	19950523	G	3411		BLADE 			PIPER 	PA28 	PA28180 	7102808	SO 										PITOT STATIC	PLUGGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	4BQ					284474				PILOT WAS INFORMED BY ATL THAT MODE 'C' ALTITUDE READINGS WERE UNSTABLE PARTICULARLY IN BANKING MANEUVER. SUDDEN CHANGE	S OF 400 FEET TO 1200 FEET IN INDICATED ALTITUDES WERE NOTICED. BENCH TESTING OF ENCODER AND TRANSPONDER SHOWED NO DEFE	CTS. TESTING OF SYSTEM IN AIRCRAFT SHOWED NO DEFECTS ON GROUND. A PARTIALLY PLUGGED CALIBRATED DRAIN PORT WAS FOUND ON	 THE TRAILING EDGE OF STATIC BLADE UNDER LEFT WING. CLEANING THE HOLE SOLVED THE PROBLEM. TACH TIME - 2528.2.			1	L	7	1 	3O				2A13 					 
1995061600490	19950616	00490	SO 	1995	6	16	95ZZZX3014 	1	19950503	G	7810	06B19913	GASKET 			PIPER 	PA46 	PA46350P 		SO 										EXHAUST	FAILED 	B			DYTR	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			R			PARTIAL RPM/PWR LOSS 			TO	TAKEOFF 	1			SO	15	9193Q	392 				4622097				AIRCRAFT LOST POWER ON TAKEOFF ROLL (ENGINE WENT TO AMBIENT M.P.) 29 INCHES INSTEAD OF 42 INCHES HG FOR TAKEOFF. INSPEC	TION REVEALED EXHAUST GASKET BETWEEN NR 1 AND NR 3 HAD BROKEN INTO 3 PIECES, 2 PIECES FOUND IN RIGHT TURBO JAMMING TURBI	NE WHEEL. EXHAUST CLAMP WAS STILL IN PLACE AND SAFETIED, BUT VERY LOOSE (GASKET MISSING). EXCESSIVE EXHAUST LEAK ALSO.	 (BOTH TURBOS REPLACED).			1	L	7	1 	3O			RT	A25SO 					 
1995061600491	19950616	00491	NE 	1995	6	16	95ZZZX3015 	2	19950529	G	8530	116731	CYLINDER 								PWA 	R1830 	R183092 	52020	NE 					NR 12	FAILED 	B			EJ4R	O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			SW	11			480 				56873			NR 12 CYLINDER SKIRT CRACKED AND BROKE OFF IN-FLIGHT AFTER CHAFING MOST OF ONE SIDE OF PISTON AWAY.											4	R			5E4				 
1995062300017	19950623	00017	NE 	1995	6	23	95ZZZX3016 	1	19950412	G	6220	7610408520041	SCISSOR 			SKRSKY	S76 	S76C 	8143008	NE 										M/R	BUSHING MISSING 	C				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25	399KK	298 				760421				INNER BUSHINGS FOUND NOT INSTALLED. FOUND WHILE INSPECTING ASSEMBLY FOR WEAR. C/A REPLACED DRIVE LINK ASSEMBLY.						1	G	7	2 	3U			NC	H1NE 					 
1995062300022	19950623	00022	SW 	1995	6	23	95ZZZX3021 	1	19950218	G	2435	214060056001	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENGINE	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	704H		60 		83C0077	28108				STARTER DRAWS TOO MANY AMPS DURING STARTING CYCLE.						2	G	7	2 	4U				H10SW 					 
1995062300023	19950623	00023	SW 	1995	6	23	95ZZZX3022 	1	19950129	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENG	DISENGAGES 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	704H		24 		82M0061	28108				STARTER DISENGAGES DURING MIDDLE OF THE STARTING CYCLE.						2	G	7	2 	4U				H10SW 					 
1995062300024	19950623	00024	SW 	1995	6	23	95ZZZX3023 	1	19950117	G	2913	212076011001	PUMP 			BELL 	212 	212 	1181420	SW 										HYD SYS	MISMFG 	C				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EU	01	708H				AU30	30641				HYDRAULIC PUMP DEFECTIVE. THE UPPER HALF OF THE PUMP BODY IS INSTALLED 180 DEGREES OUT.						1	G	7	1 	4U				H4SW 					 
1995062300025	19950623	00025		1995	6	23	95ZZZX3024 	4	19950325	G	2312	40001452500	TRANSCEIVER 			BELL 	206 	206L3 	1182108	SW 										COCKPIT VHF	INOPERATIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	726H		10 		551	51548				TRANSCEIVER FAILED. THERE IS NO TX, RCV, AND SIDELINE.						1	G	7	1 	3U				H2SW 					 
1995062300026	19950623	00026		1995	6	23	95ZZZX3025 	4	19950207	G	3455	066107200	RECEIVER 			BELL 	206 	206L3 	1182108	SW 										COCKPIT ADF	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	731H	1404 			48710	51562				RECEIVER DIGITS ARE UNREADABLE.						1	G	7	1 	3U				H2SW 					 
1995062300027	19950623	00027	GL 	1995	6	23	95ZZZX3026 	2	19950207	G	7320	23007827	VALVE 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30 	03013	GL 					ENG	INOPERATIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	732H		20 		3457	51607				VALVE INOPERATIVE.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995062300028	19950623	00028	GL 	1995	6	23	95ZZZX3027 	2	19950128	G	7320	23007827	VALVE 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30 	03013	GL 					ENG	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	732H	1526 			2395	51607				THE SOLENOID VALVE IS NOT WORKING.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995062300030	19950623	00030	SW 	1995	6	23	95ZZZX3029 	1	19950130	G	7714	212070108007	INDICATOR 			BELL 	212 	212 	1181420	SW 										TRIPLE TACH	STICKS 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	736H		62 		8002109	35048				INDICATOR N2 NEEDLE STICKS AT 65 PERCENT.						1	G	7	1 	4U				H4SW 					 
1995062300032	19950623	00032	SW 	1995	6	23	95ZZZX3031 	1	19950209	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENG	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H		2 		84L0166	28197				STARTER DOES NOT DISENGAGE AFTER START.						2	G	7	2 	4U				H10SW 					 
1995062300033	19950623	00033	SW 	1995	6	23	95ZZZX3032 	1	19950108	G	7722	3030083A	TRIM COMPENSATOR			BELL 	212 	212 	1181420	SW 										ENG TIT	INOP 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	749H	1480 			7Y394	35061				TRIM COMPENSATOR INOPERATIVE, WILL NOT TRIM ITT PROPERLY, WILL NOT ADJUST PROPERLY.						1	G	7	1 	4U				H4SW 					 
1995062300034	19950623	00034	WP 	1995	6	23	95ZZZX3033 	1	19950606	G	7810	369A8230503	EXHAUST PIPE 			HUGHES	369 	369D 	4470706	WP 										CUSHION FLANGE	CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	8639F					1280431D				EXHAUST STACK WAS FOUND CRACKED ALONG THE CUSHION FLANGE. UNIT REMOVED AND SENT IN FOR REPAIR.						1	G	7	1 	3U				H3WE 					 
1995062300036	19950623	00036	SO 	1995	6	23	95ZZZX3034 	2	19950607	G	8550	12509222	ADAPTER ASSY 			BEECH 	35 	J35 	1151522	CE 	CONT 	O470 	IO470C 	17026	SO 					OIL FILTER	WORN 	G	S			A				UNSCHED LANDING 				J	K		WARNING INDICATION 	FLUID LOSS 		CR	CRUISE 	1			EA	01	8378D	405 				D5497	786273CR			DURING CRUISE FLIGHT, THE ENGINE BEGAN TO LOSE OIL PRESSURE. THE PILOT DECLARED AN EMERGENCY AND LANDED IN A FIELD WITH	 MINIMAL DAMAGE. THE ENGINE HAD BEEN EQUIPPED WITH FULL FLOW OIL FILTER KIT INSTALLED UNDER STC 3262 WE. THE THREADS O	N THE ADAPTER ASSEMBLY BECAME WORN AND THE ADAPTER WAS LOOSE WHERE IT FITS INTO THE ENGINE ACCESSORY CASE. THE OIL LEAK	ED OUT AROUND THE ADAPTER AND THE ENGINE SEIZED. THE ADAPTER NUT ITEM NR 5 GETS TORQUED DOWN COMPRESSING A PACKING ITEM	 NR 6. IF THE NUT WERE UNDERTORQUED, THE WEIGHT OF THE FILTER PLUS THE LENGTH OF THE ADAPTER WOULD CREATE LEVERAGE TO V	IBRATE AND WEAR OUT THE THREADS OF THE ADAPTER. THE THREADS OF THE ENGINE CASE WERE IN GOOD CONDITION.	1	L	7	1 	3O	3	O		3A15 	E273				 
1995062300037	19950623	00037	GL 	1995	6	23	95ZZZX3035 	3	19950608	G	6111	T10173B8R	BLADE 			BEECH 	90 	E90 	1152914	CE 						HARTZL	HCB3T	HCB3TN3 	GL 	PROP	UNDERSIZE 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15			200 			LW75		BU4195		UPON FINDING BLADES, MODEL NR T10173B-8R, S/NS C84204, C84280, C84314, C21475, C34127, AND C34121, DIMENSIONALLY UNDER W	IDTH WISE, CUSTOMER REPORTED PROPS HAVING APPROXIMATELY 200 HOURS SINCE OVERHAUL. PROPELLERS WERE OVERHAULED LAST IN ME	XICO.				1	L	7	2 	3T				3A20 		6	C	P15EA	 
1995062300038	19950623	00038	CE 	1995	6	23	95ZZZX3036 	1	19950501	G	3230	10541000057	CHANNEL 			BEECH 	76 	76 	1153005	CE 										NLG ACT ATTACH	CRACKED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	5274M					ME24				INSPECTION FOUND CHANNEL THAT NLG ACTUATOR ATTACHES TO, CRACKED. ACFT TT 3,800 HRS.						1	L	7	2 	3O				A29CE 					 
1995062300039	19950623	00039	CE 	1995	6	23	95ZZZX3037 	1	19950501	G	3230	10541000057	CHANNEL 			BEECH 	76 	76 	1153005	CE 										NLG ACT ATTACH	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	5400M					ME30				INSPECTION FOUND CHANNEL THAT NLG ACTUATOR ATTACHES TO, CRACKED.						1	L	7	2 	3O				A29CE 					 
1995062300040	19950623	00040	EA 	1995	6	23	95ZZZX3038 	2	19950606	G	7250	310250201	BLADE 		3029312 	BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					1ST PT	TIP MISSING 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01	259AF		3729 			UB55	32028			THE POWER SECTION WAS RECEIVED FROM ARIZONA AIRWAYS WITH 35 PERCENT OF A FIRST STAGE PT BLADE TIP PLATFORM MISSING. AFT	ER THE PT BLADE AND DISK WERE DISASSEMBLED AND INSPECTED, A TOTAL OF (2) 1ST STAGE AND (11) 2ND STAGE BLADES WERE REPLAC	ED.				2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1995062300041	19950623	00041	NE 	1995	6	23	95ZZZX3039 	2	19950217	G	7250	310164701	BEARING 			BEECH 	1900 	1900D 	1154162	CE 	PWA 	PT6 	PT6A67 	52043	NE 					POWER SECT	SPALLED 	B			MASR	K				NONE 				C			F.O.D. 			IN	INSP/MAINT 	1			SW	01	9YV	5558 			84C593	UE9	114065			BEARINGS NR 5, NR 6, AND NR 7 HAVE INDICATION OF ARCING AND SPALLING. POWER SECTION WAS REPORTED HAVING SUSTAINED A LIG	HTNING STRIKE.					2	L	7	2 	4T	4	T	RT	A24CE 	E26NE				 
1995062300042	19950623	00042	NE 	1995	6	23	95ZZZX3040 	2	19950301	G	7210	310983901	SHAFT 			BEECH 	1900 	1900D 	1154162	CE 	PWA 	PT6 	PT6A67 	52043	NE 					PROP SHAFT	GALLED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	3YV	3970 			4X271	UE3	114086			THE POWER SECTION WAS REPORTED AS HARD TO ROTATE. UPON DISASSEMBLY, FOUND PROP SHAFT AND SLEEVE WAS GALLED IN SUCH A WA	Y THAT IT COULD NOT ROTATE FREELY. IT HAS BEEN DETERMINED THE GALLING OCCURRED DUE TO FUEL OIL HEATER CONTAMINATING THE	 OIL SYSTEM WITH FUEL.				2	L	7	2 	4T	4	T	RT	A24CE 	E26NE				 
1995062300043	19950623	00043	NE 	1995	6	23	95ZZZX3041 	2	19950411	G	7250	311269601	BEARING 			BEECH 	1900 	1900D 	1154162	CE 	PWA 	PT6 	PT6A67 	52043	NE 					PWR TURB	SPALLED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	154ZV	21613	557 		FC22643	UE154	32041			THE METAL OBSERVED IN THE POWER SECTION WAS BEING GENERATED BY THE NR 4 BEARING. THE CAUSE OF THE NR 4 BEARING SPALLING	 IS UNDER INVESTIGATION BY PRATT AND WHITNEY CANADA.					2	L	7	2 	4T	4	T	RT	A24CE 	E26NE				 
1995062300044	19950623	00044	NE 	1995	6	23	95ZZZX3042 	2	19950221	G	7210	310835601	SUN GEAR 								PWA 	PT6 	PT6A67 	52043	NE 					POWER SECT	TEETH MISSING 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01		4756 				UE004	114018			THE FIRST STAGE SUN GEAR WAS SPALLED AND SEVERAL GEAR WERE FOUND LIBERATED. INVESTIGATION IS LOOKING TOWARD ELECTROSTAT	IC DISCHARGE DUE TO THE SPALLING AND PAST HISTORY OF THE ENGINE AND PROPELLER COMBINATION.										4	T			E26NE				 
1995062300045	19950623	00045	EA 	1995	6	23	95ZZZX3043 	2	19950523	G	7240	310846701	COMBUSTION LINER								PWA 	PT6 	PT6* 	52043	EA 					HOT SECTION	MISIDENTIFIED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					5R143					PART WAS RECEIVED FROM I.T.S. AVIATION, INC., IDENTIFIED AS 3103775-01. PART IN REALITY IS AS 3108467-01 LINER WITH SB 	3236R2 COMPLIED WITH. THE LINER ASSEMBLY WAS NOT REIDENTIFIED WHEN THE SB WAS COMPLETED. PART RETURNED TO VENDOR.										3	T			E2NE				 
1995062300046	19950623	00046	EA 	1995	6	23	95ZZZX3044 	2	19950417	G	7230	310830101	BLADE 								PWA 	PT6 	PT6A65B 	52043	EA 					CT DISK	MISMANUFACTURED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										PART RECEIVED FROM STOCK AND FOUND THE RIVET SLOT WAS NOT MANUFACTURED PROPERLY. RIVET CHAMFER ON LEADING EDGE NOT MACH	INED. PART RETURNED TO VENDOR.										4	T			E4EA				 
1995062300047	19950623	00047	NE 	1995	6	23	95ZZZX3045 	2	19950507	G	7230	3023401	BLADE 								PWA 	PT6T 	PT6T3B 	52045	NE 					CT DISK	MISMANUFACTURED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										PART WAS RECEIVED FROM PWC AND WAS FOUND INCOMPLETE RIVET SLOT NOT CHAMFERED ON LEADING EDGE SIDE. PART RETURNED TO PWC	 FOR CREDIT.										4	U			E22EA				 
1995062300048	19950623	00048	EA 	1995	6	23	95ZZZX3046 	2	19950410	G	7250	310023601	SEAL RING 								PWA 	PT6 	PT6A65B 	52043	EA 					HOT SECT	EXCESS GAP 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										PARTS RECEIVED FROM PRATT AND WHITNEY AND WERE FOUND TO HAVE AN EXCESSIVE GAP 1,000.											4	T			E4EA				 
1995062300049	19950623	00049	EA 	1995	6	23	95ZZZX3047 	2	19950515	G	7313	3005305	WASHER KEY 								PWA 	PT6 	PT6A65B 	52043	EA 					GAS GENERATOR	MISINSTALLED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										RECEIVED FUEL NOZZLE SET FROM STOCK AND ONE KEY WASHER WAS FOUND TO BE IMPROPERLY INSTALLED. SET RETURNED TO OVERHAUL F	ACILITY REGIONAL AIRCRAFT SERVICES.										4	T			E4EA				 
1995062300050	19950623	00050	NE 	1995	6	23	95ZZZX3048 	2	19950413	G	7210	3037767CL1	GEAR ASSY 								PWA 	PT6 	PT6A67 	52043	NE 					POWER SECT	GALLED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					65C908					PART RECEIVED FROM STOCK AS NEW PART FROM PWC. PART SHOWS GAULING MARKS ON GEAR SIDEWALLS. PART RETURNED TO VENDOR.											4	T			E26NE				 
1995062300051	19950623	00051	EA 	1995	6	23	95ZZZX3049 	2	19950417	G	7240	3035567	SEAL ASSY 								PWA 	PT6 	PT6A65B 	52043	EA 					HOT SECT	MISIDENTIFIED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					50013					PART RECEIVED FROM STOCK AND WAS FOUND TO BE IMPROPERLY IDENTIFIED. PART IS A CL 5, BUT IS IDENTIFIED AS A CL 7.											4	T			E4EA				 
1995062300052	19950623	00052	SW 	1995	6	23	95ZZZX3050 	1	19950605	G	3610	222060094101	LINE 			BELL 	222 	222 	1182122	SW 										NR 1 ENG BLEED	SEVERED 	G				O				OTHER 				B	J		SMOKE/FUMES/ODORS/SPARKS 	WARNING INDICATION 		AP	APPROACH 	1			SW	99	222LL					47060				PILOT NOTICED A HIGH EGT AND OIL TEMP ON THE NR 1 ENGINE. WHILE ON 8-MILE FINAL, CREW REPORTED FUMES IN THE CABIN. AIR	CRAFT LANDED WITHOUT FURTHER INCIDENT. UPON INSPECTION, THE BLEED AIR LINE WAS FOUND SEVERED. THE LINE WAS REPLACED AN	D THE AIRCRAFT RETURNED TO SERVICE.				1	G	7	2 	3U				H9SW 					 
1995062300053	19950623	00053	WP 	1995	6	23	95ZZZX3051 	1	19950607	G	7722	369A45217	GAUGE 			HUGHES	369 	369D 	4470706	WP 										TOT	STICKS 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V				64447253	490487D				TOT GAUGE STICKS AT 450 DEGREES CELSIUS DURING START CYCLE (RAPID TOT INCREASE). PART SENT IN FOR REPAIR.						1	G	7	1 	3U				H3WE 					 
1995062300054	19950623	00054	WP 	1995	6	23	95ZZZX3052 	1	19950607	G	2435	369A455011	STARTER 			HUGHES	369 	369D 	4470706	WP 										START/GEN	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V				22079	490487D				AMMETER FLUCTUATED 150 AMPS FOR FIRST 5 MINUTES OF OPERATION - CHANGED AMMETER.						1	G	7	1 	3U				H3WE 					 
1995062300055	19950623	00055	SW 	1995	6	23	95ZZZX3053 	1	19950518	G	2821	2C271	CARTRIDGE 			BELL 	206 	206B3 	1181506	SW 										FUEL SYSTEM	DEFECTIVE 	B			TU3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	303PD					4319				PUMP WAS NOISY ALL THE TIME AND TRIPPED CIRCUIT BREAKER.						1	G	7	1 	3U				H2SW 					 
1995062300316	19950623	00316		1995	6	23	95ZZZX3074 	3	19950528	G	6110		BOLTS 			AMTR 	CH601 	CH601HDS 	05625J7	GL 										PROP FLANGE	SHEARED 	G				O				OTHER 				D			INFLIGHT SEPARATION 			AP	APPROACH 	1			SO	16	18FL					63073				DURING A POWER CHANGE IN THE TRAFFIC PATTERN, THE PROPELLER DEPARTED THE AIRCRAFT. INSPECTION OF THE CRANKSHAFT FLANGE 	SHOWED THAT ALL 6 BOLTS HAD BROKEN FLUSH WITH THE FLANGE. IT APPEARS FROM VISUAL INSPECTION THE BOLTS HAD BEEN OVERTORQ	UED AT INSTALLATION ONLY 11 HOURS PRIOR TO THIS ACCIDENT. THREE PORTIONS OF THE BROKEN BOLTS WERE REMOVED AND SENT TO T	HE NTSB FOR FURTHER ANALYSIS.			1	L	7	1 	3O			NC	1L71 					 
1995062300318	19950623	00318	SO 	1995	6	23	95ZZZX3076 	1	19950426	G	7922	75944	VALVE 			PIPER 	PA28 	PA28140 	7102802	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	6252W					2820299				WHILE C/W LYC SB 518B, FOUND NUT LOOSE AND SHAFT BENT - TT UNKNOWN.						1	L	7	1 	3O				2A13 					 
1995062300319	19950623	00319	CE 	1995	6	23	95ZZZX3077 	1	19950508	G	7922	57944	VALVE 			CESSNA	172 	172N 	2072434	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	5833J	160 			109667	73843				VERNATHERM NUT IS VERY LOOSE - ENGINE AND A/C HAVE ONLY 160.0 TT SINCE NEW.						1	H	7	1 	3O			NT	3A12 					 
1995062300320	19950623	00320	CE 	1995	6	23	95ZZZX3078 	1	19950504	G	7922	53E19600	VALVE 			CESSNA	177 	177B 	2073708	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	34680	2651 				17701937				PER AIRCRAFT ANNUAL INSPECTION, CHECKED THERMOSTATIC VALVE CONDITION. FOUND THE SERIAL NUMBER OF THIS VALVE IS NOT SUBJ	ECT TO INITIAL INSPECTION, BUT FOUND THIS THERMOSTATIC VALVE TO HAVE A LOOSE CRIMP NUT. ALL THERMOSTATIC VALVES NEED TO	 BE CHECKED OR A NEW DESIGN OF SAFETING CRIMP NUTS.				1	H	7	1 	3O				A13CE 					 
1995062300321	19950623	00321	CE 	1995	6	23	95ZZZX3079 	1	19950607	G	7922	75944	VALVE 			CESSNA	182 	TR182 	2072735	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	B			AQHD	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	739CQ	1430 			95627	R18200988				INSPECTED PART PER LYC SB 518C. FOUND LOOSE CRIMP NUT. REPLACED WITH NEW PART.						1	H	7	1 	3O				3A13 					 
1995062300322	19950623	00322	CE 	1995	6	23	95ZZZX3080 	1	19950606	G	7922	75944	VALVE 			CESSNA	150 	152 	2071835	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	35FD					15283048				C/W SB 518C (LYC) CHECKED VERNATHERM NUT, FOUND LOOSE, NOT CRIMPED CORRECTLY. NEW PART ON ORDER. PREVIOUSLY FOUND 3 OT	HER AIRCRAFT OUT OF 5 AIRCRAFT CHECKED WITH VERNATHERM NUTS LOOSE, AND THEY WERE REPLACED WITH NEW VERNATHERM VALVES AFT	ER INSPECTION TO C/W SB 518B.				1	H	7	1 	3O			NT	3A19 					 
1995062300323	19950623	00323	SO 	1995	6	23	95ZZZX3081 	1	19950606	G	7922	75944	VALVE 			PIPER 	PA28 	PA28181 	7102807	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	2332M					287890248				C/W SB 518C (LYC) CHECKED VERNATHERM NUT, FOUND LOOSE, NOT CRIMPED CORRECTLY. NEW PART ON ORDER. PREVIOUSLY FOUND 3 OT	HER AIRCRAFT OUT OF 5 AIRCRAFT CHECKED WITH VERNATHERM NUTS LOOSE, AND THEY WERE REPLACED WITH NEW VERNATHERM VALVES AFT	ER INSPECTION TO C/W SB 518B.				1	L	7	1 	3O				2A13 					 
1995062300324	19950623	00324	SO 	1995	6	23	95ZZZX3082 	1	19950606	G	7922	75944	VALVE 			PIPER 	PA28 	PA28181 	7102807	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	2145L					287990258				C/W SB 518C (LYC) CHECKED VERNATHERM NUT, FOUND LOOSE, NOT CRIMPED CORRECTLY. NEW PART ON ORDER. PREVIOUSLY FOUND 3 OT	HER AIRCRAFT OUT OF 5 AIRCRAFT CHECKED WITH VERNATHERM NUTS LOOSE, AND THEY WERE REPLACED WITH NEW VERNATHERM VALVES AFT	ER INSPECTION TO C/W SB 518B.				1	L	7	1 	3O				2A13 					 
1995062300325	19950623	00325	CE 	1995	6	23	95ZZZX3083 	1	19950606	G	7922	75944	VALVE 			CESSNA	177 	177B 	2073708	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	16185	1908 	240 		L54191	17702491				C/W SB 518C (LYC) CHECKED VERNATHERM NUT, FOUND LOOSE, NOT CRIMPED CORRECTLY. NEW PART ON ORDER. PREVIOUSLY FOUND 3 OT	HER AIRCRAFT OUT OF 5 AIRCRAFT CHECKED WITH VERNATHERM NUTS LOOSE, AND THEY WERE REPLACED WITH NEW VERNATHERM VALVES AFT	ER INSPECTION TO C/W SB 518B.				1	H	7	1 	3O				A13CE 					 
1995062300327	19950623	00327	EA 	1995	6	23	95ZZZX3085 	2	19950511	G	7414	2G6394	MAGNETO 	BOSCH 		DOUG 	DC3 	R4D8 	3021474	WP 	WRIGHT	R1820 	R182080 	67020	EA 					NR 2 ENGINE NR 1	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3906J		1200 			43344				EXCESSIVE MAGNETO DROP ON RUN-UP. SUSPECT CAUSE INTERNAL MAG PROBLEM. DOUGLAS MANUAL RECOMMENDS NO FIELD WORK, JUST RE	PLACE AND SEND FOR OVERHAUL.					2	L	7	2 	4R	4	R		6A2 	E259				 
1995062300328	19950623	00328	CE 	1995	6	23	95ZZZX3086 	1	19950510	G	2150	206SZZC	BEARING 		1019101081 	BEECH 	200 	B200 	1152922	CE 										AC COMP DRIVE	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	8093W	389 				BB1396				AT INSPECTION, AIR COND. DRIVE QUILL SHAFT WAS FOUND SHEARED. DISASSEMBLY FOUND THE AFT SUPPORT BEARING FAILED, IT APPE	ARS THE BEARING SEIZED AND SPUN ON THE DRIVE PULLEY DESTROYING THE PULLEY AND SHEARING THE DRIVE QUILL. THIS IS THE SEC	OND FAILURE OF THIS NATURE ON THIS DRIVE. THE FORWARD BEARING FAILED AT A TOTAL TIME OF 721 HOURS. BOTH BEARINGS WERE 	INSTALLED NEW AT THIS TIME. THE CURRENT FAILURE OCCURRED AT 1111 HRS (389 HRS). PROCEDURES FOR INSTALLATION AND ADJUST	MENT OF ALL PARTS WERE OBTAINED AND FOLLOWED FROM THE BEECHCRAFT B-200 MM. SUSPECT INADEQUATE LUBRICATION IN THE BEARIN	GS WHICH ARE A SEALED BEARING.	1	L	7	2 	4T				A24CE 					 
1995062300329	19950623	00329	CE 	1995	6	23	95ZZZX3087 	1	19950309	G	3244	850T061	TIRE 	GOODYEARAERO	401403 	MTSBSI	MU2 	MU2B40 		CE 										MLG	BAL WT LOOSE 	D				O				OTHER 				E			VIBRATION/BUFFET 			CL	CLIMB 	1			SW	09	458BB	175 				458SA				PILOT COMPLAINED OF MAIN WHEEL SHIMMY AFTER TAKEOFF. ATTEMPTS TO STATIC BALANCE WHEEL ASSY FAILED. BALANCE MARK WOULD 	CHANGE WITH ROTATION. DISASSEMBLED WHEEL ASSY AND FOUND MFG BALANCE PAD LOOSE IN TIRE. REPLACED TIRE. WHEEL BALANCED 	SATISFACTORY. THIS IS THE THIRD TIRE WE FOUND THIS ON. ALL TIRES MFG IN 1992.				1	H	7	2 	3T				A10SW 					 
1995062300331	19950623	00331	SW 	1995	6	23	95ZZZX3089 	1	19950320	G	3510	80270901	INDICATOR 	SCOTT 	89316442 	GULSTM	690TP 	690C 	7630517	SW 										OXYGEN PRESSURE	LEAK 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	67FE	660 			7217	11729				OXYGEN SYSTEM LEAK. FOUND THE LEAK ON THE COPILOT'S MASK. THE FLOW INDICATOR HAS A CLEAR PLASTIC PIECE TO VIEW OXYGEN 	FLOW. THIS IS THE 2ND MASK FOUND IN THE PAST 2 YEARS WITH THE SAME LEAK. THERE IS A 120-DAY BACKORDER ON THIS MASK. T	HIS REQUIRES OPERATOR TO DISCONNECT THE MASK AFTER EACH FLIGHT.				1	H	7	2 	3T				2A4 					 
1995062300332	19950623	00332	EU 	1995	6	23	95ZZZX3090 	1	19950524	G	3230	AN8244D	TEE 			ISRAEL	1124 	1124 	4500102	EU 										GEAR SELECT VLV	SCORED 	D				O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			SW	07	880WW	9188 				195				AIRCRAFT LOST HYDRAULIC PRESSURE IN-FLIGHT DUE TO LOSS OF FLUID. FLUID LEAK CAUSED BY CIRCUMFERENTIAL SCORING ON AN824-	4-D TEE WHERE IT CONTACTS FLARE ON END OF PN 723088-307 UPLOCK TUBE ASSY, BY GEAR SELECTOR VALVE. (REF. I.P.C. 29-10-00	, FIG. 2, ITEMS 16 AND 79.) CAUSE UNKNOWN. INSTALLED NEW TEE.				2	M	7	2 	4F				A2SW 					 
1995062300333	19950623	00333	WP 	1995	6	23	95ZZZX3091 	2	19950314	G	7260	3070394	BRACKET 			ISRAEL	1124 	1124 	4500102	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					ASSORY GEARBOX	BROKEN 	B		A	XEFR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	420JM	5217 				193	P77130			WHILE COWL OPENED FOR NON-RELATED MAINTENANCE, NOTED INBOARD ACCESSORY GEARBOX TO FAN SUPPORT STRUT HANGING LOOSE DUE TO	 BROKEN MOUNTING EARS ON GEARBOX STRUT ROD ATTACH BRACKET. WHILE REPLACING BRACKET AND ADJUSTING PER TFE 731-3 L.M.M. 7	2-60-01, NOTED SLIGHT PRELOAD ON BRACKET AND ROD-END BEARING OF SHAFT REQUIRED TO INSTALL LOWER BOLT. LOOSENING FIT BY 	EXPANDING LOWER ROD-END ONE-HALF TURN PRODUCED A MUCH BETTER FIT WITH NO PRELOAD. SUBMITTER SUSPECTS SLIGHT PRELOAD STR	ESS OVER TIME CREATED FATIGUE. BELIEVE NEW PN 3070394-1 BRACKET MAY BE IMPROVED PART.		2	M	7	2 	4F	4	F		A2SW 	E6WE				 
1995062300334	19950623	00334	WP 	1995	6	23	95ZZZX3092 	1	19950608	G	7714	AN55312	TACH GENERATOR 			DOUG 	DC6 	DC6A 	3021706	WP 										ENG RPM	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	4163Q					43681				TACH NOTED UNSTEADY TACH GENERATOR REPLACED.						2	L	7	4 	4R				6A3 					 
1995062300335	19950623	00335	EU 	1995	6	23	95ZZZX3093 	1	19950606	G	3233	713061505	ACTUATOR 	ALLENACFT 		ISRAEL	1124 	1124 	4500102	EU 										LT MLG	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	217BL		1468 			284				CREW REPORTED GEAR RETRACTION SEEMED SLOW. THE AIRCRAFT WAS JACKED FOR MAINTENANCE TESTS. AFTER SEVERAL GEAR RETRACTIO	N AND EXTENSIONS, A LOUD BANG WAS HEARD FROM THE LEFT GEAR WELL AFTER GEAR RETRACTION. WHEN GEAR WAS SELECTED DOWN, THE	 LEFT GEAR WENT DOWN AND LOCKED WITH GREAT SPEED. SUBSEQUENT INVESTIGATION REVEALED THE ACTUATING ROD HAD BECOME SEPARA	TED FROM THE PISTON INSIDE THE ACTUATING CYLINDER.			2	M	7	2 	4F				A2SW 					 
1995062300336	19950623	00336	CE 	1995	6	23	95ZZZX3094 	1	19950610	G	2150	206SZZC	BEARING 			BEECH 	200 	B200 	1152922	CE 										A/C COMP DRIVE	FAILED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	8093W	32 				BB1396				PILOT REPORTED AIR CONDITIONING WAS NOT WORKING. INSPECTION FOUND FORWARD SUPPORT BEARING HAD FAILED. THIS FAILURE CAU	SED THE DRIVE QUILL TO SHEAR. THIS IS THE THIRD BEARING FAILURE OF THIS NATURE. BOTH BEARINGS WERE REPLACED AT 1111 HR	S. SUBMITTER SUSPECTS BEARINGS ARE INADEQUATELY LUBRICATED.				1	L	7	2 	4T				A24CE 					 
1995062300337	19950623	00337	SW 	1995	6	23	95ZZZX3095 	1	19950512	G	2121	T1GM511C2HC	SWITCH 			GULSTM	690TP 	695 	7630518	SW 										FAN AIR COND	BURNED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	980WM					95034				PILOT REPORTED NO AIR CONDITIONING AND BURNING SMELL. FAN/AIR COND. SELECTOR SWITCH AND POWER WIRES FOR EVAPORATOR FANS	 NR 1 AND NR 2 BURNED. SUSPECT CAUSE DUE TO NR 1 EVAPORATOR FAN FAILURE LAST MONTH. WIRES AND SWITCH WERE HEATED, STAR	TING CORROSION CREATING RESISTANCE, BURNED SWITCH AND THEN FAILED. RECOMMEND INSPECTION OF THIS AREA AT EVAPORATOR FAN 	FAILURE.			1	H	7	2 	3T				2A4 					 
1995062300338	19950623	00338	SO 	1995	6	23	95ZZZX3096 	1	19950519	G	2700		TERMINAL 			GULSTM	G1159 	G1159 	3953505	SO 										FLT CONTROL	SEPARATED 	B			QK2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	13	659WL					204				DURING FABRICATION OF A REPLACEMENT PRIMARY FLIGHT CONTROL CABLE FOR A TRANSPORT CATAGORY AIRCRAFT UTILIZNG AN AT-520TK 	CABLE TERMINAL SWAGER KIT, AN A AND P TECHNICIAN EXPERIENCED A TOTAL SEPARATION OF THE THREADED PORTION OF A MS2126066-L	H TERMINAL AT THE CUTTER RADIUS.				2	L	7	2 	4F			RT	A12EA 					 
1995062300339	19950623	00339	WP 	1995	6	23	95ZZZX3097 	1	19950424	G	5312	97537513	BULKHEAD 			DOUG 	DC8 	DC873F 	302199F	WP 										FS 680	CRACKED 	B	S		EE4Y	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	23	873SJ	72486				46091				FOUND 11 INCH CRACK AT THE LEFT SIDE OF BULKHEAD PRESSURE DOME AT BS 680. PERFORMED TEMPORARY REPAIR PER MCDONNELL DOUG	LAS RECOMMENDATION.					2	L	7	4 	4F			RT	4A25 					 
1995062300340	19950623	00340	CE 	1995	6	23	95ZZZX3098 	1	19950616	G	2121	261940610	DIFFUSER TUBE 			LEAR 	35 	31 	5170530	CE 										CABIN RT	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	92EC	830 				024				DURING TROUBLESHOOTING A WINDSHIELD DEFOG PROBLEM AND RT AFT CABIN 'HOT' AREA, THE RIGHT CABIN AIR DIFFUSER INNERTUBE WA	S FOUND CRACKED ALONG THE COMPLETE CIRCUMFERENCE OF THE ASSEMBLY WELD. A LOSS OF AIR FLOW TO THE WINDSHIELD DEFOG AREA,	 PLUS A GREATER VOLUME OF AIR TO THE CABIN DIFFUSER CHAMBER OF THE ASSEMBLY RESULTED. TWO RIVETS WHICH AID IN SUPPORTIN	G THE INNERTUBE WITHIN THE DIFFUSER HAD WORKED LOOSE CAUSING STRESS ON THE WELD.			2	L	7	2 	4F			RT	A10CE 					 
1995062300341	19950623	00341	EU 	1995	6	23	95ZZZX3099 	1	19950608	G	2730	25CT223	ELEV QUADRANT 			HWKSLY	DH125 	HS125600A 	4230158	EU 										AFT OF HORZ STAB	CORRODED 	B	S	A	JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	600G	9534 				256066				DURING A VISUAL INSPECTION OF THE ELEVATOR QUADRANT, WHITE POWDER WAS NOTED AROUND THE UPPER CONTROL CABLE ATTACH POINT 	BARREL. REMOVAL OF BOTH CABLES FOUND DEEP CORROSION IN THE CONTROL CABLE ATTACH POINTS ON THE QUADRANT, THE 2400-HOUR 2	4 AND 48-MONTH INSPECTION CALL OUT FOR AN INSPECTION OF COMPONENTS AND CABLES IN THE HORIZONTAL STABILIZER AREA. NOTHIN	G ABOUT REMOVING CABLES, WITHOUT REMOVING THE CONTROL CABLES AND BARRELS FROM QUADRANT, THIS AREA WOULD NOT BE LOOKED AT	.		2	L	7	2 	4J				A3EU 					 
1995062300421	19950623	00421	EU 	1995	6	23	95ZZZX3101 	1	19950508	G	6320	2101005241	BOLT 			BOLKMS	105 	BO105CBS 	5626008	EU 										TRANSMISSION	NOT DRILLED 	B			CZ4R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	01	492HL					S803				MAINTENANCE MANUAL FOR BO-105 CALLS FOR TRANSMISSION FILTER BOLT, PN 2101005241, TO BE SAFETY WIRED, BUT THE BOLT HAS NO	 HOLE DRILLED. AT FURTHER CHECK OF 105 FLEET, REVEALS NONE OF THE BOLTS ARE DRILLED. DRILLED BOLT AND SAFETIED. EITHE	R MM SHOULD BE CHANGED OR BOLT SHOULD BE DRILLED FROM NEW.				1	G	7	2 	3U			NC	H3EU 					 
1995062300422	19950623	00422	GL 	1995	6	23	95ZZZX3102 	2	19950507	G	7314	6899253	PUMP 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE FUEL	LEAKING 	B			CZ4R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	01	492HL	3117 				S803				ENGINE DRIVEN FUEL PUMP FOUND LEAKING FUEL FROM BEARING SEAL. REPLACED PUMP.						1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995062300423	19950623	00423	EU 	1995	6	23	95ZZZX3103 	1	19950425	G	2841	117405403	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL QTY	MALFUNCTION 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117M	16 			1150	S7023				NR 1 SUPPLY NEEDLE DROPPED TO ZERO THEN CAME BACK UP. SAME PROBLEM AS BEFORE. WAS TESTED AND NO MALFUNCTION NOTED, BUT	 HERE IT IS AGAIN FAILED AFTER ONLY 12 DAYS SINCE DIAGNOSIS.					1	G	7	2 	3U				H13EU 					 
1995062300424	19950623	00424		1995	6	23	95ZZZX3104 	4	19950512	G	3453	4530103	RECEIVER 			BELL 	206 	206L1 	1182107	SW 										COCKPIT LORAN	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	224LF	3 			29255	45199				LORAN RECEIVER UNIT WOULD NOT POWER UP.						1	G	7	1 	3U				H2SW 					 
1995062300425	19950623	00425		1995	6	23	95ZZZX3105 	4	19950424	G	3446	78806060865	STORMSCOPE 		WX1000E 	BOLKMS	117 	BK117C1 		EU 										COCKPIT	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	60 			FF10300042	7505				STORMSCOPE, NO INDICATION IT IS PROCESSING.						1	G	7	2 	3U				H13EU 					 
1995062300426	19950623	00426	EU 	1995	6	23	95ZZZX3106 	1	19950519	G	7714	117905303	TACH 			BOLKMS	117 	BK117B1 	5626012	EU 										TRIPLE TACH	STICKING 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	460H	62 			433	7142				TRIPLE TACH STICKING.						1	G	7	2 	3U				H13EU 					 
1995062300427	19950623	00427	SW 	1995	6	23	95ZZZX3107 	1	19950418	G	6330	206033518007	BEARING 			BELL 	206 	206L1 	1182107	SW 										NODAL BEAM	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	5741Y	449 				45467				NODAL BEAM DOWN STOPS ARE WORN. (BEARING WORN) 2 EACH. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995062300428	19950623	00428	EU 	1995	6	23	95ZZZX3108 	1	19950530	G	6520	4639311003	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	DAMAGED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	626MB				934	7109				DAMAGED ROLLERS (5 PLACES) ON ROLLER BEARING.						1	G	7	2 	3U				H13EU 					 
1995062300429	19950623	00429	EU 	1995	6	23	95ZZZX3109 	1	19950430	G	6320	6607A2114	SWITCH 			BOLKMS	105 	BO105LSA3 	5626020	EU 										XMSN OIL PRESS	DEFECTIVE 	B			TI1R	O				OTHER 				N			FALSE WARNING 			CR	CRUISE 	1			SW	05	911SV	243 			02388	2033				NR 1 TRANSMISSION OIL PRESSURE LIGHT ON IN-FLIGHT, INTERMITTENTLY. REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU 					 
1995062300430	19950623	00430		1995	6	23	95ZZZX3110 	4	19950509	G	3421	6224808006	INDICATOR 			BEECH 	200 	B200 	1152922	CE 										COCKPIT ADI	STUCK 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	75LV				1559	BB1075				ADI STUCK IN PITCH AND RED FLAG 'ATT'. THIS IS SAME PROBLEM AS BEFORE.						1	L	7	2 	4T				A24CE 					 
1995062300495	19950623	00495	SW 	1995	6	23	95ZZZX3111 	1	19950503	G	6230	206010452109	SUPPORT 			BELL 	206 	206L3 	1182108	SW 										SWASHPLATE	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	5741Y	3153 			RE4689	45467				IN COMPLIANCE WITH A.S.B. 206L-93-89, REV B, INSPECTION OF SUPPORT. WORN BEYOND LIMITS. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995062300496	19950623	00496	SW 	1995	6	23	95ZZZX3112 	1	19950517	G	6410	212311007101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	2FOR				27	31151				BEARING CAGE SPOT WELD, EXTENDING TOO HIGH.						1	G	7	1 	4U				H4SW 					 
1995062300497	19950623	00497	SW 	1995	6	23	95ZZZX3113 	1	19950517	G	6410	212311007101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	2FOR				90	31151				BEARING CAGE SPOT WELD, EXTENDING TOO HIGH.						1	G	7	1 	4U				H4SW 					 
1995062300498	19950623	00498	SW 	1995	6	23	95ZZZX3114 	1	19950413	G	6410	212311008101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	2FOR				453	31151				BEARING CAGE SPOT WELD EXTENDING TOO HIGH.						1	G	7	1 	4U				H4SW 					 
1995062300499	19950623	00499	SW 	1995	6	23	95ZZZX3115 	1	19950413	G	6410	212311008101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	2FOR				226	31151				BEARING CAGE SPOT WELD EXTENDING TOO HIGH.						1	G	7	1 	4U				H4SW 					 
1995062300500	19950623	00500	SW 	1995	6	23	95ZZZX3117 	1	19950518	G	6410	212311007101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05					354					BEARING DEFECTIVE, WELD IN CAGE AREA.						1	G	7	1 	4U				H4SW 					 
1995062300501	19950623	00501	SW 	1995	6	23	95ZZZX3118 	1	19950518	G	6410	212311007101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05					376					BEARING DEFECTIVE, WELD IN CAGE AREA.						1	G	7	1 	4U				H4SW 					 
1995062300502	19950623	00502	SW 	1995	6	23	95ZZZX3119 	1	19950518	G	6410	212311008101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05					163					BEARING DEFECTIVE, WELD IN CAGE AREA.						1	G	7	1 	4U				H4SW 					 
1995062300503	19950623	00503	SW 	1995	6	23	95ZZZX3120 	1	19950518	G	6410	212311008101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05					154					BEARING DEFECTIVE, WELD IN CAGE AREA.						1	G	7	1 	4U				H4SW 					 
1995062300504	19950623	00504	SW 	1995	6	23	95ZZZX3121 	1	19950413	G	6410	212311007101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	2FOR				3	31151				BEARING CAGE SPOT WELD EXTENDING TOO HIGH. REPLACE BEARINGS.						1	G	7	1 	4U				H4SW 					 
1995062300505	19950623	00505	SW 	1995	6	23	95ZZZX3122 	1	19950413	G	6410	212311007101	BEARING 			BELL 	212 	212 	1181420	SW 										GRIP	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	2FOR				146	31151				BEARING CAGE SPOT WELD EXTENDING TOO HIGH. REPLACE BEARINGS.						1	G	7	1 	4U				H4SW 					 
1995062300506	19950623	00506	GL 	1995	6	23	95ZZZX3123 	2	19950521	G	7323	23007506	GOVERNOR 			BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE N2	FAILED 	D				O				OTHER 				J			WARNING INDICATION 			LD	LANDING 	1			SW	99	21470		1746 		20719	3647	CAE270043			AIRCRAFT FLEW IN NORMAL CRUISE FOR APPROXIMATELY 1.7 HOURS. PILOT LOWERED COLLECTIVE FOR ROUTINE LANDING. GOVERNOR RES	PONDED ERRATIC WITH OSCILLATING N2, THEN STABILIZED AT 103 PERCENT N2. INVESTIGATION SHOWED WHEEL GEAR CAME LOOSE FROM 	DRIVE SHAFT. AIRCRAFT MADE SAFE LANDING. CEB 1140 REV. 4 WAS FOUND EMBODIED. ALLISON NOTIFIED ON 250 REPORT SNK102002	.			1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995062300508	19950623	00508		1995	6	23	95ZZZX3125 	4	19950517	G	2562	7A1132	ELT 	NARCO 	SHARC7 	CESSNA	310 	310Q 	2074242	CE 										G-SWITCH	INOPERATIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	69573					310Q0791				G-SWITCH DOES NOT FUNCTION ON ELT; OTHERWISE, WORKS OKAY. SUBMITTER FOUND 6 SHARC ELT'S WITH BAD G-SWITCHES IN THE PAST	 12 MONTHS.					1	L	7	2 	3O				3A10 					 
1995063000001	19950630	00001	CE 	1995	6	30	95ZZZX3126 	1	19950417	G	2730	05341221	BELLCRANK 			CESSNA	172 	172P 	2072436	CE 										ELEVATOR	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	98776	1889 				17276350				DURING ANNUAL INSPECTION, ELEVATOR BELLCRANK (REAR) WAS FOUND TO HAVE BEARING LOOSE IN BELLCRANK.						1	H	7	1 	3O			NT	3A12 					 
1995063000003	19950630	00003	SO 	1995	6	30	95ZZZX3128 	1	19950530	G	2430	P1D	WIRE 			PIPER 	PA28 	PA28181 	7102807	SO 										BATTERY	BURNED 	B			YA1R	K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			SW	09	2273Q	5308 				287790359				ALUMINUM BATTERY CABLE BECAME RESISTIVE CAUSING BATTERY TERMINAL CONNECTOR TO OVERHEAT AND MELT OFF OF G-35 BATTERY. CO	MPLIANCE WITH PIPER SB 836A WOULD HAVE PREVENTED THIS PROBLEM.					1	L	7	1 	3O			 	2A13 					 
1995063000004	19950630	00004	GL 	1995	6	30	95ZZZX3129 	1	19950526	G	6120	191783	PROP CONTROL 			BLANCA	17 	1730A 	1220433	GL 										PROP GOV	BOLT WORN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	14793	1529 				7430				WHILE RUNNING THE ACFT AFTER AN ANNUAL INSPECTION, FOUND PROP CONTROL VERY STIFF. EVENTUALLY, AFTER ATTEMPTING TO MOVE 	THE CONTROL, IT BROKE OFF. THE POINT OF BREAK WAS APPROXIMATELY 8 INCHES FORWARD ON THE CONTROL KNOB. IN REPLACING THE	 CABLE, FOUND THE BOLT SECURING THE CABLE TO THE PROP GOVERNOR WAS WORN.				1	L	7	1 	3O				A18CE 					 
1995063000005	19950630	00005	SO 	1995	6	30	95ZZZX3130 	2	19950516	G	7314	6493683AIR	PUMP 			PIPER 	PA34 	PA34200T 	7103406	SO 	CONT 	O360 	LTSIO360EB 	17025	SO 					RT ENG FUEL	SEAL LEAK 	D				O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			GL	03	76PB	332 			B119404BR	347970067	266445R			ON 2-21-95, THE RIGHT ENGINE DEVELOPED A SURGE ON F.F. AND M.A.P. DURING CRUISE. AFTER TROUBLESHOOTING, DISCOVERED ANER	OID SEAL HAD FAILED. THE PUMP WAS REPAIRED AND REINSTALLED (PART TT 257.5.) ON 5-16-95, THE SAME THING HAPPENED TO THE	 RIGHT ENGINE 62.6 HRS AFTER IT WAS REPAIRED. GENUINE T.C.M. PARTS WERE USED AND IT WAS REPAIRED BY A T.C.M. DEALER UND	ER WARRANTY. NOTE: THE PUMPS T.B.O. IS 1800 HOURS.			1	L	7	2 	3O	3	O		A7SO 	E9CE				 
1995063000006	19950630	00006	SO 	1995	6	30	95ZZZX3131 	2	19950531	G	8530	630046	PISTON PIN 			CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					NR 5 CYLINDER	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	25	1587G	523 				421B0817	267282R			AFTER REMOVAL OF NR 5 CYLINDER DUE TO LOW COMPRESSION (PAST THE RINGS), NOTED THE PISTON PIN WAS SHORTER THAN USUAL. FR	OM ITS APPEARANCE, IT WAS FROM A SMALLER BORE CYLINDER LIKE AN O-470. SHORT PINS WERE ALSO FOUND IN NR 3, NR 4, AND NR 	6.				1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995063000007	19950630	00007	SO 	1995	6	30	95ZZZX3132 	2	19950608	G	8530	649358	CYLINDER 			CESSNA	210 	T210N 	2073456	CE 	CONT 	O520 	TSIO520R 	17040	SO 					NR 4 CYL HEAD	SEPARATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	6501N		18 			21063074	517100			CYLINDER HEAD SEPARATED COMPLETELY FROM BARREL. TOTAL TIME SINCE RE-BARREL, 18 HRS.						1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995063000008	19950630	00008	SO 	1995	6	30	95ZZZX3133 	1	19950608	G	2434	758250	BRUSH 	CHRYSLER 	4111810 	PIPER 	PA28 	PA28236 	7102815	SO 										ALTERNATOR	WORN 	G				A				UNSCHED LANDING 				H			ELECT. POWER LOSS-50 PC 			CR	CRUISE 	1			GL	03	8174X	1700 				288011067				PILOT EXPERIENCED ALTERNATOR FAILURE WHILE ON IFR FLIGHT PLAN. LANDED WITHOUT INCIDENT. MECHANIC REPLACED BRUSHES IN A	LTERNATOR AND RETURNED AIRCRAFT TO SERVICE.					1	L	7	1 	3O				2A13 					 
1995063000009	19950630	00009	SO 	1995	6	30	95ZZZX3134 	2	19950419	G	8520		CRANKCASE 			BEECH 	55 	95B55 	1152706	CE 	CONT 	O470 	IO470L 	17026	SO 					NR 4 CYLINDER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	06	213CH	733 				TC2298	272888R			DURING INSPECTION, A .75 INCH CRACK WAS FOUND RADIATING UPWARD FROM THE AFT UPPER MOUNTING STUD FOR NR 4 CYLINDER. THE 	ENGINE HAD 732.9 HOURS SINCE BEING REBUILT BY THE FACTORY AND HAD BEEN IN SERVICE FOR 24 MONTHS.					1	L	7	2 	3O	3	O		3A16 	3E1				 
1995063000010	19950630	00010	SO 	1995	6	30	95ZZZX3135 	1	19950606	G	7921	8526250	COOLER 	LORINORDAM 	APO7AU00603 	PIPER 	PA28 	PA28235 	7102810	SO 										ENGINE OIL	RUPTURED 	D				K				NONE 				K			FLUID LOSS 			CR	CRUISE 	1			WP	25	33LH	2600 			RR599	2811098				AFTER 35 MINUTES OF A 45-MINUTE FLIGHT, THE OIL TEMPERATURE STARTED TO RISE, BUT NEVER HIT RED LINE. A SAFE LANDING WAS	 MADE. OIL WAS DRIPPING OFF RT SIDE OF COWL AND FIREWALL ENGINE WAS WASHED DOWN AND LEAK CHECKED REVEALED THE OIL COOLE	R HAD SPLIT AT THE BEAD LINE OF THE LOWER PASSAGE WAY. NEW COOLER HAD TO BE INSTALLED.				1	L	7	1 	3O				2A13 					 
1995063000011	19950630	00011	CE 	1995	6	30	95ZZZX3136 	1	19950511	G	7120	630695	BRACKET 			BEECH 	55 	E55 	1152732	CE 										LOWER ENG MOUNT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	06	777BC	1266 				TE1116				DURING 50-HOUR INSPECTION, A SMALL .50 INCH CRACK WAS NOTED ON THE LOWER LEFT ENGINE MOUNT BRACKET OF THE LEFT ENGINE. D	YE PENETRANT INSPECTION CONFIRMED THE EXISTANCE OF THE CRACK. DURING ANNUAL INSPECTION 50 HOURS EARLIER, NO CRACKS WERE	 NOTED ON THIS PORT WHILE COMPLYING WITH AD 94-09-07 AND AD 95-03-14 WHICH REPLACED IT. RECOMMEND BEING SURE TO COMPLY 	WITH LATEST AD ON THIS BRACKET AND TO VISUALLY INSPECT THE BRACKET ANY TIME WHEN WORKING IN THE AREA.			1	L	7	2 	3O				3A16 					 
1995063000012	19950630	00012	EA 	1995	6	30	95ZZZX3137 	2	19950605	G	7414	M3637	CONTACT 	SLICK 	4250R 	CESSNA	172 	172N 	2072434	CE 	LYC 	O360 	O360A4A 	41514	EA 					MAGNETO	POINTS CLOSED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	734RA	68 			1010138	17269044	L1032136F			A MISS ON ONE MAG CAUSED REMOVAL AND EXAMINATION OF THE MAG. THE POINT GAP WAS CLOSED DOWN AND THE POINTS WERE OF A TYP	E NOT SEEN IN THIS SERIES MAG BEFORE. SINCE THEY HAD BEEN INSTALLED A SHORT TIME BEFORE, A CALL TO THE INSTALLING AGENC	Y WAS MADE. ACCORDING TO THEIR SLICK MANUAL, M3637 WAS CORRECT (1993). ACCORDING TO THE '94 (AND '89) MANUAL, M3081 WO	ULD BE CORRECT. A CALL TO SLICK VERIFIED THE MISTAKE IN THE 1993 MANUAL.			1	H	7	1 	3O	3	O	NT	3A12 	E286				 
1995063000013	19950630	00013	CE 	1995	6	30	95ZZZX3138 	1	19950504	G	7120	505403034	SUPPORT 			CESSNA	421 	421C 	2076016	CE 										LT SIDE ENG MT	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	110KU	3669 				421C1401				FOUND CRACK IN ENGINE MOUNT TOP SUPPORT OF BEAM. LOCATED ON LT SIDE. THIS SUPPORT ALSO SUPPORTS THE TURBOCHARGER BRACE	. THIS PART IS THE REAR CROSSOVER OF THE ENGINE BEAM.					1	L	7	2 	3O				A7CE 					 
1995063000014	19950630	00014	CE 	1995	6	30	95ZZZX3139 	1	19950501	G	3150		CIRCUIT BOARD 			BEECH 	55 	95B55 	1152706	CE 										PANEL ANNUN	DEFECTIVE 	B	L		UKJR	L				ABORTED APPROACH 				P			NO WARNING INDICATION 			AP	APPROACH 	1			EA	23	3822L	1694 				TC2373				DURING GEAR EXTENSION, NO INTRANSIT OR 3 GREEN INDICATIONS. EMERGENCY GEAR EXTENSION USED TO ENSURE GEAR DOWN. TROUBLE	SHOOTING FOUND CIRCUIT BOARD FOR ANNUNCIATOR PANEL TO BE THE PROBLEM.					1	L	7	2 	3O				3A16 					 
1995063000015	19950630	00015	EA 	1995	6	30	95ZZZX3140 	2	19950512	G	7414	ES10382585	BREAKER POINT 	BENDIX 	3FLN3000 	MOONEY	M20 	M20C 	5870208	SW 	LYC 	O360 	IO360A3B6 	41514	EA 					CAM FOLLOWER	EXCESS WEAR 	B	L	A	DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	6079Q	3 			C090010G	3255	l2568151A			DURING 100-HOUR PHASE INSPECTION, MAG WAS REPLACED WITH OVERHAULED UNIT. TWO AND ONE-HALF FLIGHT HOURS LATER, MAG FAILE	D. FOUND CAM FOLLOWER ON BOTH BREAKER POINTS EXCESSIVELY WORN. MAG TIMING OUT OF LIMITS. SUBMITTER SUGGESTS MFG CHANG	E FROM PHENOLIC TO PLASTIC CAM FOLLOWER MATERIAL TO BE THE CONTRIBUTING FACTOR.				1	L	7	1 	3O	3	O		2A3 	1E10				 
1995063000016	19950630	00016	SO 	1995	6	30	95ZZZX3141 	1	19950517	G	7922	LW120980210	VALVE 			PIPER 	PA32 	PA32RT300 	7103215	SO 										THERMO BYPASS	MISSING 	B	P		BLBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	17	36398					7885157				WHEN COMPLYING WTIIH LYCOMING SB 518C (COPY ATTACHED) FOUND CRIMPED NUT HOLDING VALVE TOGETHER WAS MISSING. UPON FURTHE	R INVESTIGATION, FOUND NUT LODGED IN HOSE ELBOW TO OIL COOLER.					1	L	7	1 	3O				A3SO 					 
1995063000017	19950630	00017	SO 	1995	6	30	95ZZZX3142 	1	19950511	G	3250	4438600	ARM ASSY 			PIPER 	PA24 	PA24250 	7102404	SO 										NLG STEERING	BOLTS PULLED 	D	P			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	11	6771P					241902				ARM ASSEMBLY THAT IS MOUNTED ON TOP OF NOSE GEAR, HELD IN PLACE BY 3 BOLTS (AN3H-7A) CAME LOOSE. THE THREADS WERE PULLE	D OUT OF TOP OF STRUT. THIS ALLOWED UNIT TO BIND ON STEERING BRACKET, WOULD NOT ALLOW GEAR TO FULLY EXTEND, TRIPPING CI	RCUIT BREAKER. THIS PART SHOULD BE INSPECTED VERY CAREFULLY AT ANNUAL, BECAUSE THEY GET BROKEN BY TOWING.				1	L	7	1 	3O				1A15 					 
1995063000018	19950630	00018	CE 	1995	6	30	95ZZZX3143 	1	19950531	G	2752	B36	BEARING 			BEECH 	90 	C90A 	1152911	CE 										FLAP DRIVE	MISSING NEEDLES 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	484JA	3378 				LJ1196				DURING THE FLAP DRIVE INSPECTION AND LUBRICATION EVENT, FOUND THAT THE NEEDLE BEARINGS WERE MISSING FROM THE BEARING HO	USING AT THE WORN GEAR UPPER BEARING. ONLY THE BEARING SHELL WAS INSTALLED. THERE WAS NO EVIDENCE IN THE GEARBOX OF TH	E MISSING NEEDLE BEARINGS.				1	L	7	2 	3T			RT	3A20 					 
1995063000019	19950630	00019	SO 	1995	6	30	95ZZZX3144 	2	19950508	G	7414	6310	MAGNETO 	SLICK 		BEECH 	36 	A36 	1151604	CE 	CONT 	O550 	IO550B 		SO 					RT MAG	MISTIMED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	21	5538N					E2541	296580R			INVESTIGATED PILOT COMPLAINT OF EXCESSIVE RPM DROP OF RIGHT MAGNETO ON RUN-UP. FOUND LEFT MAGNETO TIMED AT 24 DEGREES B	TC AND RIGHT MAGNETO AT 13 DEGREES BTC. REMOVED AND PARTIALLY DISASSEMBLED RIGHT MAGNETO. FOUND INTERNAL TIMING CORREC	T AND VISUAL INSPECTION SHOWED NOTHING ABNORMAL. IT SHOULD BE NOTED THAT THIS IS A FACTORY REBUILT ENGINE WITH BUILD DA	TE OF 12-07-94 AND THE ORIGINAL TCM WHITE TORQUE SEAL WAS FOUND ON THE ENGINE CASE TO MAGNETO MATING POINT INDICATING IT	 LEFT THE FACTORY IN THIS CONDITION.		1	L	7	1 	3O	3	O		3A15 	E3SO				 
1995063000020	19950630	00020	SO 	1995	6	30	95ZZZX3145 	1	19950608	G	3030	464356	HEAT ELEMENT 			PIPER 	PA28 	PA28181 	7102807	SO 										PITOT MAST	FAILED 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	8262K	1113 				288290165				DURING ANNUAL INSPECTION, PITOT MAST WAS CHECKED FOR PROPER OPERATION OF THE HEATER. WHILE THE MAST WAS WARM TO THE TOU	CH, IT WAS NOT REALLY GETTING HOT. FURTHER INVESTIGATION SHOWED THAT ONE OF THE HEATING ELEMENTS WAS BURNED OUT. P/N I	NVOLVED 464-356 AND 464-357.				1	L	7	1 	3O				2A13 					 
1995063000021	19950630	00021	EA 	1995	6	30	95ZZZX3146 	2	19950526	G	8530	LW11633	CYLINDER 			PIPER 	PA38 	PA38112 	7103812	SO 	LYC 	O235 	O235L2C 	41505	EA 					NR 1,2,3,4	PITTED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	2554D	3547 	1546 			3879A0369	L1813115			UPON REMOVAL OF CYLINDERS (PN LW-1663) FOR ACCOMPLISHMENT OF STC SE792NW (INCREASE IN HORSEPOWER FROM 112 HP TO 125 UP),	 ALL FOUR CYLINDER WALLS SHOWED CONSIDERABLE PITTING. CAMSHAFT (PN 75706) LOBES AND LIFTERS (PN 71105) SHOWED FLAT SPOT	TING, PITS, AND EXCESSIVE WEAR. SUSPECT CONDITIONS WERE CAUSED BY RUSTING WHICH OCCURRED WHEN AIRCRAFT WAS INACTIVE.				1	L	7	1 	3O	3	O		A18SO 	E223				 
1995063000022	19950630	00022	SO 	1995	6	30	95ZZZX3147 	1	19950526	G	5312	7755402	BULKHEAD 			PIPER 	PA38 	PA38112 	7103812	SO 										FS 240.62	CRACKED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	2554D	3547 	1546 			3879A0369				UPON INSPECTION FOR COMPLIANCE WITH AD 82-27-08, THE FOLLOWING DISCREPANCIES WERE NOTED: A. FS 240.62 BULKHEAD (PN 775	54002) HAD 2 CRACKS APPROXIMATELY 2 INCHES LEFT AND RIGHT OF THE TAIL TIE-DOWN FITTING. THE CRACKS EXTENDED THROUGH THE	 BULKHEAD FLANGES.				1	L	7	1 	3O				A18SO 					 
1995063000023	19950630	00023	SO 	1995	6	30	95ZZZX3148 	1	19950526	G	5311	7746709	FRAME 			PIPER 	PA38 	PA38112 	7103812	SO 										FS 99.29	BUCKLED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	2554D	3547 	1546 			3879A0369				FS 99.29 FRAME ASSEMBLY (PN 77467-09) WAS FOUND BUCKLED IN THE VICINITY OF THE RT WING AFT ATTACH POINT. PIPER SERVICE 	KIT 765-177 REAR SPAR FRAME STIFFENER HAD NOT BEEN INSTALLED. DAMAGE APPEARS TO HAVE BEEN CAUSED BY POSSIBLE HARD LANDI	NG.				1	L	7	1 	3O				A18SO 					 
1995063000024	19950630	00024	SO 	1995	6	30	95ZZZX3149 	1	19950526	G	5751		SKIN 			PIPER 	PA38 	PA38112 	7103812	SO 										RT AILERON	BENT 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	2554D	3547 	1546 			3879A0369				THE LOWER RT AILERON SKIN IN THE VICINITY OF THE OUTBOARD HINGE WAS BENT OUTWARD FROM ITS NORMAL POSITION. THIS ALLOWED	 THE AILERON SKIN TO CATCH INTERMITTENTLY ON THE LOWER, WING SKIN WHICH WOULD PREVENT THE AILERON FROM MOVING DOWN PAST 	NEUTRAL. IF THIS OCCURRED IN-FLIGHT, LOSS OF AILERON CONTROL COULD HAVE BEEN POSSIBLE.				1	L	7	1 	3O				A18SO 					 
1995063000025	19950630	00025	EU 	1995	6	30	95ZZZX3150 	1	19950612	G	5520	12621022	CAP SCREW 			SLNSBY	T67 	T67M260 	8323006	EU 										OTBD TIP ELEV	WRONG PART 	B		A	UNER	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	03	3161F	13 				2189				AFTER 13.0 HOURS OF FLIGHT AND DURING A TRANSFER INSPECTION AT THE USAFA, A UNC MAINTENANCE TECHNICIAN DISCOVERED THE WR	ONG CAP SCREW INSTALLED IN THE RIGHT OTBD ELEVATOR (T67M031-008) ATTACHMENT BRACKET. THE SCREW THREADS WERE NOT ENGAGED	 IN THE ANCHORING NUTPLATE. THE SCREW WAS .75 INCH TOO SHORT. IF IT WERE NOT FOR A SECONDARY SECURING CIRCLIP, THE SCR	EW COULD HAVE DISLODGED DURING FLIGHT. THE ENTIRE USAF SLINGSBY FLEET HAS BEEN INSPECTED. NO OTHER REPORTED CASES. TH	E ELEVATOR ASSEMBLY IS ASSEMBLED IN ENGLAND. TEXAS ASSEMBLY MAY HAVE DISASSEMBLED DURING PRODUCTION. THIS IS A SAFETY 	OF FLIGHT ISSUE.	1	L	7	1 	3O			NT	A73EU 					 
1995063000026	19950630	00026		1995	6	30	95ZZZX3151 	4	19950523	G	3455	G686201	CONTROL HEAD 	GABLES 		AMD 	FALC50	FALCON50MYST	2730106	EU 										NR 2 ADF	SHORTED 	B			AMCR	A				UNSCHED LANDING 				O			OTHER 			NR	NOT REPORTED 	1			GL	09	40TH		744 		119	85				CIRCUIT BREAKER FOR THE NR 2 ADF TRIPPED. WAS RESET, AND BREAKER TRIPPED AGAIN WITHIN SECONDS. AFTER RETURNING TO BASE	, TROUBLESHOOTING REVEALED THERE WAS A SHORT IN THE CONTROL PANEL FOR THE NR 2 ADF. AFTER REMOVING THE CONTROL HEAD, TH	E UNIT SMELLED BURNED. UNIT WAS SUBMITTED TO MANUFACTURER FOR REPAIR.				2	L	7	3 	4F				A46EU 					 
1995063000027	19950630	00027	NM 	1995	6	30	95ZZZX3152 	1	19950613	G	5711	50374050	SPAR 			BOEING	707 	707330C 	138367G	NM 										FS 387-640	CORRODED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	770JS					19626				DURING A C-CHECK, RT WING FORWARD SPAR LOWER CHORD, FSS 387-640, FOUND WITH CORROSION AROUND HI-LOCKS. PART REPLACED. A	CFT TT 52,324.7 HOURS. ACFT TC 20,628 CYCLES.					2	L	7	4 	4F				4A26 					 
1995063000028	19950630	00028	SO 	1995	6	30	95ZZZX3153 	1	19950524	G	2720	PE640042	BUSHING 			EMB 	110 	EMB110P1 	3260122	SO 										PILOT RUD PEDAL	CRACKED 	B		A	BIOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	710NH					110250				WHEN C/W SB 110-027-0080, RUDDER PEDAL PIVOT BUSHINGS, FOUND ALL 8 BUSHINGS ON PILOT'S SIDE WITH CRACKS, 2 OF THESE BUSH	INGS WERE BROKEN IN HALF. TIME ON PARTS UNKNOWN. ACFT TT: 14,778.1 HOURS. P/N OF BUSHINGS: PE64004-2.					1	L	7	2 	4T				A21SO 					 
1995063000029	19950630	00029	EA 	1995	6	30	95ZZZX3154 	1	19950526	G	2911	2770571105	ACCUMULATOR 			CNDAIR	CL601 	CL6013A 	8070802	EA 										NR 3 SYSTEM	LEAKING 	C				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	25	339CF	1640 			0246A	5084				'NR 3 HYDRAULIC SYSTEM HAS A LOUD NOISE WHEN PUMPS TURNED ON.' FOUND PRE-CHARGE ON ACCUMULATOR LOW. JACKED AIRCRAFT AN	D REPLACED ACCUMULATOR. REPLACED ACCUMULATOR AND SERVICED SYSTEM WITH FLUID. RETRACTED GEAR 5 CYCLES PER MM TO BLEED S	YSTEM. SERVICED SYSTEM WITH FLUID, LOWERED AIRCRAFT, REMOVED JACKS. SYSTEM OPERATED NORMALLY AND LEAK CHECK GOOD.				2	L	7	2 	4F			RT	A21EA 					 
1995063000030	19950630	00030	NM 	1995	6	30	95ZZZX3155 	1	19950613	G	5711	50873922	SPAR 			BOEING	707 	707338C 	138367N	NM 										FS 360-586	CORRODED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	770JS					19626				DURING A C-CHECK, THE RT WING FORWARD SPAR UPPER CHORD BETWEEN FSS 360 AND FSS 586 FOUND WITH CORROSION AROUND HI-LOCKS.	 PART REPLACED. ACFT TT 52,324.7 HOURS. ACFT TC 20,628 CYCLES.					2	L	7	4 	4F				4A26 					 
1995063000031	19950630	00031	NM 	1995	6	30	95ZZZX3156 	1	19950613	G	5415	6595600	FITTING 			BOEING	707 	707338C 	138367N	NM 										NR 2-3 PYLON	CRACKED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	770JS					19626				WHILE PERFORMING A C3 CHECK AND THE A.A.C.I.P. SB 3173, FOUND NR 2 AND NR 3 OVERWING FITTING CRACKED FORWARD OF FUSELAGE	 ATTACHMENT BOLT. INSTALLED NEW TYPE FITTING: NR 1, PYLON AT: ATT 51,029/ATC 20,325, FEB 91. NR 2 AND NR 3, ATT 52,	324/ATC 20,629 MAY 95. NR 4, REPLACED, PREVENTIVE ONLY, MAY 95.				2	L	7	4 	4F				4A26 					 
1995063000032	19950630	00032	EU 	1995	6	30	95ZZZX3157 	1	19950307	G	3231	25UM78123A	DOOR STRUT 			HWKSLY	DH125 	HS125600A 	4230158	EU 										LT-RT MLG	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	121SG	6842 				256071				DURING THE 24-MONTH OUT OF PHASE INSPECTION, X-RAYS SHOW OVER 50 PERCENT OF THE ROD-END CONNECT POINT TO BE SEVERELY COR	RODED ON BOTH LT AND RT MLG DOOR STRUT ASSEMBLIES. RECOMMENDED AND REPLACED BOTH WITH NEW.					2	L	7	2 	4J				A3EU 					 
1995063000033	19950630	00033	CE 	1995	6	30	95ZZZX3158 	1	19950523	G	3244	301320870	TIRE 	GOODYEARAERO	9543991 	LEAR 	35 	35A 	5170602	CE 										RT MLG OTBD	BLOWN 	G				O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			SW	11	450MC	379 				368				ON TAKEOFF ROLL AT 10-15 KNOTS BELOW V 1 (136 KNOTS), THE RIGHT MAIN LANDING GEAR TIRE BLEW OUT. FULL BRAKING AND THRUS	T REVERSER DEPLOYMENT COULD NOT PREVENT THE AIRCRAFT FROM OVERUNNING THE DEPARTURE END OF THE RUNWAY AND A DRAINAGE DITC	H. CAUSE OF TIRE FAILURE IS STILL UNDER INVESTIGATION. LANDINGS, 175.				2	L	7	2 	4F				A10CE 					 
1995063000034	19950630	00034	NM 	1995	6	30	95ZZZX3159 	1	19950524	G	5754		BRACKET 			BOEING	727 	727230 	1384080	NM 										NR 4-5 LE FLAP	CORRODED 	B			VG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	357KP					20675				DURING C-CHECK INSPECTION, FOUND NR 4 AND NR 5 KREUGER FLAP BULL NOSE UPPER ROD ATTACH BRACKETS CORRODED BEYOND LIMITS.						2	L	7	3 	4F				A3WE 					 
1995063000035	19950630	00035	NM 	1995	6	30	95ZZZX3160 	1	19950524	G	5320		HAT CHANNEL 			BOEING	727 	727230 	1384080	NM 										FS 1183 LBL 30	CORRODED 	B			VG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	357KP					20675				DURING C-CHECK AND C.P.C.P. INSPECTION, FOUND AT BS 1183, LBL 30, WALL SUPPORT HAT CHANNEL CORRODED BYEOND LIMITS. (SUS	PECT CAUSE MOISTURE INTRUSION.)					2	L	7	3 	4F				A3WE 					 
1995063000036	19950630	00036	NM 	1995	6	30	95ZZZX3161 	1	19950524	G	5320		CHANNEL 			BOEING	727 	727230 	1384080	NM 										LT AFT LAV FLOOR	CORRODED 	B			VG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	357KP					20675				DURING C-CHECK AND C.P.C.P. INSPECTION, FOUND LEFT AFT LAV FLOOR CHANNEL BELOW DOOR CORRODED BEYOND LIMITS. (SUSPECT CA	USE MOISTURE INTRUSION.)					2	L	7	3 	4F				A3WE 					 
1995063000037	19950630	00037	NM 	1995	6	30	95ZZZX3162 	1	19950524	G	5320		ANGLE 			BOEING	727 	727230 	1384080	NM 										RT AFT LAV FLOOR	CORRODED 	B			VG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	357KP					20675				DURING C-CHECK AND C.P.C.P. INSPECTION, FOUND RIGHT AFT LAV FLOOR, FORWARD ANGLE CORRODED BEYOND LIMITS. (SUSPECT CAUSE	 MOISTURE INTRUSION.)					2	L	7	3 	4F				A3WE 					 
1995063000038	19950630	00038	NM 	1995	6	30	95ZZZX3163 	1	19950524	G	5320		STRAP 			BOEING	727 	727230 	1384080	NM 										LT AFT LAV FLOOR	CORRODED 	B			VG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	357KP					20675				DURING C-CHECK AND C.P.C.P. INSPECTION, FOUND LEFT AFT LAV, FLOOR STRAP CORRODED BELOW AFT WALL, BEYOND ALLOWABLE LIMITS	. (SUSPECT CAUSE MOISTURE INTRUSION.)					2	L	7	3 	4F				A3WE 					 
1995063000039	19950630	00039	NE 	1995	6	30	95ZZZX3164 	2	19950518	G	7200		ENGINE 			LEAR 	23 	23LEAR 	5170102	CE 	GE 	CJ610 	CJ6104 	30006	NE 					LT ENGINE	FLAME OUT 	C				B				EMER. DESCENT 				X			ENGINE FLAMEOUT 			CL	CLIMB 	1			SO	17	154AG	6814 	3490 			23034				LEFT ENGINE FLAMED OUT AT 40,900 FEET CLIMBING THROUGH BAD WEATHER. PILOT REQUEST DESCENT TO 10,000 FEET AND NEAREST AI	RPORT. AIRCRAFT ENGINE RE-LIGHT PROCEDURES FOLLOWED, ENGINE RE-STARTED AT 20,000 FEET, AND NORMAL LANDING AT NEAREST AI	RPORT. ENGINE INSPECTED FOR DAMAGE, NONE NOTED. GROUND RUNS PERFORMED ALL NORMAL. AIRCRAFT RETURNED TO SERVICE. ATTR	IBUTE CAUSE TO POOR WEATHER, HEAVY TURBULENCE AND RAINS.			1	L	7	2 	4J	4	J		A5CE 	1E16				 
1995063000040	19950630	00040	CE 	1995	6	30	95ZZZX3165 	1	19950607	G	5511	24311062	RIB FAIRING 			LEAR 	35 	35A 	5170602	CE 										VERT STAB FWD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	240JS					241				ON STABILIZER ACTUATOR REMOVAL FOR 600-HOUR INSPECTION, FORWARD RIB FAIRING FOUND CRACKED IN SEVERAL PLACES AND MISSING 	NUTPLATES. SUGGEST USING MORE CARE IN REMOVAL OF ACTUATOR TO AVOID DAMAGING RIB.					2	L	7	2 	4F				A10CE 					 
1995063000041	19950630	00041	SO 	1995	6	30	95ZZZX3166 	1	19950606	G	5720	1159WM2022B2	PLATE 			GULSTM	G1159 	G1159 	3953505	SO 										RT WING FLAPWELL	CORRODED 	B		A	BTVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	90HH	8687 				078				THE AIRCRAFT OPERATOR BROUGHT ACFT TO FACILITY TO INVESTIGATE A BULGE ON THE UNDERSIDE OF THE RT WING AT APPROXIMATELY R	BS 191 (THIS IS DIRECTLY UNDER THE FLIGHT SPOILER ACTUATOR ATTACH FITTING). AFTER DISASSEMBLY OF THE AREA IN QUESTION, 	THE 'LOAD PLATE' UNDER THE ACTUATOR ATTACH FITTING WAS ENTIRELY INVOLVED WITH INTERGRANULAR, EXFOLIATION CORROSION, CAUS	ING THE LOWER SKIN TO BULGE. REF: OPER CONTROL NR BTVR 950606.			2	L	7	2 	4F			RT	A12EA 					 
1995063000042	19950630	00042	SW 	1995	6	30	95ZZZX3167 	1	19950517	G	3310	2719115075	PANEL 			SWRNGN	SA227 	SA227AC 	8780603	SW 										OVERLAY	SHORTED 	G				O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			GL	05	26863					650B				WHILE IN CRUSE FLIGHT, SMOKE STARTED COMING FROM AREA OF RIGHT ESSENTIAL LIGHTED OVERLAY PANEL. OVERLAY PANEL APPEARED 	TO HAVE SHORTED INTERNALLY.					1	L	7	2 	4T				A8SW 					 
1995063000045	19950630	00045	NE 	1995	6	30	95ZZZX3170 	1	19950516	G	6730	7665009805109	SERVO 			SKRSKY	S76 	S76B 	8143007	NE 										M/R FWD	PITTED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	1WL	1296 			1083	760395				WHILE PERFORMING 750-HOUR ANNUAL REQUIREMENTS INSPECTION, THE MAINTENANCE CREW FOUND THE AFT AND FORWARD MAIN ROTOR SERV	O PISTONS ASSEMBLY (IN MID-STRIKE RANGE - ON GEARBOX SIDE) SURFACE PLATING STARTING TO DEGRADE. THERE WAS VISUAL SCORIN	G THAT WAS COPPER COLOR, AND PITTING WHICH COULD BE FELT BY PASSING YOUR THUMB NAIL ACROSS THE PISTON SURFACE IN THE AFF	ECTIVE AREA. THIS AREA CAN ONLY BE VIEWED WITH EXTERNAL HYDRAULICS POWER APPLIED TO THE AIRCRAFT WITH COLLECTIVE CONTRO	L IN FULL UP POSITION, AND VIEWING THE SERVO PISTONS FROM THE GEARBOX SIDE.		1	G	7	2 	4U				H1NE 					 
1995063000046	19950630	00046	NE 	1995	6	30	95ZZZX3171 	1	19950516	G	6730	7665009805109	SERVO 			SKRSKY	S76 	S76B 	8143007	NE 										M/R FWD	PITTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	1WL	1296 			1084	760395				WHILE PERFORMING 750-HOUR ANNUAL REQUIREMENTS INSPECTION, THE MAINTENANCE CREW FOUND THE AFT AND FORWARD MAIN ROTOR SERV	O PISTONS ASSEMBLY (IN MID-STRIKE RANGE - ON GEARBOX SIDE) SURFACE PLATING STARTING TO DEGRADE. THERE WAS VISUAL SCORIN	G THAT WAS COPPER COLOR, AND PITTING WHICH COULD BE FELT BY PASSING YOUR THUMB NAIL ACROSS THE PISTON SURFACE IN THE AFF	ECTIVE AREA. THIS AREA CAN ONLY BE VIEWED WITH EXTERNAL HYDRAULICS POWER APPLIED TO THE AIRCRAFT WITH COLLECTIVE CONTRO	L IN FULL UP POSITION, AND VIEWING THE SERVO PISTONS FROM THE GEARBOX SIDE.		1	G	7	2 	4U				H1NE 					 
1995063000316	19950630	00316	EA 	1995	6	30	95ZZZX3191 	2	19950510	G	7414	10357584	DISTRIBUTOR GEAR		S4LN20 	PIPER 	PA28 	PA28180 	7102808	SO 	LYC 	O360 	O360A3A 	41514	EA 					MAGNETO	LOOSE FINGER 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			EA	07	9521J				942448T	283739				ENGINE RAN ROUGH ON RIGHT MAG. DISASSEMBLED MAG AND FOUND TEETH ON DISTRIBUTOR GEAR MISSING AND LOOSE DISTRIBUTOR FINGE	R ELECTRODE. LOOSE ELECTRODE PROBABLY HIT STATIONARY ELECTRODE CAUSING TEETH TO BREAK.					1	L	7	1 	3O	3	O		2A13 	E286				 
1995063000317	19950630	00317	SO 	1995	6	30	95ZZZX3192 	2	19950526	G	7314	6467661	PUMP 			BEECH 	36 	A36 	1151604	CE 	CONT 	O550 	IO550* 		SO 					ENG FUEL	DEFECTIVE 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			WP	25	8180N	198 				E2606	281968R			ENGINE RAN ROUGH AT ALTITUDE, AUTOMIX NOT WORKING. WOULD NOT AUTOLEAN.						1	L	7	1 	3O	3	O		3A15 	E3SO				 
1995092900001	19950929	00001		1995	9	29	95ZZZX3193 	4	19950530	G	3424	1013800323	INDICATOR 			BEECH 	90 	C90A 	1152911	CE 										TURN & BANK	CASE BROKEN 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	23	477JA					LJ1162				UPON INSTALLATION IN THE ACFT - BACK OF THE UNIT CAME OFF IN THE TECHNICIAN'S HANDS. FURTHER INVESTIGATION FOUND THAT B	LACK ELECTRICAL TAPE WAS COVERING BROKEN OUT INSTRUMENT CASE MOUNTING HOLES FOR THE REAR PLATE. THE ONLY THING HOLDING 	THE INSTRUMENT TOGETHER WAS THE ELECTRICAL TAPE. THE TURN AND BANK CAME OFF THE SHELF FRESH BACK FROM OVERHAUL.				1	L	7	2 	3T			RT	3A20 					 
1995063000318	19950630	00318	CE 	1995	6	30	95ZZZX3194 	1	19950531	G	7603	AN311	BOLT 			BEECH 	33 	F33A 	1151425	CE 	CONT 	O520 	IO520BA 	17032	SO 					THROTTLE CONTROL	BROKEN 	D				A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			GL	03	24184					CE765	569214			PILOT REPORTED NO THROTTLE CONTROL WHILE AT CRUISE POWER. AFTER LANDING, FOUND THROTTLE CONTROL DISCONNECTED FROM FUEL 	CONTROL ARM. BOLT WAS FOUND IN ENGINE COMPARTMENT BROKEN OFF AT THE COTTER PIN HOLE.					1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995063000319	19950630	00319	SO 	1995	6	30	95ZZZX3195 	1	19950608	G	6123	A24913	ROD 			PIPER 	PA34 	PA34200T 	7103406	SO 										PROP LATCH	STRIPPED 	B		A	FG6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	33401					347570115				PROP WOULD NOT STAY IN LATCH. FEATHER ON SHUT DOWN AND WOULD NOT LATCH MANUALLY. INSPECTION REVEALED A3205 LATCH SCREW	 HAD STRIPPED OUT OF A2491-3 PITCH CHANGE ROD. THREADS IN ROD WERE GONE AND SCREW THREADS WERE DAMAGED. ROD HAD .004 I	NCH RUNOUT - SUSPECT POSSIBLE PREVIOUS ACCIDENT.				1	L	7	2 	3O				A7SO 					 
1995063000320	19950630	00320	SW 	1995	6	30	95ZZZX3196 	1	19950601	G	7713		GAUGE 			GULSTM	112 	112A 	7630302	SW 										MANIFOLD PRESS	MALFUNCTION 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	1441J					441				MANIFOLD PRESSURE GAUGE STICKS AND THEN FREEZES WHEN VISIBLE MOISTURE OR RAIN IS PRESENT. SB WITH RESTRICTOR FITTING PE	RFORMED PREVIOUSLY. OPS CHECK NORMAL IN DRY CONDITIONS. GAUGE SENT OUT FOR OVERHAUL. TT ON PART 2418.					1	L	7	1 	3O				A12SO 					 
1995063000321	19950630	00321	EA 	1995	6	30	95ZZZX3197 	2	19950528	G	8500		ENGINE 			PIPER 	PA28 	PA28151 	7102805	SO 	LYC 	O320 	O320D3G 	41508	EA 					CAM	FAILED 	D				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			NE	03	71BJ	2044 	35 			287615325	L1710639A			AIRCRAFT ENGINE QUIT IN-FLIGHT. NO SUDDEN STOPPAGE. SEVERAL ATTEMPTS TO RESTART N.G. ACFT LANDED ON RUNWAY (MMK) OKAY	. NO DAMAGE. INITIAL INVESTIGATION REVEALS CAMSHAFT DOES NOT ROTATE. ENGINE CRATED AND SENT TO LYCOMING FOR FURTHER I	NVESTIGATION. FAA TAG INSTALLED.				1	L	7	1 	3O	3	O		2A13 	E274				 
1995063000322	19950630	00322	EU 	1995	6	30	95ZZZX3198 	1	19950613	G	3211	AN527A	BOLT 			PARTEN	P68 	P68 		EU 										MLG JOIST	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	28FG	3920 				325180B				WHILE REMOVING LANDING GEAR FAIRING TO ACCESS JACK POINT, IT WAS DISCOVERED THE REAR BOLT SECURING THE MLG TO THE MLG JO	IST ASSY WAS BROKEN AT START OF THE THREADED AREA. THE REASON FOR FAILURE WAS UNKNOWN. INITIATING A TIME CHANGE MIGHT 	PREVENT THIS.				1	H	7	2 	3O				A31EU 					 
1995063000323	19950630	00323	CE 	1995	6	30	95ZZZX3199 	1	19950606	G	7722	3019383EI	HARNESS 			BEECH 	90 	E90 	1152914	CE 										LT ENG T5	TERMINAL BROKEN 	D				O				OTHER 				O			OTHER 			CR	CRUISE 	1			EA	23	75JP	2490 			2F925	LW158				DURING FLIGHT, PILOT NOTICED I.T.T. HAD DROPPED TO ZERO. MAINTENANCE WAS NOTIFIED AND A RESISTANCE CHECK WAS DONE. MAI	NTENANCE FOUND A TERMINAL ON THE T-5 HARNESS HAD BROKEN LOOSE IN THE CERAMIC HOUSING CAUSING T-5 TO DROP OFF. ENGINE C-	FLANGE WAS SPLIT AND HARNESS CHANGED. RESISTANCE CHECK FOUND NO FURTHER PROBLEMS AFTER CHANGE.				1	L	7	2 	3T				3A20 					 
1995063000325	19950630	00325	WP 	1995	6	30	95ZZZX3201 	1	19950606	G	5320	3532815514D	BATHTUB FITTING 			DOUG 	DC7 	DC7 	3021802	WP 										STR 26 RT OTBD	CORRODED 	C			GCVG	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	6353C	8451 				45486				EXFOLIATON FOUND, DUE TO CORROSION IN THE BOTTOM PORTION OF THE RECESSED AREAS OF THIS PART, POSSIBLY DUE TO THE ABILITY	 OF CONTAMINATES AND MOISTURE TO ACCUMULATE AND HOLD IN THIS AREA. POSSIBLE SOLUTION - A THOROUGH CLEAN-UP OF THE AREA 	AND APPLICATION OF LPS-3 CORROSION INHIBITER.				2	L	7	4 	4R				4A10 					 
1995063000327	19950630	00327		1995	6	30	95ZZZX3203 	1	19950519	G	7922	75944	VALVE 								LYC 	O360 	O360* 	41514	EA 					THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21										ON C/W LYC SB 518C BY CHECKING FOR LOOSE CRIMP NUTS, HAVE INSPECTED 6 AND FOUND 4 LOOSE NUTS.											3	O			E286				 
1995063000328	19950630	00328	WP 	1995	6	30	95ZZZX3204 	1	19950609	G	3233	106580270	ACTUATOR 			NAMER 	F51 	P51D 	6402304	WP 										LT MLG WELL	MALFUNCTION 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	151RJ					4474404				FOUND GEAR ACTUATOR CYLINDER CHROME HAD FLAKED OFF OF THE PISTON AND GOUGED UP A RIDGE OF METAL IN THE CYLINDER BARREL T	HAT WOULD NOT ALLOW THE GEAR TO EXTEND.					1	L	7	1 	4V				L113 					 
1995063000329	19950630	00329	CE 	1995	6	30	95ZZZX3205 	1	19950609	G	3230	504501032	TORQUE TUBE 			CESSNA	421 	421A 	2076012	CE 										RT MLG	BROKEN 	B			EIPR	O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			WP	07	2957Q					421A0057				PILOT REPORTED NO GREEN ON RT MLG. INSPECTED RT MLG AND FOUND TORQUE TUBE BROKEN AWAY AT PUSH/PULL ROD ATTACH POINT. P	USH/PULL TUBE SEVERED (PN 0840125-15). UPLOCK PUSH/PULL TUBE (PN 0841121-1) WAS BENT. REPLACED ALL PARTS WITH NEW. TO	TAL TIME UNKNOWN. HOBBS 682.3. REPLACED DOWN ACTUATOR CRANK, PN 5045001-202.				1	L	7	2 	3O				A7CE 					 
1995063000330	19950630	00330	CE 	1995	6	30	95ZZZX3206 	1	19950606	G	5551	07321014	REINFORCEMENT 			CESSNA	182 	R182 	2072734	CE 										LT H STAB ATTACH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	48G					R18202021				ACTT 3,957.8. OPERATOR DISCOVERD 1 INCH CRACK AT LEFT HORIZONTAL STABILIZER REAR SPAR ATTACH POINT REINFORCEMENT BRACKE	T, OUTBOARD HOLE IN BEND RADIUS (LOWER). DEFECT FOUND DURING PRE-FLIGHT. THIS IS THE SECOND OCCURRENCE AT 2202.1 TOTAL	 TIME. OPERATOR REPORTS THIS DEFECT HAS OCCURRED TO FLEET OF LIKE AIRCRAFT NUMEROUS TIMES. SUBMITTER SUGGESTS POSSIBLE	 CAUSE USING TAIL TO STEER AIRCRAFT. RECOMMEND A CLOSER LOOK AT HORIZONTAL STABILIZER REAR ATTACH POINT EACH INSPECTION	.		1	H	7	1 	3O			RT	3A13 					 
1995063000331	19950630	00331	SO 	1995	6	30	95ZZZX3207 	1	19950530	G	8120	LW131768S050	HOSE 			PIPER 	PA46 	PA46350P 		SO 										LT TURBO SCAV	FAILED 	B			OF1R	O				OTHER 				K			FLUID LOSS 			NR	NOT REPORTED 	1			EA	25	4MD	660 				4622116				OIL SCAVENGE LINE FROM LEFT TURBOCHARGER INTERNALLY COLLAPSED CAUSING LEFT TURBO TO PUMP OIL INTO INTAKE AND OUT TAILPIP	E, 3 QUARTS OF OIL LOST IN APPROXIMATELY 1.5 HOURS. REPLACED ALL OIL SCAVENGE HOSES WITH NEW, SINCE ALL HOSES DATED SAM	E, 12/21/90 AND ALL HAVE ONLY 660 HOURS. SUBMITTER RECOMMENDS THESE HOSES BE REPLACED WITH TEFLON INNER WALL HOSES OR R	IGID LINES, OR BE REPLACED AT EARLIER INTERVALS THAN 5 YEARS 2,000 HOURS AS RECOMMENDED.			1	L	7	1 	3O			RT	A25SO 					 
1995063000332	19950630	00332		1995	6	30	95ZZZX3208 	4	19950524	G	2562	SHARC7	ELT 	LEIGH 		CESSNA	150 	150M 	2071830	CE 										ELT CASE	RUPTURED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	66770					15076264				AT ANNUAL INSPECTION, FOUND ELT CASE HAD RUPTURED VIOLENTLY DESTROYING ELT, BATTERIES HAD NOT RUPTURED. THERE WAS NO COR	ROSION ON AIRFRAME. ELT HAD BEEN OVERHAULED IN 1992, BATTERIES WERE 2 YEARS OLD. THIS IS SECOND SHARC 7 ELT FOUND IN T	HIS CONDITION IN 2 YEARS.				1	H	7	1 	3O				3A19 					 
1995063000333	19950630	00333		1995	6	30	95ZZZX3209 	4	19950515	G	6113		SUPPORT PLATE 			UNIVAR	108 	1083 	9230408	NM 										SPINNER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	529C	1982 				1083529				CIRCUMFERENTIAL CRACKS AROUND ATTACH BOLT HOLES ON ALL BUT ONE HOLE - PLATE ABOUT TO LEAVE, APPEARED SPINNER HAD NOT BEE	N REMOVED IN SOME TIME. SUSPECT CAUSED BY OVERTORQUING OF ATTACH BOLTS.					1	H	7	1 	3O				A767 					 
1995063000334	19950630	00334	EA 	1995	6	30	95ZZZX3210 	2	19950531	G	8520	75038	CRANKSHAFT 			PIPER 	PA32 	PA32260 	7103206	SO 	LYC 	O540 	O540E4B5 	41532	EA 					NR 2 CYL	CRACKED 	G				A				UNSCHED LANDING 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			EA	21	16354	3740 	1773 		63229	327300025	L1524940			AIRCRAFT MADE AN OFF-FIELD LANDING 200 YARDS SHORT OF THE AIRPORT. A COMPLETE LOSS OF OIL OCCURRED EXITING A HOLE IN TH	E CRANKCASE ADJACENT TO THE NR 2 CYLINDER. THE NR 1 AND NR 2 CYLINDER CAM FOLLOWER LIFTER BODY HEADS WERE SEPARATED ON 	THE INTAKE AND EXHAUST SIDES. SEVERE METAL CONTAMINATION RESULTED. ENGINE WAS ON OIL ANALYSIS. ALL PREVIOUS SAMPLES N	ORMAL.			1	L	7	1 	3O	3	O		A3SO 	E295				 
1995063000335	19950630	00335	SO 	1995	6	30	95ZZZX3211 	1	19950501	G	5320		TUBE 			PIPER 	PA18 	PA18150 	7101828	SO 										FS 127.5 RT	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	5378Y					188141				DURING ANNUAL INSPECTION, DISCOVERED FUSELAGE TUBE AT FS 127.5 ON RT SIDE BROKEN AT APPROXIMATELY CENTER OF TUBE. DAMAG	ED AREA WAS REMOVED AND AN INNER SLEEVE SPLICE REPAIR WAS MADE. ALTHOUGH AN OBVIOUS REASON FOR DAMAGE WAS NOT EVIDENT, 	IT IS SUSPECTED HARD LANDINGS AND/OR UNUSUAL FLIGHT ATTITUDES ARE THE CAUSE. AIRCRAFT IS OPERATED ON FLOATS.				1	H	7	1 	3O				1A2 					 
1995063000336	19950630	00336	CE 	1995	6	30	95ZZZX3212 	1	19950515	G	8100	STCSA5223NM	TURBONORMALIZING			BEECH 	33 	F33A 	1151425	CE 										ENGINE	FAULTY 	H	L	A		K				NONE 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			GL	05	16PA					CE1465				DECREASED AIRCRAFT PERFORMANCE NOTED FOLLOWING INSTALLATION OF TURBO-NORMALIZING STC NR SA 5223NM. INVESTIGATION FOUND 	TURBO FLITE SYSTEM WEIGHT DATA TO BE INCORRECT. USING CORRECTED DATA STILL DOES NOT APPEAR CORRECT PER ACTUAL WEIGHT DA	TA FROM AIRCRAFT.				1	L	7	1 	3O				3A15 					 
1995063000337	19950630	00337	SO 	1995	6	30	95ZZZX3213 	2	19950615	G	8530	530658	BUSHING 		632043 	CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520L 	17032	SO 					PISTON PIN	SPLIT 	B			NT2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	525RG	903 				421C0616	241062R			FOUND NR 1 PISTON PIN ROD BUSHINGS CRACKED CIRCUMFERENCE WISE .3750 INCH AND SPLIT ABOUT .0312 INCH. FOUR OUT OF 6 BUSH	INGS CRACKED. NR 2 CYLINDERS WERE REMOVED FOR LOW COMPRESSION AT ANNUAL.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995063000338	19950630	00338		1995	6	30	95ZZZX3214 	4	19950615	G	2300	047048740001	MOUNT RACK 	KING 																EQUIP MOUNT	WELD BROKEN 	B			C3FR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	05										RECEIVED NEW MATERIALS FROM BENDIX/KING. UPON INCOMING INSPECTION, FOUND THE EQUIPMENT MOUNTING RACKS HAD SEVERAL BROKE	N WELDS. THROUGH FURTHER TESTING AND INSPECTION FOUND MANY OF THE WELDS FAILED AND THE RACK HAD SEVERE CORROSION.																		 
1995063000339	19950630	00339	SO 	1995	6	30	95ZZZX3215 	1	19950525	G	5102	41601	HANGER SPRING 		F1 	BALWKS	FIREFY	FIREFLY7 	1050100	SO 										BURNER	DEFECTIVE 	B			RG1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01	90696				191	F7759				THE BALLOON WORKS HAS ISSUED SB NR B30, DATED MARCH, 1995. WHEN BALLOON CAME IN FOR ANNUAL, THE PARTS RECEIVED FROM THE	 BALLOON WORKS TO PERFORM SB NR B30 WERE NOT AIRWORTHY. THE SAID PARTS CONSIST OF 2 SPRINGS AND A CLIP WITH A ROLL PIN.	 THREE PARTS ARE NEEDED FOR EACH SB. OF THE 3 PARTS RECEIVED, ONE WAS OKAY, ANOTHER HAD THE ROLL PIN HOLE DRILLED AT S	UCH AN ANGLE THAT THE ROLL PIN MISSED THE SECOND HOLE AND THE THIRD HAD NO ROLL PIN AT ALL.			1	B	0	0 					A14SO 					 
1995063000340	19950630	00340	EA 	1995	6	30	95ZZZX3216 	2	19950501	G	8530		RING 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	LTIO540J2BD 	41533	EA 					CYLINDER	BROKEN 	D				E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			CR	CRUISE 	1			NM	07	27354		153 			317752180	L222568A			ENGINE SHUT DOWN IN-FLIGHT DUE TO LOSS OF OIL PRESSURE. INVESTIGATION REVEALED BROKEN COMPRESSION RINGS ON 1 CYLINDER A	ND SEVERELY WORN RINGS ON ANOTHER. THESE WERE NUCHROME CYLINDERS WITH 153.2 HOURS SINCE NEW. ENGINE OVERHAUL AGENCY IN	DICATED THEY HAVE SEEN THIS PROBLEM BEFORE AND ATTRIBUTE ITS CAUSE TO AN EXCESSIVELY LEAN MIXTURE CREATING HIGH HEAD TEM	PERATURES. ENGINE HAS BEEN REPAIRED.			1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995063000341	19950630	00341	CE 	1995	6	30	95ZZZX3217 	1	19950607	G	7603		ROD END 			CESSNA	182 	182 	2072702	CE 										THROTTLE	FAILED 	B			EIPR	O				OTHER 				O			OTHER 			DE	DESCENT 	1			WP	07	4904N					18267448				DURING DESCENT, PILOT ATTEMPTED TO REDUCE POWER. ENGINE DID NOT RESPOND. REMOVED COWLING AND INSPECTED. FOUND THROTTL	E DISCONNECTED FROM CARBURETOR LINKAGE. NO HARDWARE FOUND. INSTALLED NEW THROTTLE CABLE ROD-END AND HARDWARE. OPS CHE	CK OKAY. TACH 302.4.				1	H	7	1 	3O			NT	3A13 					 
1995063000342	19950630	00342	EA 	1995	6	30	95ZZZX3218 	2	19950511	G	8550	LW13383	BAFFLE 			PIPER 	PA46 	PA46350P 		SO 	LYC 	O540 	TIO540AE2A 	41532	EA 					OIL SUMP	DAMAGED 	B			LCPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	727K	124 				4622178	L957461A			AT ENGINE OIL CHANGE, A RIVET HEAD WAS FOUND IN THE OIL SUCTION SCREEN. LYCOMING SB NR 489A PERTAINS TO THIS SUBJECT. R	ECEIVED APPROVAL FROM LYCOMING TO MODIFY A NEW OIL SUMP BAFFLE, THEN REMOVED AND REPLACED DAMAGED BAFFLE. THE ENGINE WA	S RETURNED TO SERVICE.				1	L	7	1 	3O	3	O	RT	A25SO 	E14EA				 
1995063000343	19950630	00343	EA 	1995	6	30	95ZZZX3219 	2	19950519	G	8530	M139973	VALVE KEY 			PIPER 	PA25 	PA25260 	7102508	SO 	LYC 	O540 	O540G1A5 	41532	EA 					EXHAUST VALVE	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	9561P	750 				257556224				FOUND EXHAUST VALVE KEY HAD BROKEN AND WORN ABOUT ONE-THIRD OF THE DIAMETER OF THE VALVE STEM.						1	L	7	1 	3O	3	O		2A10 	E295				 
1995063000344	19950630	00344	CE 	1995	6	30	95ZZZX3220 	1	19950516	G	7603	5052456843	LEVER ASSY 			BEECH 	90 	E90 	1152914	CE 										IDLE CONTROL	BENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	608A	3935 				LW79				FOUND LEVER ASSY WORN THIN TO POINT OF BENDING. WORN THIN BY RUBBING ON PEDESTAL AND BENDING.						1	L	7	2 	3T				3A20 					 
1995063000345	19950630	00345		1995	6	30	95ZZZX3221 	4	19950518	G	6113	05503211	BULKHEAD 			CESSNA	172 	172M 	2072418	CE 										PROP SPINNER AFT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	5418R					17263539				AT ANNUAL INSPECTION, BOTH FORWARD AND REAR PROP SPINNER BULKHEADS FOUND TO HAVE MULTIPLE CRACKS AROUND BOLT HOLES AND R	IVETS. REAR BULKHEAD WAS SLIGHTLY DEFORMED. SOMEONE HAD STOP-DRILLED CRACKS AT SAME TIME IN THE PAST. SUBMITTER SUGGE	STED CRACKS OF THIS NATURE RENDER PART UNAIRWORTHY.				1	H	7	1 	3O			NT	3A12 					 
1995063000346	19950630	00346		1995	6	30	95ZZZX3222 	4	19950518	G	6113	05503214	BULKHEAD 			CESSNA	172 	172M 	2072418	CE 										PROP SPINNER FWD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	5418R					17263539				AT ANNUAL INSPECTION, BOTH FORWARD AND REAR PROP SPINNER BULKHEADS FOUND TO HAVE MULTIPLE CRACKS AROUND BOLT HOLES AND R	IVETS. REAR BULKHEAD WAS SLIGHTLY DEFORMED. SOMEONE HAD STOP-DRILLED CRACKS AT SAME TIME IN THE PAST. SUBMITTER SUGGE	STED CRACKS OF THIS NATURE RENDER PART UNAIRWORTHY.				1	H	7	1 	3O			NT	3A12 					 
1995063000347	19950630	00347	SO 	1995	6	30	95ZZZX3223 	1	19950511	G	3213	7521504	STRUT 			PIPER 	PA42 	PA421000 	7104225	SO 										LT MLG	SPLIT 	G				C				ABORTED TAKEOFF 				O			OTHER 			TO	TAKEOFF 	1			WP	27	42MD	2282 				425527015				AIRCRAFT HAS EXTRA TANKS INSTALLED AND WAS FULLY FUELED FOR FLIGHT TO NEW ZEALAND. AIRCRAFT AUTHORIZED 125 PERCENT CTOW	 BY DIRECTORATE, BUT WAS LOADED TO 118 PERCENT CTOW. AIRCRAFT BEGAN TAKEOFF ROLL AND WAS TRAVELLING APPROXIMTELY 40 KNO	TS WHEN TAKEOFF WAS ABORTED. UPON APPLICATION OF BRAKES, LEFT MAIN GEAR UPPER STRUT HOUSING SPLIT OPEN ALLOWING THE STR	UT TO EXIT AFT. SB 929A WAS PERFORMED JUST HOURS EARLIER WITH NO CRACKS DETECTED. RECOMMEND THIS MODEL BE REQUIRED TO 	RETROFIT TO STRONGER OPTIONAL MAIN GEAR PN 75215-06.		1	L	7	2 	4T			RT	A23SO 					 
1995063000348	19950630	00348		1995	6	30	95ZZZX3224 	4	19950501	G	3457	2000APR	GPS RECEIVER 			CESSNA	340 	340A 	2076405	CE 										COCKPIT	DEFECTIVE 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	05	69540				4262628	340A0694				OPERATOR INTERVENTION ALLOWS THE TURN-OFF PRIVILEGE OF EXTERNAL ANNUNCIATOR LIGHTS. SUBMITTER BELIEVES THIS IS A SAFETY	 ISSUE.					1	L	7	2 	3O				3A25 					 
1995063000349	19950630	00349	CE 	1995	6	30	95ZZZX3225 	1	19950519	G	5511	12326194	RIB 			CESSNA	210 	T210N 	2073456	CE 										STAB NOSE	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	4895Y	1200 				21064033				FOUND 2 NOSE RIBS ON EACH STABILIZER WERE BENT OR BROKEN, ALSO, THE SKIN WAS CRACKED AROUND A RIVET IN ONE PLACE. SUSPE	CT THIS WAS CAUSED BY PUSHING DOWN ON TAIL TO MOVE AIRCRAFT.					1	H	7	1 	3O				3A21 					 
1995063000350	19950630	00350	SW 	1995	6	30	95ZZZX3226 	1	19950607	G	2910	6790244287	TUBE ASSY 			GULSTM	680TP 	681 	0141718	SW 										FS 33 Z 55.50	HOLE CHAFED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	07	3203P	5430 				6019				AILERON DRUMS SUPPORT CHANNEL, PN 5530168-3. AT APROX STA 33.0, IS SECURED TO THE STRUCTURE WITH 4 EACH MS27039-1-09 SC	REWS. THE HYD PRESSURE LINE WAS ROUTED UNDER ONE OF THESE SCREWS AND PROPER CLEARANCE WAS NOT PROVIDED. OVER SEVERAL Y	EARS IT APPEARS CHAFING EVENTUALLY WORKED ITS WAY THROUGH THE TUBING SIDE WALL CAUSING A MASSIVE HYDRAULIC LEAK. SUBMIT	TER RECOMMENDS AN INSPECTION OF HYDRAULIC LINES ROUTED UNDER THIS CHANNEL AT THE NEXT 100-HOUR/ANNUAL INSPECTION AND EXE	CUTE PROPER CLAMPING OF THESE LINES. AS IT APPEARED, SUBMITTED SUGGESTED THIS WAS A MANUFACTURE DEFECT.		1	H	7	2 	3T				2A4 					 
1995063000351	19950630	00351	CE 	1995	6	30	95ZZZX3227 	1	19950601	G	7810	085071031	EXHAUST RISER 			CESSNA	310 	T310Q 	2074244	CE 										LT ENG NR 2 CYL	HOLE BURNED 	D				O				OTHER 				O			OTHER 			CL	CLIMB 	1			SW	99	7584Q		855 			310Q0084				DURING DEPARTURE CLIMB, THE EXHAUST RISER ON THE LEFT ENGINE NR 2 CYLINDER DEVELOPED A HOLE ON THE LOWER SIDE. PRIOR TO	 THE FAILURE OF THE PART IT APPEARED TO BE IN GOOD CONDITION. DURING THE PRECEDING FEW HOURS OF FLIGHT THE AIRCRAFT WAS	 USED FOR FLIGHT TRAINING INCLUDING SINGLE ENGINE PROCEDURES AT WHICH TIME IT IS POSSIBLE THAT SHOCK COOLING MAY HAVE BE	EN INDUCED THAT COULD HAVE STARTED THE CRACK WHICH LED TO THE FAILURE OF THE PART.			1	L	7	2 	3O				3A10 					 
1995063000352	19950630	00352	CE 	1995	6	30	95ZZZX3228 	1	19950602	G	3260	S13771	UPLOCK SWITCH 			CESSNA	210 	T210M 	2073451	CE 										LT MLG	DEFECTIVE 	D				A				UNSCHED LANDING 				P			NO WARNING INDICATION 			CL	CLIMB 	1			WP	21	7072					21061962				AFTER TAKEOFF AND GEAR UP SELECTED, NO 'UP' LIGHT AND THE POWER PACK CONTINUED TO RUN. CREW SELECTED GEAR DOWN WITH NO 	PROBLEMS. MAINTENANCE PERSONNEL INSPECTED AND FOUND THE LT MLG UPLOCK SWITCH MOUNTING JAM NUT HAD BACKED OFF LOOSENING 	THE SWITCH CAUSING THE SWITCH TO MOVE AND NOT MAKE CONTACT WITH THE GEAR. THIS CAUSES THE 'UP' LIGHT NOT TO ILLUMINATE 	AND THE POWER PACK TO CONTINUE TO RUN AS THERE IS NO SENSE THE GEAR WAS UP AND LOCKED. (IN FACT, IT WAS.) SUBMITTER RE	COMMENDS CESSNA INSTALL JAM NUTS THAT CAN ACCEPT SAFETY WIRE TO LOCK JAM NUTS AFTER ADJUSTMENTS AND ALIGNMENTS.		1	H	7	1 	3O				3A21 					 
1995063000353	19950630	00353	CE 	1995	6	30	95ZZZX3229 	1	19950523	G	2913	9881141	MOTOR 		98811241 	CESSNA	182 	R182 	2072734	CE 										POWERPACK	SEIZED 	D				O				OTHER 				O			OTHER 			AP	APPROACH 	1			NE	03	6465T	1205 			5892	R18202033				DURING FLIGHT, LANDING GEAR WOULD NOT DOWN AND LOCK UNDER ITS OWN POWER. DOWN AND LOCK WAS ACCOMPLISHED BY EMERGENCY HA	ND PUMP EXTENSION. DISASSEMBLY AND INSPECTION OF POWERPACK ASSY FOUND MOTOR SEIZED. DISASSEMBLY AND INSPECTION OF MOTO	R FOUND CARBON BRUSH ELEMENTS DETERIORATED AND BROKEN. THE LARGER BROKEN OFF BRUSH PIECES WERE FOUND JAMMING THE ARMATU	RE WHICH WAS THE CAUSE OF THE MOTOR SEIZURE. RE-ASSEMBLED POWERPACK WITH NEW MOTOR. RETRACTION TEST ACCEPTABLE.			1	H	7	1 	3O			RT	3A13 					 
1995063000356	19950630	00356	EU 	1995	6	30	95ZZZX3232 	1	19950608	G	6120	8954851	GASKET 			BAG 	JETSTM	JETSTM3201 	1500217	EU 										PROP PITCH CONT	MISMANUFACTURED 	B	S	A	W6NR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25										GASKET RECEIVED NEW FROM VENDOR INCORRECTLY MANUFACTURED. INSTALLATION WOULD CAUSE MAJOR OIL LEAK FROM PROP PITCH CONTR	OL. RECENTLY FOUND PROP PITCH CONTROL MOUNTING GASKETS INCORRECTLY MANUFACTURED.					2	L	7	2 	4T			RT	A56EU 					 
1995063000357	19950630	00357	WP 	1995	6	30	95ZZZX3233 	1	19950608	G	2435	150SG117Q	GENERATOR 			HUGHES	369 	369E 	4470707	WP 										START/GEN	SHAFT SHEARED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	34CT		748 		3283	0392E				DURING NORMAL OPERATION, STARTER/GENERATOR FAILED DUE TO SHEARING OF SHAFT.						1	G	7	1 	3U				H3WE 					 
1995063000358	19950630	00358	NE 	1995	6	30	95ZZZX3234 	2	19950605	G	7532	2856201	BLEED VALVE 			SNIAS 	350 	AS350BA 	8680817	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					ENGINE	INOP 	D		A		A				UNSCHED LANDING 				K			FLUID LOSS 			CR	CRUISE 	1			WP	13	269JM					1398	401			AIRCRAFT DEPARTED. ON ITS FIRST FLIGHT ABOUT 8:45, PILOT HEARD A BIG BANG COMING FROM THE ENGINE FOLLOWED BY POPPING SO	UND AND LOSS OF POWER. THE PILOT WENT INTO EMERGENCY PROCEDURE. AS DECREASE OF POWER, ENGINE CAME BACK ON-LINE. THE P	ILOT MANAGED TO SET THE ACFT DOWN ON A PRIVATE PROPERTY. MECHANICS WERE SENT OUT AND FOUND BLEED VALVE INOP. REPLACED 	THE VALVE AND C/W RUN-UP AND OPS CHECK AND FOUND ACFT AND ENGINE SERVICEABLE.			1	G	7	1 	3U	3	U	NC	H9EU 	E19EU				 
1995063000360	19950630	00360	EU 	1995	6	30	95ZZZX3236 	1	19950616	G	7810	02922807580	EXHAUST 			SNIAS 	350 	AS350B1 	8680811	EU 										ENG RT AFT END	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05	350CM	67 				2265				EXHAUST, RIGHT SIDE, CRACKED 5 INCHES UP, 2 INCHES PLUS LONG AT OUTLET END. REMOVED AND REPLACED EXHAUST STACK. THIS I	S THE 2ND TIME THIS EXHAUST STACK CRACKED. FIRST TIME IT WAS SENT OUT FOR REPAIR.					1	G	7	1 	3U				H9EU 					 
1995063000361	19950630	00361	SW 	1995	6	30	95ZZZX3237 	1	19950607	G	6330	222031605109	FLEXTURE 			BELL 	222 	222 	1182122	SW 										TRANSMISSION	DEBONDED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	510W	838 			BW240	47133				INSPECTION FOUND FLEXTURE DEBONDED. REPLACED WITH NEW FLEXTURE.						1	G	7	2 	3U				H9SW 					 
1995063000376	19950630	00376	SO 	1995	6	30	95ZZZX3238 	1	19950524	G	7120		TUBING CLUSTER 			PIPER 	PA36 	PA36285 	7103610	SO 										ENG MOUNT TOP	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	13	9960P	4550 				367560071				TUBING WAS CRACKED AFT OF FIREWALL. AT ENGINE MOUNT ATTACH POINTS, GUSSETS WERE INSTALLED PER AD 79-12-09 BEFORE CRACKS	 WERE FOUND. REMOVED HOPPER FOR WELDING AND FOUND CRACK 2 INCHES LONG ON TOP OF TUBING CLUSTER LT SIDE.					1	L	7	1 	3O				A10SO 					 
1995063000377	19950630	00377	EA 	1995	6	30	95ZZZX3239 	2	19950518	G	8530	73806	PUSHROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					CYLINDER	TIP FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	11	5241Q					15285088	L2241915			PUSHROD TIP SEPARATION. SECOND FAILURE ON THIS ENGINE. TOTAL TIME 6696. ENGINE TSMOH 366. REMOVED PN 73806. REPLACE	D WITH NEW PUSHROD PN 73806, REV A.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995063000378	19950630	00378	CE 	1995	6	30	95ZZZX3240 	1	19950614	G	7160	AM107635FP	AIR FILTER 			CESSNA	177 	177B 	2073708	CE 										MOUNT TAB	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	20375	480 				177002664				AIR FILTER WAS REMOVED DURING AN ANNUAL INSPECTION, ONE MOUNT TAB (WHICH WAS SPOT WELDED TO THE FRAME) WAS BROKEN OFF. A	LSO, THE NEOPRENE GASKET WAS LOOSE AND SUCKING INTO THE INDUCTION SYSTEM.					1	H	7	1 	3O				A13CE 					 
1995063000379	19950630	00379	CE 	1995	6	30	95ZZZX3241 	1	19950607	G	5511	12326232	BRACKET 			CESSNA	210 	210N 	2073453	CE 										HORIZ STAB ATTAH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	6625N					21063126				BRACKET CRACKED AT SCREW HOLE FOR AFT SPAR ATTACHMENT ON HORIZONTAL STABILIZER. CESSNA SL SE 84-17 ADDRESSES THIS PROBL	EM. SUBMITTER SUGGESTS MANDATORY REPLACMENT OF IMPROVED CESSNA PART.					1	H	7	1 	3O				3A21 					 
1995063000380	19950630	00380	CE 	1995	6	30	95ZZZX3242 	1	19950424	G	5753	24250011	TRACK 			CESSNA	150 	152 	2071835	CE 										WING FLAP	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	69112	5883 				15282489				AIRCRAFT IS PRIMARILY A LINE TRAINER AND IS STORED OUTSIDE FOR MOST OF ITS SERVICE. CORROSION DEVELOPED BETWEEN FLAP RO	LLER BUSHINGS AND TRACK SLOTS. SUBMITTER SUGGESTS KEEPING SLOTS CLEAN AND INSPECT REGULARLY.					1	H	7	1 	3O			NT	3A19 					 
1995063000381	19950630	00381	CE 	1995	6	30	95ZZZX3243 	1	19950605	G	7602	MS21042524	LOCK NUT 		6494682A1 	BEECH 	45 	T34B 	1152014	CE 										MIXTURE SHFT ARM	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	134MM	365 			K018504A	86299				AFTER SHUT DOWN, THE ENGINE COULD NOT BE STARTED. NO FUEL PRESSURE COULD BE PRODUCED. SUBSEQUENT INVESTIGATION REVEALE	D THE LOCK NUT RETAINING THE MIXTURE ARM ON THE METERING UNIT SHAFT HAD LOOSENED. THE SHAFT COULD NOT BE ROTATED WITH T	HE ARM UNTIL THE NUT WAS RE-TORQUED TO 100-120 INCHES/POUNDS.				1	L	7	1 	3O				5A3 					 
1995063000382	19950630	00382	SO 	1995	6	30	95ZZZX3244 	2	19950613	G	8550		IDLE SHAFT 			PIPER 	PA28 	PA28201T 	7102819	SO 	CONT 	O360 	TSIO360FB 	17025	SO 					OIL PUMP	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	27	8168Z	1400 				28R8031074	237400R			OIL PUMP WOULD LOSE PRIME AND HAVE NO OIL PRESSURE AFTER START-UP. OIL PUMP IDLE SHAFT EXTREMELY WORN AND BOTH GEARS WO	RN. WORE THE PUMP HOUSING CAUSING AN OIL SHORTAGE TO THE ENGINE WITH BEARING AND CASE DAMAGE. THE PUMP HOUSING AND SHA	FTS WERE TIGHT AND CORRECT PER CONTINENTAL.				1	L	7	1 	3O	3	O		2A13 	E9CE				 
1995063000383	19950630	00383	EA 	1995	6	30	95ZZZX3245 	2	19950609	G	8530	77998	HOUSING 			PIPER 	PA31 	PA31310 	7103103	SO 	LYC 	O540 	TIO540A2C 	41532	EA 					ENG INDUCT SYS	BOLT DETACHED 	B			BCBR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			EA	03	44RL		124 			317401217				HOUSING FOR YEARS HAS BEEN INSTALLED WITH 4 EACH STD 1875 BOLTS AND THE TWO INTERNAL BOLTS WERE STD 1890 DRILLED HEADS F	OR SAFETY WIRE, STD 1890 NOW IS CHANGED TO STD 1875 UNDRILLED AND INSTALLED WITH A PLAIN WASHER, AN960, AND MS535333 ST	ARLOCK WASHER. ONE OF THE INSIDE BOLTS BACKED OUT AND WENT INTO NR 2 CYLINDER AND DESTROYED THE PISTON, CYLINDER HEAD, 	AND VALVES.			1	L	7	1 	3O	3	O	RT	A20SO 	E14EA				 
1995063000384	19950630	00384	SO 	1995	6	30	95ZZZX3246 	2	19950612	G	8530	643766	GUIDE 								CONT 	O520 	IO520* 	17032	SO 					INTAKE	OUT OF LIMITS 	B			YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11										INSPECTION OF NEW PARTS FOUND 6 EACH INTAKE VALVE GUIDES DEFECTIVE OUT OF 6 EACH NEW TCM CYLINDERS. ALL GUIDES ARE OUT 	OF NEW LIMITS AND TAPERED FROM TOP TO BOTTOM. TOTAL OF 18 INTAKE GUIDES, PN 643766, REPORTED OUT OF LIMITS BY SUBMITTER	.									3	O			E5CE				 
1995063000385	19950630	00385	SO 	1995	6	30	95ZZZX3247 	2	19950612	G	8530	643767	GUIDE 								CONT 	O520 	IO520* 	17032	SO 					EXHAUST	OUT OF LIMITS 	B			YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11										SIX EACH EXHAUST VALVE GUIDES DEFECTIVE OUT OF 6 EACH NEW TCM CYLINDERS. ALL GUIDES ARE OUT OF NEW LIMITS AND TAPERED F	ROM TOP TO BOTTOM. TOTAL OF 18 EXHAUST GUIDES, PN 643767, REPORTED OUT OF LIMITS BY SUBMITTER.										3	O			E5CE				 
1995063000386	19950630	00386	NE 	1995	6	30	95ZZZX3248 	2	19950503	G	7323	3535196	DRIVE PIN 	WOODWARD 	8061526 						GE 	CFM56 	CFM565A 	13802	NE 					HMU	MISMANUFACTURED 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	99					79445					INVESTIGATI0N OF 2 FIELD REJECTS (DUE TO OVERSPEED GOV FAULT INDICATIONS). MFG FND CARBIDE WEAR PAD OF GOV DRIVE PIN AS	SY IMPROPERLY POSITIONED WHEN BRAZED IN PLACE. INVESTIGATION FOCUSED UPON 1 MFG LOT. THESE CONDITIONS RESULT IN WEAR W	HICH CAUSES A SHIFT IN OVERSPEED GOV SET POINT (IN REDUCED SPEED DIRECTION). THIS IS NOT BELIEVED TO BE A SAFETY CONCER	N BECAUSE OF FAULT INDICATING LOGIC WHICH WILL PRECEDE ANY OPERATING PROBLEMS. WOODWARD & GEAE ARE COORDINATING ADVISAB	ILITY OF SB TO INFORM FIELD OF CONDITION & RECOMMEND CHECK/REPLACE INTERVAL IN ORDER TO PREVENT POSSIBLE UNSCHEDULED REM	OVAL. AFFECTED S/NS: WYG 79269-79270, WYG 79272-79290, WYG 79374-79382, WYG 79436-79443, WYG 79445, WYG 84161-84162.						4	F			E29NE				 
1995063000387	19950630	00387	GL 	1995	6	30	95ZZZX3249 	1	19950616	G	2430	1241051113	SOLENOID 			AMTR 	LANCAR	LANCAIR 	05616TS	GL 										BATTERY	FAILED 	D				O				OTHER 				H	P		ELECT. POWER LOSS-50 PC 	NO WARNING INDICATION 		NR	NOT REPORTED 	1			CE	05	444WH					100				PANEL ELECTRICAL FAILURE. EMERGENCY EXTENSION OF GEAR DID NOT LOCK AND THERE WERE NO GEAR LIGHTS AVAILABLE. GEAR LOCKS	 OKAY ON GROUND.					1	L	7	1 	3O			RT	EXPA1L71					 
1995063000388	19950630	00388	CE 	1995	6	30	95ZZZX3250 	1	19950518	G	5521	9562001071	CHANNEL 			BEECH 	58 	58 	1152740	CE 										LT ELEV RIB INBD	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	6654Y	3143 				TH1061				FOUND BOTTOM FORWARD CHANNEL CRACKED ON LEFT ELEVATOR INBOARD FORWARD RIB. SUBMITTER RECOMMENDS REINFORCING CHANNEL PLA	TES ON ELEVATOR RIBS.					1	L	7	2 	3O				3A16 					 
1995063000389	19950630	00389	EU 	1995	6	30	95ZZZX3251 	1	19950523	G	5102	PA1425AM	VALVE 			CAMRON	MODELO	N105 	1880225	EU 										EXTERNAL FUEL	STUCK OPEN 	G	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	2987N					5195				DURING BALLOON INFLATION USING AN EXTERNAL FUEL TANK AND SHERWOOD VALVE CONNECTION, THE CHECK VALVE STUCK OPEN ALLOWING 	PROPANE TO ESCAPE AND IGNITE RESULTING IN BURNS TO THE PILOT'S FACE AND ARMS. ALSO, DAMAGE TO THE BALLOON ENVELOPE OCCU	RRED.				1	B	0	0 					B1EU 					 
1995063000390	19950630	00390		1995	6	30	95ZZZX3252 	2	19950609	G	7414	M3975	COIL 	SLICK 	6210 															RT MAG	SHORTED 	B			WWKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03		458 			89030266					COIL SHORTED CAUSING MAG TO NOT WORK. COIL WAS NOT CRACKED. HAD A SMALL PIN HOLE BURNED OUT.																			 
1995063000391	19950630	00391	CE 	1995	6	30	95ZZZX3253 	1	19950616	G	5312	21121362	BULKHEAD 			CESSNA	210 	P210R 	2073455	CE 										FS 209 BRACKET	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	540CE					P21000853				FOUND BULKHEAD CRACKED AT THE LEFT AND RIGHT HORIZONTAL STABILIZER ATTACHMENT BRACKETS.						1	H	7	1 	3O			RT	3A21 					 
1995063000392	19950630	00392	NM 	1995	6	30	95ZZZX3254 	1	19950602	G	5210		DOOR 			PIPER 	PA60 	PA60600 	7106001	NM 										UPPER CABIN	MALFUNCTIONED 	B			BSYR	A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			GL	07	90609					600320118				UPPER CABIN DOOR CAME OPEN IN-FLIGHT, AIRCRAFT LANDED. REMOVED AND REPLACED UPPER CABIN DOOR ASSY.						1	M	7	2 	3O			RT	A17WE 					 
1995063000393	19950630	00393	CE 	1995	6	30	95ZZZX3255 	1	19950602	G	7603	5038901229	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										THROTTLE	BROKEN 	B			BSYR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	07	4098S					TH600				RIGHT THROTTLE CABLE BROKEN. REMOVED AND REPLACED THROTTLE CABLE.						1	L	7	2 	3O			 	3A16 					 
1995063000394	19950630	00394	CE 	1995	6	30	95ZZZX3256 	1	19950512	G	7602	5038901229	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										MIXTURE	FAILED 	B			BSYR	A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CL	CLIMB 	1			GL	07	26CC					TH136				LEFT MIXTURE CABLE FAILED, ENGINE QUIT ON TAKEOFF. RETURNED TO AIRPORT. REMOVED AND REPLACED CABLE.						1	L	7	2 	3O			 	3A16 					 
1995063000395	19950630	00395	CE 	1995	6	30	95ZZZX3257 	1	19950602	G	3230		GEAR 			CESSNA	310 	310R 	2074245	CE 										RT MLG	MALFUNCTIONED 	B			BSYR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	07	37575					310R1207				RIGHT GEAR WILL NOT DOWN AND LOCK. JACKED AIRCRAFT, CYCLED GEAR SEVERAL TIMES, NO PROBLEM FOUND.						1	L	7	2 	3O				3A10 					 
1995063000396	19950630	00396	EA 	1995	6	30	95ZZZX3258 	2	19950602	G	7322	25244919	SERVO 			PIPER 	PA60 	PA60600 	7106001	NM 	LYC 	O540 	IO540K1J5 	41532	EA 					FUEL INJ LT	DEFECTIVE 	B			BSYR	K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			GL	07	8090J					600576796118	L646648A			LEFT ENGINE WILL NOT PRODUCE POWER. REMOVED AND REPLACED FUEL SERVO. OPS CHECKED GOOD.						1	M	7	2 	3O	3	O	RT	A17WE 	1E4				 
1995063000397	19950630	00397	CE 	1995	6	30	95ZZZX3259 	1	19950616	G	3040	50175421	DUCT 			CESSNA	402 	402A 	207590M	CE 										PILOT DEFROST	DEFORMED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	4504Q					402A0004				INLET ON DUCT DEFORMED DUE TO HEAT RESTRICTING AIR FLOW (PILOT DEFROST). SUBMITTER FABRICATED NEW DUCT OUT OF FIBERGLAS	S USING OLD DUCT AS PATTERN. DAMAGE DIFFICULT TO DETECT. SUBMITTER SUGGESTS REMOVING HOSE, CABIN FIREWALL, TO INSPECT.					1	L	7	2 	3O				A7CE 					 
1995063000398	19950630	00398	CE 	1995	6	30	95ZZZX3260 	1	19950616	G	3040	50175422	DUCT 			CESSNA	402 	402A 	207590M	CE 										COPILOT DEFROST	DEFORMED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	4504Q	4601 				402A0004				INLET ON DUCT DEFORMED DUE TO HEAT RESTRICTING AIR FLOW. (COPILOT DEFROST.) SUBMITTER FABRICATED NEW DUCT OUT OF FIBER	GLASS USING OLD DUCT AS PATTERN. DAMAGE DIFFICULT TO DETECT. SUBMITTER SUGGESTS REMOVING HOSE, CABIN FIREWALL, TO INSP	ECT.				1	L	7	2 	3O				A7CE 					 
1995063000399	19950630	00399	CE 	1995	6	30	95ZZZX3261 	1	19950613	G	7820	165003338	MUFFLER 			CESSNA	188 	A188B 	2073005	CE 										EXHAUST SYSTEM	SHROUD FAILED 	G				O				OTHER 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			SO	05	4916Q					18802651T				SHROUD MISSING FROM EXHAUST SYSTEM MUFFLER WHICH CAUSED MUFFLER TO HEAT UP ENOUGH TO BURN A HOLE IN IT. BURNED UP INTAK	E AIR FILTER WHICH WAS INDUCED INTO ENGINE CAUSING ENGINE FAILURE.					1	L	7	1 	3O				A9CE 					 
1995063000401	19950630	00401		1995	6	30	95ZZZX3263 	4	19950501	G	3416		INDICATOR 	UNITEDINST 	593RP1 															ALTIMETER CASE	VSI COMPONENTS 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03					15457					VSI INDICATOR DELIVERED TO AN INSTRUMENT SHOP FOR OVERHAUL/REPAIR WAS FOUND TO HAVE A DATA PLATE REFLECTING AN ALTIMETER	 PN 593RP-1, SN 15457, NO OTHER IDENTIFICATION AS TO THE PN, SN, ON MANUFACTURER OF VSI. THE INSTRUMENT SHOP COULD NOT 	IDENTIFY MANUFACTURER OF VSI IN THE ALTIMETER CASE. INSTRUMENT REMOVED FROM SERVICE AND IDENTIFIED AS NON-SERVICEABLE.																	 
1995063000402	19950630	00402	SO 	1995	6	30	95ZZZX3264 	2	19950612	G	7314	6462121A5	FUEL PUMP 			CESSNA	185 	A185F 	2072821	CE 	CONT 	O520 	IO520D 	17032	SO 					ENGINE	DEFECTIVE 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			NE	05	4446C	536 			C319410BR	18504338	293028R			AIRCRAFT EXPERIENCED INTERMITTENT ROUGHNESS. FUEL PRESSURE CHECK SHOWED FLUCTUATING FUEL PRESSURE. REPLACED PUMP, ENGI	NE RAN SMOOTH WITH NO FLUCTUATION OF FUEL PRESSURE.					1	H	7	1 	3O	3	O		3A24 	E5CE				 
1995063000403	19950630	00403	SO 	1995	6	30	95ZZZX3265 	2	19950607	G	8530		CYLINDER 			CESSNA	150 	150 	2071802	CE 	CONT 	O200 	O200A 	17020	SO 					NR 4 CYL ROCKER	BOSS BROKEN 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			NE	05	66386		1283 			150760101	31612A			PILOT COMPLAINED OF ROUGH RUNNING ENGINE. UPON INVESTIGATION, FOUND NR 4 CYLINDER ROCKER SHAFT BOSSES (3 EACH) BROKEN O	FF. CYLINDER HAD ONLY 1283 HOURS SINCE OVERHAUL. SEE AD 94-05-05.					1	H	7	1 	3O	3	O	NT	3A19 	E252				 
1995063000404	19950630	00404	EU 	1995	6	30	95ZZZX3266 	1	19950605	G	3246	AH42671	WHEEL HALF 	DUNLOP 		HWKSLY	DH125 	BH125400A 	4230138	EU 										HUB	CRACKED 	B			QH5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	72HC				1051	NA780				INSPECTION FOUND A 1 INCH CRACK LOCATED IN THE RADIUS OF THE HUB ADJACENT TO THE PART NUMBER/SERIAL NUMBER. THIS PART W	AS EDDY CURRENT TESTED IAW DUNLOP 32-40-02(4), REV. 41.					2	L	7	2 	4J				A3EU 					 
1995063000405	19950630	00405	EA 	1995	6	30	95ZZZX3267 	2	19950616	G	8530	AL19001	VALVE 			CESSNA	172 	172M 	2072418	CE 	LYC 	O360 	O360A4M 	41514	EA 					EXHAUST	WORN 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			AL	03	64456	165 				17265243	L3218736A			ENGINE WAS OVERHAULED 7-25-94. SPIRIT AIR VALVES, PN AL19001 AND AL73938, WERE INSTALLED NEW AT THAT TIME. AT 165.0 HO	URS TSO, ENGINE RAN ROUGH. INSPECTION REVEALED ALL EXHAUST VALVES, PN AL19001, HAD ABNORMAL WEAR, ONE BEING EXTREME AND	 VERY NEAR FAILURE. ONLY ONE OF THE VALVE TIPS HAD NOT ERODED THE PART NUMBER AWAY. IT IS MARKED FAA-PMA Z 6 94 AL1900	1. TOTAL ENGINE FAILURE WAS IMMINENT.			1	H	7	1 	3O	3	O	NT	3A12 	E286				 
1995063000595	19950630	00595	SO 	1995	6	30	95ZZZX3269 	2	19950619	G	8530	539740	ROCKER ARM PIN 			CESSNA	414 	414 	2075908	CE 	CONT 	O520 	TSIO520J 	17040	SO 					LT ENG CYLS	WORN 	B			MJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	13MN		1400 			4140422	218655R			ROCKER ARM PINS WERE WORN ON ONE SIDE BEYOND LIMITS. SUSPECT WEAR WAS DUE TO AGE OF PARTS AND POSSIBLE OIL STARVATION.						1	L	7	2 	3O	3	O	RT	A7CE 	E8CE				 
1995063000596	19950630	00596	EA 	1995	6	30	95ZZZX3270 	2	19950612	G	8530		VALVE GUIDE 			PIPER 	PA32 	PA32301T 	7103209	SO 	LYC 	O540 	TIO540S1AD 	41532	EA 					EXHAUST	EXCESS WEAR 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	8317Y	873 				328124005	L751761A			C/W INSPECTION ITEM NR 9. REMOVAL OF ROCKER BOX COVERS EA400 HOURS AND FOUND EXCESSIVE EXHAUST DEPOSITS ON AND AROUND V	ALVE SPRINGS. C/W LYC SB 388B. EXHAUST VALVE GUIDE WEAR TO BE VERY EXCESSIVE .050 INCH PLUS ON FIVE OF THE SIX CYLINDE	RS, 837.00 HOURS SINCE NEW. SUBMITTER SUGGESTS VALVE FAILURE WAS IMMINENT WHICH COULD CAUSE TOTAL LOSS OF POWER.				1	L	7	1 	3O	3	O		A3SO 	E14EA				 
1995063000597	19950630	00597	EU 	1995	6	30	95ZZZX3271 	1	19950623	G	5730	T76G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING LT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3037H	1001 				2135				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000598	19950630	00598	EU 	1995	6	30	95ZZZX3272 	1	19950623	G	5730	T76G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING RT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3037H	1001 				2135				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000599	19950630	00599	SO 	1995	6	30	95ZZZX3273 	1	19950614	G	2822	2B664	PUMP 			PIPER 	PA31 	PA31350 	7103110	SO 										LT ENG FUEL	DEFECTIVE 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			WP	19	27419	14 			8AC87	317751170				EN ROUTE, LEFT ENGINE BECAME ROUGH AND LOST POWER. DURING INSPECTION, THE ENGINE WAS DETERMINED TO HAVE 2 PLUGGED INJEC	TORS. DURING RETURN, LEG FROM THE LOW PRESSURE FUEL LIGHT ILLUMINATED. DURING INSPECTION, THE SOURCE OF THE CONTAMINAT	ION WAS TRACED TO OVERHAULED LOW PRESSURE FUEL BOOST PUMP.				1	L	7	2 	3O				A20SO 					 
1995063000600	19950630	00600	CE 	1995	6	30	95ZZZX3274 	1	19950617	G	5400	08227811	GUSSET 		082260039 	CESSNA	310 	310C 	2074210	CE 										LT ENG NACELLE	CORRODED 	B			CSVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	1719H	5000 				310C35819				ANNUAL INSPECTION FOUND GUSSET LOCATED BELOW AUGMENTOR IN LT ENG NACELLE COMPLETELY CORRODED THROUGH. NUMEROUS RIVETS I	N AREA WERE GONE ALSO DUE TO CORROSION FROM EXHAUST GASSES AND HEAT OVER THE YEARS. PART IS LOCATED IN NACELLE ON TOP O	F WING SKIN AND CONNECTS REAR SPAR ASSY PN 0822600-39 AND LANDING GEAR WEB ASSY PN 0822175-3.				1	L	7	2 	3O				3A10 					 
1995063000601	19950630	00601	SO 	1995	6	30	95ZZZX3275 	2	19950615	G	7414	4201	MAGNETO 	SLICK 		CESSNA	150 	150J 	2071820	CE 	CONT 	O200 	O200A 	17020	SO 					ENGINE	COIL CRACKED 	B	S		CSVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	60971	745 			0010183R	15070705				UPON INSPECTION OF INTERNAL COMPONENTS OF MAGNETO AT ANNUAL INSPECTION, HIGH TENSION COIL WAS FOUND CRACKED.						1	H	7	1 	3O	3	O		3A19 	E252				 
1995063000602	19950630	00602	SO 	1995	6	30	95ZZZX3276 	1	19950617	G	7920	6390172	HOSE 			PIPER 	PA28 	PA28140 	7102802	SO 										COOLER LINE	RUPTURED 	B			CSVR	A				UNSCHED LANDING 				K	Y	E	FLUID LOSS 	ENGINE STOPPAGE 	VIBRATION/BUFFET 	NR	NOT REPORTED 	1			CE	01	5817V	3960 				2826647				DURING FLIGHT CHECKOUT, ENGINE STARTED RUNNING ROUGH WITH OIL PRESSURE DROPPING AND ENGINE SEIZED IN MID-AIR. FOUND OIL	 LINE TO COOLER RUPTURED. ORIGINAL HOSE NOT CHANGED AT OVERHAUL - DATED 1969. HOSE COVERED BY FIRESLEEVE, UNABLE TO IN	SPECT.				1	L	7	1 	3O				2A13 					 
1995063000603	19950630	00603	SO 	1995	6	30	95ZZZX3277 	1	19950617	G	5330	99473000	J-CHANNEL 			PIPER 	PA32 	PA32300 	7103212	SO 										LOWER CENTER SKI	FRACTURED 	B	S		CSVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	31737	1143 				327840146				AT ANNUAL INSPECTION, NOTICED EMPENNAGE AFT LOWER CENTER SKIN CRACKED. FOUND J-CHANNEL FRACTURED 1 INCH AFT OF 99477-00	0 CONNECTION AND ALSO FRACTURED 1 INCH AFT OF 6244300 BULKHEAD ASSY.					1	L	7	1 	3O				A3SO 					 
1995063000605	19950630	00605	CE 	1995	6	30	95ZZZX3279 	1	19950516	G	5312	07126155	BULKHEAD 			CESSNA	182 	182R 	2072731	CE 										FUSELAGE	CRACKED 	B			AHDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	171P					18268147				DURING ANNUAL INSPECTION, CRACKS WERE FOUND ON BULKHEAD EXTENDING INBOARD AND OUTBOARD FROM UPPER END OF DOUBLER PN 1212	127-3 BOTH LEFT AND RIGHT SIDE. AT THAT TIME CHECKED THE THREE OTHER 182'S UNDER THIS OPERATOR'S CONTROL. FOUND SIMILA	R CRACKS IN N181P, SN 18268135, TOTAL TIME 6271.5. THESE AIRCRAFT ARE OPERATED 'LOW AND SLOW' AND IN TURBULENT AIR WHIC	H SUBMITTER BELIEVED CAUSED THESE CRACKS. SUBMITTER SUGGESTS A MODIFICATION LIKE THE ONE FOR THE 200 SERIES WOULD REINF	ORCE THE BULKHEAD ENOUGH TO PREVENT LIKE CRACKS. THIS MODIFICATION IS AVAILABLE UNDER CESSNA'S SB SEB88-3 FOR CESSNA 21	0 SERIES ONLY.	1	L	7	1 	3O			NT	3A13 					 
1995063000606	19950630	00606	CE 	1995	6	30	95ZZZX3280 	1	19950516	G	5312	07126155	BULKHEAD 			CESSNA	182 	182R 	2072731	CE 										FUSELAGE	CRACKED 	B			AHDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	181P					18268135				DURING ANNUAL INSPECTION, CRACKS WERE FOUND ON BULKHEAD EXTENDING INBOARD AND OUTBOARD FROM UPPER END OF DOUBLER PN 1212	127-3 BOTH LEFT AND RIGHT SIDE. AT THAT TIME CHECKED THE THREE OTHER 182'S UNDER THIS OPERATOR'S CONTROL. FOUND SIMILA	R CRACKS IN N181P, SN 18268135, TOTAL TIME 6271.5. THESE AIRCRAFT ARE OPERATED 'LOW AND SLOW' AND IN TURBULENT AIR WHIC	H SUBMITTER BELIEVED CAUSED THESE CRACKS. SUBMITTER SUGGESTS A MODIFICATION LIKE THE ONE FOR THE 200 SERIES WOULD REINF	ORCE THE BULKHEAD ENOUGH TO PREVENT LIKE CRACKS. THIS MODIFICATION IS AVAILABLE UNDER CESSNA'S SB SEB88-3 FOR CESSNA 21	0 SERIES ONLY.	1	L	7	1 	3O			NT	3A13 					 
1995063000607	19950630	00607	CE 	1995	6	30	95ZZZX3281 	1	19950616	G	7603	5038901223	CONTROL ASSY 			BEECH 	58 	58 	1152740	CE 										LT THROTTLE	ROD END FAILED 	E				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			O			OTHER 			NR	NOT REPORTED 	1			SW	11	169RR	4487 				TH999				DURING FLIGHT, LT THROTTLE ROD END BROKE OFF OF CABLE. FLIGHT CREW CARRIED OUT LT ENGINE SHUT-DOWN CHECK LIST AND LANDE	D WITHOUT INCIDENT. SUBMITTER SUGGESTS IN ORDER TO PREVENT RECURRENCE, A LIFE LIMIT SHOULD BE ESTABLISHED FOR THE CABLE	 ASSEMBLY.				1	L	7	2 	3O				3A16 					 
1995063000608	19950630	00608	SO 	1995	6	30	95ZZZX3282 	2	19950619	G	8530	534397	ROCKER ARM 			CESSNA	414 	414 	2075908	CE 	CONT 	O520 	TSIO520J 	17040	SO 					LT ENG CYLS	BEARING WORN 	B			MJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	13MN		1400 			4140422	218655R			ROCKER ARM BEARING WORN BEYOND LIMITS. SUSPECT DUE TO AGE AND OIL STARVATION TO THIS PART.						1	L	7	2 	3O	3	O	RT	A7CE 	E8CE				 
1995063000609	19950630	00609	SO 	1995	6	30	95ZZZX3283 	2	19950619	G	8530	534398	ROCKER ARM 			CESSNA	414 	414 	2075908	CE 	CONT 	O520 	TSIO520J 	17040	SO 					LT ENG CYLS	WORN 	B			MJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	13MN		1400 			4140422	218655R			ROCKER ARM BEARING WORN BEYOND LIMITS. SUSPECT DUE TO AGE AND OIL STARVATION TO THIS PART.						1	L	7	2 	3O	3	O	RT	A7CE 	E8CE				 
1995063000610	19950630	00610	SW 	1995	6	30	95ZZZX3284 	1	19950601	G	2823		VALVE ROD 			BBAVIA	7 	7GC 	2110126	SW 										FUEL SHUTOFF	BROKEN 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	4871E					7GC76				FUEL SHUT OFF EXTENSION ROD UNIVERSAL JOINT SEPARATED WHILE TURNING FUEL ON. SUSPECT INADEQUATE STRENGTH. HAVE INSPECT	ED SEVERAL AIRCRAFT AND FOUND THESE UNIVERSAL JOINTS BADLY WORN AND WILL NOT ALLOW FULL RANGE OPERATION OF FUEL SHUTOFF 	VALVE. SUBMITTER RECOMMENDS REDESIGN OF UNIVERSAL JOINTS AND INSPECT FULL RANGE OPERATION OF VALVE.				1	H	7	1 	3O				A759 					 
1995063000611	19950630	00611	EU 	1995	6	30	95ZZZX3285 	1	19950620	G	5730	T67G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING LT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	7020D	662 				2109				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000612	19950630	00612	EU 	1995	6	30	95ZZZX3286 	1	19950620	G	5730	T67G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING RT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	7020D	662 				2109				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000613	19950630	00613	EU 	1995	6	30	95ZZZX3287 	1	19950620	G	5730	T67G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING RT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	30377	357 				2138				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000614	19950630	00614	EU 	1995	6	30	95ZZZX3288 	1	19950620	G	5730	T67G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING LT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	30377	357 				2138				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000615	19950630	00615	EU 	1995	6	30	95ZZZX3289 	1	19950620	G	5730	T67G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING RT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3037X	346 				2137				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000616	19950630	00616	EU 	1995	6	30	95ZZZX3290 	1	19950620	G	5730	T67G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING LT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3037X	346 				2137				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000617	19950630	00617	EU 	1995	6	30	95ZZZX3291 	1	19950620	G	5730	T67G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING LT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	30364	297 				2132				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995063000618	19950630	00618	EU 	1995	6	30	95ZZZX3292 	1	19950620	G	5730	T67G20003	SKIN 			SLNSBY	T67 	T67M260 	8323006	EU 										WING RT NR 2 RIB	DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	30364	297 				2132				A ONE-TIME INSPECTION FOUND LT AND RT WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTER LINE.						1	L	7	1 	3O			NT	A73EU 					 
1995070700005	19950707	00005	WP 	1995	7	7	95ZZZX3297 	1	19950615	G	7603	369A7313	HOUSING 			HUGHES	369 	369D 	4470706	WP 										COLLECTIVE	WORN 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R	7173 				1151D				PILOT REPORTED THE IDLE WAS TOO LOW AT LIGHT OFF AND TOO HIGH AFTER ROLL-DOWN FROM FLIGHT IDLE. AFTER A LENGTHY PROCESS	 OF POKING, RIGGING, AND PRODDING, DISCOVERED THE SWITCH HOUSING AT THE END OF THE COLLECTIVE WAS WORN AT ITS INTERNAL S	TOPS. REPLACED UNIT AND RIGGED THE THROTTLE SYSTEM.				1	G	7	1 	3U				H3WE 					 
1995070700016	19950707	00016	CE 	1995	7	7	95ZZZX3303 	1	19950215	G	5751	9913000011	SKIN 		99130000618 	BEECH 	99 	C99 	1154006	CE 										RT AIL UPPER	CRACKED 	B	S	A	EHHR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	6645K	6750 			U219R	U209				RIGHT AILERON FOUND CRACKED ON TOP AFT OUTBOARD SKIN FORWARD SIDE. DURING ROUTINE, 4 INCH CRACK FOUND AT FORWARD SECTIO	N OF AFT SKIN WHERE IT MEETS FORWARD SKIN AT AILERON CENTER SPAR.					1	L	7	2 	3T				A14CE 					 
1995070700017	19950707	00017	CE 	1995	7	7	95ZZZX3304 	1	19950215	G	5751	9913000011	SKIN 		99130000618 	BEECH 	90 	E90 	1152914	CE 										RT AIL UPPER	CRACKED 	B			EHHR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	74VR	6750 				LW135				RIGHT AILERON FOUND CRACKED ON TOP AFT OUTBOARD SKIN FORWARD SIDE. DURING ROUTINE, 4 INCH CRACK FOUND AT FORWARD SECTIO	N OF AFT SKIN WHERE IT MEETS FORWARD SKIN AT AILERON CENTER SPAR.					1	L	7	2 	3T				3A20 					 
1995070700018	19950707	00018	CE 	1995	7	7	95ZZZX3305 	1	19950613	G	5210	551123515	HINGE 			CESSNA	500 	550 	2076604	CE 										CABIN DOOR	CRACKED 	B		A	JA2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	57AJ	4491 				5500085				WHILE CHECKING A DOOR SEAL PROBLEM, THE PAINT WAS FOUND CRACKED ON THE LOWER CABIN DOOR HINGE LEG. IT WAS FOUND TO BE A	 CRACK THAT EXTENDS APPROXIMATELY 65 PERCENT IN LENGTH OF LOWER PART LEG. REMOVED AND INSTALLED NEW HINGE ASSEMBLY. TH	E LOWER LEG RECEIVED ALL DOOR OPEN LIMIT LOADS AS DESIGNED.				1	L	7	2 	4F				A22CE 					 
1995070700019	19950707	00019	CE 	1995	7	7	95ZZZX3306 	1	19950612	G	7603	9938000131	CONTROL CABLE 			BEECH 	200 	B200 	1152922	CE 										RT WHEELWELL	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	6182A	339 				BB1484				DURING PRE-FLIGHT INSPECTION, FND RUB MARK ON PROTECTIVE COVERING ON RT IDLE CNTRL CABLE. RUB AREA LOCATION IN RT WW, F	WD OTBD SIDE, APPROX 2 INCHES INBD FROM ADEL CLAMP & ABOUT 1 INCH IN LENGTH. NOTICED SPACERS FOR BOTH WW ADEL CLAMPS WE	RE .75 INCH LONG & PUSHING BOTH IDLE CNTRL CABLE PN 99-380001-31 & PWR CNTRL CABLE PN 115-389001-27 INTO PATH OF NR 4 MA	IN TIRE (STD GEAR) DURING RETRACTION/EXTENSION PROCESS. REMOVED .75 INCH LONG ALUM SPACER & INSTALLED .50 INCH LONG ALU	M SPACERS. WRAPPED CABLE IN TEFLON SPIRAL WRAP, IN RUB AREA. SWUNG GEAR SEVERAL TIMES. OPS CHD OK, NO RUBBING NOTICED.	 NOTE: INSPECTED SEVERAL 200 SERIES KING AIRS & FND THEY HAD .50 INCH SPACERS OR LESS. ACTT 338.9, TOTAL CYCLES 289.	1	L	7	2 	4T				A24CE 					 
1995070700020	19950707	00020	CE 	1995	7	7	95ZZZX3307 	1	19950613	G	5520	45AS66010009	HORN 			BEECH 	MU300 	400BEECH 		CE 										LT ELEVATOR	BURNED THROUGH 	B		A	OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	3038V	473 				RK93				LEFT ELEVATOR HEATED HORN SURFACE BURNED THROUGH SURFACE IN 5 SPOTS. TOTAL BURN AREA APPROX 3 SQUARE INCHES. METAL LIN	ER BENEATH TIP ALSO MELTED ALONG TO OUTBOARD EDGE. SUBMITTER STATED THIS IS FOURTH FAILURE BY THIS OPERATOR OF 2 AIRCRA	FT. FAILURES ARE SINGULAR IN NATURE OVER TOTAL OF 700 HOURS OF OPERATION.				2	H	7	2 	4F			RT	A16SW 					 
1995070700021	19950707	00021	CE 	1995	7	7	95ZZZX3308 	1	19950612	G	3242	16413601	DISC 			CESSNA	185 	A185F 	2072821	CE 										RT BRAKE	BROKEN 	D				O				OTHER 				O			OTHER 			TX	TAXI/GRND HDL 	1			NE	01	9F					18502855				WHILE TAXIING, PILOT LOST STEERING CONTROL WITH BRAKES. FOUND RIGHT BRAKE DISC BROKEN AWAY FROM WHEEL ASSEMBLY AT BOLT 	FLANGE. WHEEL HALF AND BOLTS STILL ATTACHED AND TORQUED. INSTALLED NEW DISC AND RETURNED TO SERVICE.					1	H	7	1 	3O				3A24 					 
1995070700022	19950707	00022	CE 	1995	7	7	95ZZZX3309 	1	19950603	G	3211		BOLT 			CESSNA	180 	180 	2072602	CE 										RT MLG SADDLE	BROKEN 	D		A		O				OTHER 				O			OTHER 			LD	LANDING 	1			GL	15	3149D					31947				AIRCRAFT VEERED OFF OF RIGHT SIDE OF RUNWAY RUNNING INTO TREES, CAME TO REST, THEN BURST INTO FLAMES. THE PASSENGER REP	ORTED THE AIRCRAFT DRIFTED TO THE RIGHT JUST BEFORE TAKEOFF. DURING INVESTIGATION, THE BOLT HOLDING THE RIGHT LANDING G	EAR STRUT TO A SADDLE ON THE AIRFRAME WAS FOUND BROKEN. REF CESSNA IPC F & I 41-9.				1	H	7	1 	3O			NC	5A6 					 
1995070700023	19950707	00023	CE 	1995	7	7	95ZZZX3310 	1	19950612	G	2436		REGULATOR 			CESSNA	182 	TR182 	2072735	CE 										CONNECTOR	WATER CONTAM 	B			LX2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	27	737VT					R18200886				CUSTOMER COMPLAINED ALTERNATOR WAS CUTTING IN AND OUT. PULLED IN SHOP, CHECKED ALTERNATOR. CHECKED VOLTAGE REGULATOR (	ALTERNATOR CONTROL UNIT). IT WAS OK. RAN UP AIRCRAFT, ALTERNATOR STILL INTERMITTENT. INSPECTED WIRING, NO PROBLEM FOU	ND. REMOVED ALTERNATOR CONTROL UNIT FROM FIRE WALL AND ACCIDENTALLY TIPPED UPSIDE DOWN, WATER RAN OUT OF 6-PIN PLASTIC 	CONNECTOR. DRIED OUT CONNECTOR, NO MORE PROBLEMS. SUBMITTER SUGGESTS SEAL WIRE HOLES WITH SILICON OR MOUNT PLUG HORIZO	NTALLY, SO NO WATER CAN FILL UP PLUG.		1	H	7	1 	3O				3A13 					 
1995070700024	19950707	00024	EA 	1995	7	7	95ZZZX3311 	2	19950525	G	7414	10400326	IMPULSE COUPLING	BENDIX 	D6LN3000 	EAGLE 	DW 	DW1 	3230203	GL 	LYC 	O540 	IO540M1B5 	41532	EA 					MAGNETO	WORN 	B			CSLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	88032	500 			2060559	DW1002681	L2116648A			AIRCRAFT WOULD NOT START. FOUND IMPULSE COUPLING WOULD NOT ENGAGE AT ALL TIMES. FOUND EXCESSIVE WEAR ON TOE OF FLYWEIG	HTS WHICH WOULD NOT ALLOW COUPLING TO ENGAGE TOP PINS. NO WEAR NOTED ON PINS. INSPECTION PER TCM BULLETIN WOULD HAVE I	NDICATED AN AIRWORTHY COUPLING. THIS COUPLING IS THE NEW STYLE SNAP RING STYLE.				1	Q	7	1 	3R	3	O	NC	A4NW 	1E4				 
1995070700025	19950707	00025	NE 	1995	7	7	95ZZZX3312 	2	19950614	G	8500		ENGINE 			DOUG 	DC3 	DC3A 	3021433	WP 	PWA 	R1830 	R183090D 	52020	NE 					NR 2	MAKING METAL 	C			RPFB	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	17	32MS	1183 	473 			4978	CP350411			OIL TEMP HIGHER THAN NORMAL ON TRAINING FLIGHT. FOUND SMALL AMOUNT OF METAL IN OIL SCREEN. ENGINE REMOVED FOR REPAIR 6	-13-95.					2	L	7	2 	4R	4	R		A669 	5E4				 
1995070700603	19950707	00603		1995	7	7	95ZZZX3313 	1	19950213	G	2432	ABC11530	CHARGER 	ACME URDC 																BATTERY	DEFECTIVE 	B			SH5R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	03					267					INSPECTION OF BATTERY CHARGER FOUND DRIVER ASSEMBLY P/N 117BC106-F BURNED. ALSO, Q101 AND Q102, HIGH CURRENT SWITCHING 	TRANSISTORS BURNED. VISUAL INSPECTION ALSO FOUND CAPACITOR ASSEMBLY 117BC104 TO BE THE WRONG REV NR. SHOULD BE REV 'C'	. FOUND CLIP FOR C106 NOT CORRECT PART NUMBER, SHOULD BE 6018-8A. FOUND LOOSE HARDWARE ON CR104. THIS UNIT IS IMPROPE	RLY IDENTIFIED AS A P/N-11.																 
1995070700604	19950707	00604	GL 	1995	7	7	95ZZZX3314 	1	19950507	G	7921	8406E	COOLER 			AMTR 	LONGEZ	LONGEZ 	05690Z8	GL 										ENGINE OIL	RUPTURED 	G				A				UNSCHED LANDING 				K			FLUID LOSS 			CR	CRUISE 	1			GL	23	57JP	2200 			14922	1023				OIL COOLER IS PART OF A CERTIFIED ENGINE INST ON A CE-172M. DURING CRUISE FLIGHT, THE OIL COOLER RUPTURED IN THE AREA O	F THE END TANK ON THE OUTPUT SIDE OF THE COOLER. THIS CAUSED A RAPID LOSS OF OIL AND ENGINE FAILURE. ON-AIRPORT LANDIN	G WITHOUT FURTHER DAMAGE. IT IS SUSPECTED DURING MFG OF THIS PART, THE SOLDER FLUX WAS NOT THOROUGHLY CLEANED FROM THE 	TANK WHICH CAUSED A THINNING OF THE METAL.			1	M	7	1 	3O			RT	EXPA1M71					 
1995070700605	19950707	00605	EA 	1995	7	7	95ZZZX3315 	2	19950428	G	7414		MAGNETO 	BENDIX 	6050880 	BEECH 	B80 	B80 	1153010	CE 	LYC 	O540 	IGSO540A1D 	41532	EA 					LT ENG LT MAG	POINTS GROUNDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	65RW	2224 	924 			LD404	L256450			ON THE THIRD FLIGHT OF THE DAY, THE LEFT ENGINE FAILED TO START. THE CAP WAS REMOVED FROM THE MAG AND MOISTURE WAS FOUN	D WHICH WAS GROUNDING THE VIBRATOR POINTS. MAG WAS DRYED OUT. OPS CHECK OK.					1	L	7	2 	3O	3	O	RT	3A20 	1E7				 
1995070700606	19950707	00606	NE 	1995	7	7	95ZZZX3316 	1	19950406	G	5543	17004811	TAB ANGLE 		1700481 	CONAER	LA4 	LA4250 	5110320	NE 										RUDDER TRIM	CRACKED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	09	8427E					94				WHILE INSTALLING RUDDER TRIM KIT FROM AEROFAB, ANGLE SUPPLIED WITH KIT WAS FOUND IN A CRACKED CONDITION IN BEND RADIUS. 	 A REPLACEMENT PART WAS ORDERED FROM FACTORY, IT ARRIVED WITH SAME CRACK IN IDENTICAL LOCATION. THESE ARE NEW PARTS. A	FTER CONTACTING MFG A SECOND TIME, FOUND STOCK PARTS HAD SAME DEFECTS. A SERVICEABLE PART WAS FOUND BY MFG AND WAS SENT	. SUBMITTER RECOMMENDS ANYONE WHO HAS INSTALLED ONE OF THESE KITS INSPECT ANGLE ASSY ON TRIM TAB AS SOON AS POSSIBLE.			1	H	7	1 	3O				1A13 					 
1995070700607	19950707	00607	GL 	1995	7	7	95ZZZX3317 	3	19950127	G	6111	D495	FORK 			BEECH 	200 	200BEECH 	1152920	CE 						HARTZL	HCD4N3	HCD4N3A 	GL 	PITCH CHANGE	CRACKED 	B			FR6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03								FY18		DURING TIME OVERHAUL OF THESE PROPS, THE PITCH CHANGE FORK WAS FOUND CRACKED. FAILURE OF THIS PART WOULD CAUSE ONE BLAD	E NOT TO BE CONTROLLED DURING PITCH CHANGE OF THE PROP AND COULD CAUSE SEVERE VIBRATION BECAUSE BLADE ANGLES WOULD NO LO	NGER MATCH BETWEEN BLADES.				1	L	7	2 	4T				A24CE 		5	C	STC	 
1995070700608	19950707	00608	EU 	1995	7	7	95ZZZX3318 	1	19950607	G	3320	5100D10	LIGHTING TUBE 			AMD 	FALC50	FALCON900 	2700160	EU 										CABIN	OVERHEAT 	B	L	A	RO3R	K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			CE	03	900MA					67				DURING ROUTINE FALCON 900 C-INSPECTION, THE CABIN DECORATIVE WINDOW PANELS WERE REMOVED. CABIN FLUORESCENT LIGHTING TUB	E END FITTING INSULATORS WERE DISCOLORED AND CRACKED. FABRIC ON THE DECORATIVE WINDOW PANEL WAS CHARRED IN 5 PLACES. L	IGHT BULBS HELD IN POSITION WITH TYE-WRAPS AROUND TUBE INSULATORS WHICH WERE FOUND DISCOLORED AND BRITTLE. THERE ARE 16	 TUBE END FITTINGS INSULATORS PER SIDE. LIGHT BULBS ARE LOCATED BETWEEN FRAME 9 (STA 152.38) THROUGH FRAME 22 (STA 451.	80). FALCON JET 900 CUSTOMER INFORMATION BULLETIN DATED JULY, '91, REV 1 STATES 'THAT DISCOLORED AND CRACKED INSULATORS	 ARE ALLOWABLE'. THE C.I.B. PROVIDES FOR A TEMPORARY REPAIR UNTIL REPLACEMENT.	2	L	7	3 	4F			RT	A46EU 					 
1995070700609	19950707	00609	EU 	1995	7	7	95ZZZX3319 	1	19950607	G	3320	5100D10	LIGHTING TUBE 			AMD 	FALC50	FALCON900 	2700160	EU 										CABIN	OVERHEAT 	B	L		RO3R	K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			CE	03	900HC					68				DURING ROUTINE FALCON 900 C-INSPECTION, THE CABIN DECORATIVE WINDOW PANELS WERE REMOVED. CABIN FLUORESCENT LIGHTING TUB	E END FITTING INSULATORS WERE DISCOLORED AND CRACKED. FABRIC ON THE DECORATIVE WINDOW PANEL WAS CHARRED IN 5 PLACES. L	IGHT BULBS HELD IN POSITION WITH TYE-WRAPS AROUND TUBE INSULATORS WHICH WERE FOUND DISCOLORED AND BRITTLE. THERE ARE 16	 TUBE END FITTINGS INSULATORS PER SIDE. LIGHT BULBS ARE LOCATED BETWEEN FRAME 9 (STA 152.38) THROUGH FRAME 22 (STA 451.	80). FALCON JET 900 CUSTOMER INFORMATION BULLETIN DATED JULY, '91, REV 1 STATES 'THAT DISCOLORED AND CRACKED INSULATORS	 ARE ALLOWABLE'. THE C.I.B. PROVIDES FOR A TEMPORARY REPAIR UNTIL REPLACEMENT.	2	L	7	3 	4F			RT	A46EU 					 
1995070700610	19950707	00610	WP 	1995	7	7	95ZZZX3320 	1	19950622	G	2721	AN310	CONTROL ROD BOLT			NAMER 	B25 	TB25N 	6400714	WP 										RUD TRIM TAB	FAILED 	D	L	A		A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			DE	DESCENT 	1			SW	15	25YR	11 				4327868				DURING DESCENT, ACFT EXPERIENCED A VIOLENT SHAKING DUE TO RUDDER OSCILLATION. SUCCESSFUL LANDING ACCOMPLISHED. FOUND R	UDDER TRIM TAB BOLT SHEARED AND FALLEN OUT. TAB WAS FREE TO FLUTTER INDUCING LARGE RUDDER INPUTS. ALL TAB CONTROL COMP	ONENTS WERE INTACT AT WALK-AROUND				2	M	7	2 	4R				LTC2 					 
1995070700611	19950707	00611	CE 	1995	7	7	95ZZZX3321 	1	19950510	G	5700	NAS679A5	NUT 			CESSNA	206 	TU206F 	2073353	CE 										WING LIFT STRUT	BROKEN 	G	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	1046V	2126 				U20602418				ON ANNUAL INSPECTION WHEN LOWER LIFT STRUT FAIRINGS WERE REMOVED, SEVERAL PIECES OF BROKEN NAS679 NUTS FELL OUT. INSPEC	TION OF REMAINING NUTS REVEALED SEVERAL CRACKED NUTS. WHEN NUTS WERE REMOVED FOR REPLACEMENT, SOME BOLTS FELL OUT. SUS	PECT CAUSE IS BAD BATCH OF NUTS FROM MANUFACTURER. RECOMMEND ONE TIME AD REQUIRING REPLACEMENT OF NUTS AND BOLTS WITH B	OLTS AND NUTS USED ON LATER CE 206 MODEL ACFT. P/N NAS464P5A27 BOLT AND P/N MS 21042L5 NUT.			1	H	7	1 	3O				A4CE 					 
1995070700612	19950707	00612	GL 	1995	7	7	95ZZZX3322 	3	19950612	G	6114	57D32612	HUB 			PIPER 	PA31 	PA31 	7103102	SO 						HARTZL	HCE3Y	HCE3YR2 	GL 	PROP	CRACKED 	B			QV2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	111PK	2014 				317401246		DJ7963		PROPELLER RETURNED FOR OVERHAUL. CRACK FOUND IN HUB DURING PENETRANT INSPECTION. HUB RETURNED TO HARTZELL FOR EVALUATI	ON. NOTE: THIS HUB IS POST AD 94-17-13.					1	L	7	2 	3O				A20SO 		5	C	P33EA	 
1995070700613	19950707	00613	CE 	1995	7	7	95ZZZX3323 	1	19950626	G	7922	75944	VALVE 			BEECH 	76 	76 	1153005	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	6706Y	1200 			109180	ME299				WHILE COMPLYING WITH LYCOMING SB NR 518C, FOUND VALVE RETAINING NUT LOOSE (BOTH ENGINES). RECOMMEND NUT BE WELDED AT FA	CTORY. NO ATTEMPTS SHOULD BE MADE TO RE-CRIMP NUTS AS THEY WILL FRACTURE AND FRACTURE MAY GO UNNOTICED. SUBMITTER SUGG	ESTS AD NOTE BE ISSUED.				1	L	7	2 	3O				A29CE 					 
1995070700614	19950707	00614	CE 	1995	7	7	95ZZZX3324 	1	19950626	G	7922	75944	VALVE 			BEECH 	76 	76 	1153005	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	6706Y	1200 			110310	ME299				WHILE COMPLYING WITH LYCOMING SB NR 518C, FOUND VALVE RETAINING NUT LOOSE (BOTH ENGINES). RECOMMEND NUT BE WELDED AT FA	CTORY. NO ATTEMPTS SHOULD BE MADE TO RE-CRIMP NUTS AS THEY WILL FRACTURE AND FRACTURE MAY GO UNNOTICED. SUBMITTER SUGG	ESTS AD NOTE BE ISSUED.				1	L	7	2 	3O				A29CE 					 
1995070700615	19950707	00615	GL 	1995	7	7	95ZZZX3325 	3	19950601	G	6111	A321	SCREW 		C1301 	BEECH 	95 	95 	1153402	CE 						HARTZL	HC92W	HC92WK2 	GL 	BLADE CLAMP	BROKEN 	B			UP7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13					EF7883					DURING DISASEMBLY, INNER CLAMP SCREW FOUND BROKEN OFF ON THE SHANK AT TOP THREAD, ENTERING CLAMP. SURFACE OF BREAK APPE	ARED CLEAN WITH A SMALL PIT ORIGINATING IN THE MIDDLE OF THE THREAD AREA. SUSPECT PIT WAS CAUSED BY MOISTURE CREEPING A	ROUND SOCKET HEAD OF SCREW. SUGGEST COUNTER BORE OF BOLT BE SEALED WITH RTV, 102, OR 103 AFTER SCREW IS INSTALLED AND T	ORQUED. SCREW IS SUBJECT TO SB 202 AND AD NOTE 95-11-08.			1	L	7	2 	3O				3A16 		5	C	P16EA	 
1995070700617	19950707	00617	SW 	1995	7	7	95ZZZX3327 	1	19950601	G	7922	75944	VALVE 			GULSTM	500 	500S 	0141107	SW 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	303EG					3313				INSPECTED VALVE ASSEMBLY PER LYCOMING SB 518C. FOUND SLIGHT MOVEMENT OF NUT IN CRIMP AREA. MODIFIED VALVE IAW LYCOMING	 SI 1423.					1	H	7	2 	3O				6A1 					 
1995070700618	19950707	00618	EA 	1995	7	7	95ZZZX3328 	2	19950406	G	7322	2539449	ADJUSTING NUT 	BENDIX 	252427311 	CESSNA	188 	A188B 	2073005	CE 	LYC 	O540 	IO540K1G5 	41532	EA 					SERVO BALL STEM	MISSING 	B			JK2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	4854R				31705	18802373T	L1880848A			INJECTOR ARRIVED WITH NO FUEL FLOW. UPON PUTTING IT ON FLOW BENCH USING NORMAL FLOW PROCEDURES, WAS UNABLE TO GET FUEL 	FLOW. REMOVED HEX BRASS NUT FROM REGULATOR. THE RETAINING AND FLOW ADJUSTING NUT WAS MISSING. RECOMMEND ALL FLOW BENC	H OPERATORS SHOULD BE CAUTIONED ABOUT C/W SB RS-71, LOCTITE THE ADJUSTING NUT.				1	L	7	1 	3O	3	O		A9CE 	1E4				 
1995070700619	19950707	00619	NE 	1995	7	7	95ZZZX3329 	2	19950502	G	7250	411105064	ROTOR 								LYC 	LTS101	LTS101650C3 	41560	NE 					GP ROTOR	BLADES CRACKED 	B			E5RR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		202 					LE41115			DURING INSPECTION PER SB LT101-72-50-0150, SEVERAL BLADES FOUND TO HAVE INDICATION OF CRACKS DURING FPI. CRACKS WERE IN	 THE BLADE ROOT AREA. INVESTIGATION IS ON-GOING.										3	U			E5NE				 
1995070700620	19950707	00620	CE 	1995	7	7	95ZZZX3330 	1	19950623	G	7603	850433	BALL JOINT 		45AS4201013 	BEECH 	MU300 	400BEECH 		CE 										LT ENG CONTROL	DETACHED 	B	L	A	UJDR	D				RETURN TO BLOCK 				O			OTHER 			TX	TAXI/GRND HDL 	1			EA	05	10J					RK31				WHILE TAXIING FOR TAKEOFF, NOTED LEFT ENG FAILED TO RESPOND TO POWER LEVER INPUT TO ACCELERATE. THE TAKEOFF WAS WAIVED 	AND TAXIING BACK TO THE RAMP, THE LEFT ENG WAS NOT RESPONDING TO ANY POWER LEVER COMMANDS. THE ENG WAS SHUT DOWN USING 	THE FIREWALL SHUT-OFF VALVES. INVESTIGATION DISCLOSED THE BALL JOINT SWIVEL ASSY LOCATED ON THE FORWARD END OF THE ENG 	CONTROL CABLE HAD UNTHREADED. ALSO, NOTED THE BALL JOINT SWIVEL ASSY ON THE RT ENG CONTROL CABLE WAS LOOSE ON THE CONTR	OL CABLE SHAFT AND COULD BE UNTHREADED BY ROTATING USING LIGHT FINGER PRESSURE. NEITHER LT OR RT CONTROL CABLES APPEARE	D DAMAGED IN THE AREA OF THE SWIVEL ASSEMBLIES.	2	H	7	2 	4F			RT	A16SW 					 
1995071400130	19950714	00130	GL 	1995	7	14	95ZZZX3332 	2	19950415	G	7210	524919	SEAL 			BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20 	03013	GL 					ENG GEARBOX	LEAKING 	B			TU3R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	07	303PD	472 				4319	CAE270680			SEAL LEAKING. REMOVED AND REPLACED WITH NEW P/N SEAL.						1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995071400131	19950714	00131	NE 	1995	7	14	95ZZZX3333 	2	19950510	G	7323	25249994	GOVERNOR 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					NR 1 ENGINE	MALFUNCTION 	D				O				OTHER 				Y			ENGINE STOPPAGE 			CL	CLIMB 	1			SW	03	21498	10423	4573 		A52500	36003	CPPS63184			AFTER TAKEOFF FROM HELIPORT, NR 1 ENGINE DROPPED OFF LINE. CONTINUED ON TO PHI. LANDED WITHOUT INCIDENT. INVESTIGATIO	N FOUND GOVERNOR MALFUNCTION. P & W IPC, 72-10-30, PAGE 0, FIGURE 1, ITEM 20.					1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995071400132	19950714	00132	GL 	1995	7	14	95ZZZX3334 	2	19950608	G	7321	23057344	FUEL CONTROL 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	MALFUNCTION 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y		66 			490496D	CAE831718			AIRCRAFT HUNG-START AT 30 PERCENT - ALL SUBSEQUENT ADJUSTMENT HAD LITTLE OR NEGATIVE EFFECT ON THE FUEL SCHEDULING. REM	OVED AND REPLACED UNIT AND AIRCRAFT STARTS NOW. UNIT SENT IN FOR OVERHAUL.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995071400133	19950714	00133	GL 	1995	7	14	95ZZZX3335 	2	19950515	G	7532	23005366	BLEED VALVE 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					ENGINE	FAILED 	E				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			SW	03	6610Y		1326 		FF26510	51419	CAE895529			SHORTLY AFTER TAKEOFF, PILOT REPORTED ENGINE COMPRESSOR STALL. LANDED ON OFFSHORE PLATFORM WITHOUT INCIDENT. FOUND BLE	ED VALVE STUCK IN OPEN POSITION. ALLISON 250-C30 IPC, CHAPTER 75, SECTION 10-00, FIGURE 5, ITEM 1J.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995071400134	19950714	00134	GL 	1995	7	14	95ZZZX3336 	2	19950512	G	7250	6876667	AIR TUBE 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20 	03013	GL 					NR 1 ENGINE	HOLE CHAFED 	E				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			SW	03	54197		1663 		CAT37782	S805	CAE802035F			IN CRUISE FLIGHT, PILOT EXPERIENCED AN ENGINE TORQUE SPLIT, NR 1 ENGINE DROPPING OFF-LINE. LANDED ON OFFSHORE PLATFORM 	WITHOUT INCIDENT. FOUND HOLE CHAFED IN AIR TRANSFER TUBE, WITH ASSOCIATED CRACKS. ALLISON IPC, CHAPTERS 2-60, FIGURE 1	3, ITEM 24.				1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995071400135	19950714	00135	GL 	1995	7	14	95ZZZX3337 	2	19950531	G	7261	6895096	FILTER CAP 		23035179 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					GEAR BOX OIL	BROKEN 	E				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			B	J		SMOKE/FUMES/ODORS/SPARKS 	WARNING INDICATION 		CR	CRUISE 	1			SW	03	1546K				CAG90620	760082	CAE890616S			ON 5-31-95 AT 1700, PILOT REPORTED NR 2 ENGINE LOW PRESSURE LIGHT ON. OIL PRESSURE LOW. SMELL OF OIL IN CABIN. SHUT D	OWN ENGINE. SINGLE ENGINE LANDING MADE IN HOUMA. FOUND EAR ON ENGINE OIL FILTER CAP BROKEN, O-RING CUT. MINIMUM OIL P	RESSURE BEFORE ENGINE SHUT DOWN, 50 PSI. S-76 IPC, FIGURE 9, SECTION 72-60-00, ITEM 4.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995071400136	19950714	00136	SW 	1995	7	14	95ZZZX3338 	1	19950525	G	6730	212076005703	MAIN SERVO 			BELL 	412 	412 	1182202	SW 										RT CYCLIC	LEAKING 	E				A				UNSCHED LANDING 				K			FLUID LOSS 			CR	CRUISE 	1			SW	03	3911L	3531 	1361 		7785	33023				PILOT REPORTED DROP IN NR 1 HYDRAULIC SYSTEM OIL PRESSURE. LANDED AT OFFSHORE HELIPORT WITHOUT INCIDENT. FOUND RT CYCL	IC SERVO LEAKING FLUID OUT OF TOP OF SERVO BETWEEN CAP AND PISTON. 412 IPC, FIGURE 67-2, ITEM 41.					1	G	7	2 	4U				H4SW 					 
1995071400137	19950714	00137	SW 	1995	7	14	95ZZZX3339 	1	19950514	G	7714	206075681115	DUAL TACHOMETER 			BELL 	206 	206B 	1181511	SW 										COCKPIT	ERRATIC 	B			TU3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	303PD				536	4319				DUAL TACHOMETER'S NEEDLES JUMPING.						1	G	7	1 	3U				H2SW 					 
1995071400138	19950714	00138	SW 	1995	7	14	95ZZZX3340 	1	19950602	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1075Y		409 			45378				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 408.6 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400139	19950714	00139	SW 	1995	7	14	95ZZZX3341 	1	19950602	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1075Y		409 			45378				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 408.6 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400140	19950714	00140	SW 	1995	7	14	95ZZZX3342 	1	19950613	G	6220	206010101129	YOKE 		206011100021	BELL 	206 	206B 	1181511	SW 										RADIUS RING BORE	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	115AL	5864 	1180 		A922	2383				SCHEDULED 1200 HOUR OVERHAUL FOUND M/R HUB HAS CORROSION IN RADIUS RING BORE BEYOND LIMITS OF .002 INCH PER BELL 206B-3 	CR & O MANUAL. SUSPECT CAUSED BY MOISTURE AND DISSIMILAR METAL CONTACT BETWEEN RADIUS RING AND YOKE BORE.					1	G	7	1 	3U				H2SW 					 
1995071400141	19950714	00141	SW 	1995	7	14	95ZZZX3343 	1	19950531	G	6320	204040353023	MAIN CASE 		204040353023	BELL 	212 	212 	1181420	SW 										XMSN INPUT QUILL	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	16785		1422 		A3394	30817				ON DISASSEMBLY FOR OVERHAUL, FOUND CRACK ABOVE INPUT QUILL IN CASE WEB. CAUSE: UNKNOWN. SUBMITTER STATED THIS HAS OCC	URRED ON THE BELL 212 MAIN TRANSMISSION CASE SEVERAL TIMES IN THE PAST.					1	G	7	1 	4U				H4SW 					 
1995071400142	19950714	00142	SW 	1995	7	14	95ZZZX3344 	1	19950615	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	173AL		401 			52066				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 400.9 HOURS,				1	G	7	1 	3U			NC	H2SW 					 
1995071400143	19950714	00143	SW 	1995	7	14	95ZZZX3345 	1	19950615	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	173AL		401 			52066				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 400.9 HOURS,				1	G	7	1 	3U			NC	H2SW 					 
1995071400144	19950714	00144	SW 	1995	7	14	95ZZZX3346 	1	19950531	G	5312	206032400027S	BULKHEAD 		206033004045	BELL 	206 	206L1 	1182107	SW 										FORWARD ON T/B	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2092U	7851 	150 		A0KP01145	45697				AFTER REMOVAL OF SHIMS TO COMPLY WITH TB 206L-94-169, CRACK WAS FOUND UNDER SHIM AT LEFT LOWER ATTACH POINT. APPARENTLY	, A STRESS CRACK CAUSED BY WORKING RIVETS IN INTERCOSTAL ASSEMBLY.					1	G	7	1 	3U				H2SW 					 
1995071400145	19950714	00145	SW 	1995	7	14	95ZZZX3347 	1	19950615	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2092U		634 			45697				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 634.3 HOURS,				1	G	7	1 	3U				H2SW 					 
1995092900002	19950929	00002	SW 	1995	9	29	95ZZZX3348 	1	19950601	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2092U		634 			45697				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 634.3 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400146	19950714	00146	SW 	1995	7	14	95ZZZX3349 	1	19950602	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27554		646 			45246				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 646.1 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400147	19950714	00147	SW 	1995	7	14	95ZZZX3350 	1	19950602	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27554		646 			45246				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 646.1 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400148	19950714	00148	SW 	1995	7	14	95ZZZX3351 	1	19950615	G	5312	206032400027	BULKHEAD 		206033004143	BELL 	206 	206L3 	1182108	SW 										FORWARD	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	346AL	5942 	150 			51378				AFTER REMOVAL OF SHIM TO COMPLY WITH TB 206L-94-169. FORWARD BULKHEAD FOUND CRACKED AT RT UPPER AND RT LOWER ATTACH FIT	TING AREAS. SUSPECT DUE TO STRESS FROM WORKING RIVETS IN INTERCOSTAL ASSEMBLY.					1	G	7	1 	3U				H2SW 					 
1995071400149	19950714	00149	SW 	1995	7	14	95ZZZX3352 	1	19950602	G	6510	206040325017	DRIVESHAFT 		206040325201	BELL 	206 	206L3 	1182108	SW 										NR 1 T/R	FLANGE WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	349AL	4786 			BT277	51388				DURING 4800 HOURS INSPECTION, FOUND TOTAL INDICATED RUN-OUT INSPECTION REVEALED SURFACE OF FLANGE TO BE .001 INCH BEYOND	 MANUFACTURER'S MAXIMUM LIMIT. CAUSE OF OCCURRENCE UNKNOWN.					1	G	7	1 	3U				H2SW 					 
1995071400150	19950714	00150	SW 	1995	7	14	95ZZZX3353 	1	19950613	G	6520	206340103101	SEAL 		206040402003	BELL 	206 	206L3 	1182108	SW 										T/R GEARBOX	LEAK 	B			ALGR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	362AL	40 				51471				TAIL ROTOR GEARBOX REMOVED FROM AIRCRAFT DUE TO LEAKING INPUT SEAL. SEAL MATERIALS APPEAR NORMAL. NO APPARENT DEFECTS.	 THIS IS A NEW-TYPE SEAL. THIS IS THE SECOND TIME THIS NEW-TYPE SEAL HAS LEAKED A SHORT TIME AFTER INSTALLATION.					1	G	7	1 	3U				H2SW 					 
1995071400151	19950714	00151	SW 	1995	7	14	95ZZZX3354 	1	19950615	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	343AL		494 			51372				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 494.1 HOURS.				1	G	7	1 	3U				H2SW 					 
1995071400152	19950714	00152	SW 	1995	7	14	95ZZZX3355 	1	19950615	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	343AL		494 			51372				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 494.1 HOURS.				1	G	7	1 	3U				H2SW 					 
1995071400153	19950714	00153	SW 	1995	7	14	95ZZZX3356 	1	19950615	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	355AL		444 			51444				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 443.7 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400154	19950714	00154	SW 	1995	7	14	95ZZZX3357 	1	19950615	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	355AL		444 			51444				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 443.7 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400155	19950714	00155	SW 	1995	7	14	95ZZZX3358 	1	19950602	G	6230	206010335001	LINK ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	348AL		407 			51386				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 407.0 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400156	19950714	00156	SW 	1995	7	14	95ZZZX3359 	1	19950602	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	348AL		407 			51386				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 407.0 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400157	19950714	00157	SW 	1995	7	14	95ZZZX3360 	1	19950607	G	6510	204040623003	BEARING 		212040600005	BELL 	412 	412 	1182202	SW 										DRV SHAFT HANGER	ROUGH 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	398AL	288 			ZV5812	33212				ON DISASSEMBLY FOR REPAIR OF SUSPECTED ROUGH BEARING, INSPECTED TAIL ROTOR HANGER ASSEMBLY AND FOUND BEARING ROUGH. BEA	RING IS UNSERVICEABLE.					1	G	7	2 	4U				H4SW 					 
1995071400159	19950714	00159	SW 	1995	7	14	95ZZZX3362 	1	19950531	G	5312	206032400027S	BULKHEAD 		206033004045	BELL 	206 	206L1 	1182107	SW 										FORWARD ON T/B	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57334	13276	135 		A0KP00960	45445				AFTER REMOVAL OF SHIMS TO COMPLY WITH TB 206L-94-169. FORWARD BULKHEAD WAS FOUND CRACKED UNDER SHIM AT LEFT LOWER ATTAC	H POINT. THIS IS PROBABLY A STRESS CRACK CAUSED BY WORKING RIVETS IN THE INTERCOSTAL ASSEMBLY.					1	G	7	1 	3U				H2SW 					 
1995071400160	19950714	00160	SW 	1995	7	14	95ZZZX3363 	1	19950615	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5740L		710 			45459				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 709.6 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400161	19950714	00161	SW 	1995	7	14	95ZZZX3364 	1	19950615	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5740L		710 			45459				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS 6605D64 BOLTS, AND 1 EACH 206-010-4	70-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 709.6 HOURS,				1	G	7	1 	3U				H2SW 					 
1995071400162	19950714	00162	SW 	1995	7	14	95ZZZX3365 	1	19950613	G	6230	206040576103	BEARING 		206040014103	BELL 	206 	206L3 	1182108	SW 										MAST ASSY	FAILED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5843	3882 			ZV1220	51467				ON TEAR-DOWN INSPECTION DURING 3,000 HOUR OVERHAUL, 2 BALLS FOUND WITH CUTS. FOUND UNSERVICEABLE IAW BHT 206 SERIES CR 	& O MANUAL, CHAPTER 63-00-00, PAGE 201, PARA 9.9B.					1	G	7	1 	3U				H2SW 					 
1995071400163	19950714	00163	NE 	1995	7	14	95ZZZX3366 	1	19950622	G	5313	7620403001112	LONGERON 			SKRSKY	S76 	S76A 	8143006	NE 										STA 215-300	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	741SW	9936 	1450 			760070				DISCOVERED DURING A/C REFURB, RT LOWER LONGERON WITH EXCESSIVE CORROSION. PARTS WERE CLEANED, TREATED, AND PRIMED WITH 	SUPER KOROPON AND REINSTALLED.					1	G	7	2 	3U				H1NE 					 
1995071400164	19950714	00164	NE 	1995	7	14	95ZZZX3367 	1	19950622	G	5313	7620203003102	LONGERON 			SKRSKY	S76 	S76A 	8143006	NE 										STA 215-300	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	741SW	9936 	1450 			760070				DISCOVERED DURING A/C REFURB, RT UPPER LONGERON, STA 215-300, CRACKED, PART UNSERVICEABLE.						1	G	7	2 	3U				H1NE 					 
1995071400165	19950714	00165	NE 	1995	7	14	95ZZZX3368 	1	19950622	G	5302	76209030020120	ATTACH FITTING 			SKRSKY	S76 	S76A 	8143006	NE 										T/B STA 300	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	741SW	9936 	1450 			760070				DISCOVERED DURING A/C REFURB, T/B ATTACH FITTING, STA 300, WITH EXCESSIVE CORROSION, PART UNSERVICEABLE.						1	G	7	2 	3U				H1NE 					 
1995071400166	19950714	00166	NE 	1995	7	14	95ZZZX3369 	1	19950622	G	5313	7620403001111	LONGERON 			SKRSKY	S76 	S76A 	8143006	NE 										STA 215-300	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	741SW	9936 	1450 			760070				DISCOVERED DURING A/C REFURB, LT LOWER LONGERON WITH EXCESSIVE CORROSION. PARTS WERE CLEANED, TREATED, AND PRIMED WITH 	SUPER KOROPON AND REINSTALLED.					1	G	7	2 	3U				H1NE 					 
1995071400167	19950714	00167	NE 	1995	7	14	95ZZZX3370 	1	19950622	G	5330		VERTICAL PYLON 			SKRSKY	S76 	S76A 	8143006	NE 										AFT FUSELAGE	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	741SW	9936 	1450 			760070				DISCOVERED DURING A/C REFURB, VERTICAL PYLON HAS EXCESSIVE CORROSION REQUIRING COMPLETE DISASSEMBLY OF PYLON ASSEMBLY. P	ARTS WERE CLEANED, TREATED, PRIMED WITH SUPER KOROPON PRIMER AND REASSEMBLED. NO MAJOR PARTS REQUIRED REPLACEMENT.					1	G	7	2 	3U				H1NE 					 
1995071400168	19950714	00168	NE 	1995	7	14	95ZZZX3371 	1	19950608	G	7120	7630907007053	MOUNT 			SKRSKY	S76 	S76A 	8143006	NE 										ENGINE DECK	CHAFED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	709AL		1500 			760278				DURING 1500 HOUR INSPECTION, FOUND ENGINE MOUNT CHAFED BEYOND LIMITS, DAMAGED WHEN RIVETS INSTALLED.						1	G	7	2 	3U				H1NE 					 
1995071400169	19950714	00169	NE 	1995	7	14	95ZZZX3372 	1	19950608	G	7120	7630907007053	MOUNT 			SKRSKY	S76 	S76A 	8143006	NE 										ENGINE DECK	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	709AL		1500 			760278				DURING 1500 HOUR INSPECTION, FOUND ENGINE MOUNT HAS A SMALL CRACK, NOT SERVICEABLE, DEFECTIVE WELD.						1	G	7	2 	3U				H1NE 					 
1995071400170	19950714	00170	GL 	1995	7	14	95ZZZX3373 	2	19950525	G	7250	23035262	ROLLER BEARING 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					COMPRESSOR NR 1	FAILED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	708AL	1965 	244 		MP00558	760277	CAE890775S			REPORTED LOUD GRINDING NOISE ON SHUT DOWN. COMPRESSOR WAS DISASSEMBLED DUE TO IMPELLER DRAGGING ON SHROUD AND FOUND NR 	1 ROLLER BEARING HAD FAILED. UPON DISASSEMBLY, FOUND SEPARATE CAGE FOR ROLLERS BROKEN. APPROXIMATELY 80 DEGREES OF SEP	ARATOR CAGE BROKEN OFF. FOUND 2 EACH ROLLERS AND PARTS FROM SEPARATOR CAGE LAYING ON TOP OF BEARING INSIDE OF NR 1 BEAR	ING HOUSING.			1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995072100505	19950721	00505	NE 	1995	7	21	95ZZZX3426 	2	19950516	G	7261		ENGINE 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					OIL SYSTEM	LOSING OIL 	E				A				UNSCHED LANDING 				K			FLUID LOSS 			CR	CRUISE 	1			SW	03	60951	1294 				2771	9281			AIRCRAFT DEPARTED LAND BASE FOR OFFSHORE LOCATION. ENGINE OIL PRESSURE LIGHT FLICKERED. RETURNED TO SHORE BASE AND LAN	DED WITHOUT INCIDENT. OIL PRESSURE HAD DROPPED TO ZERO UPON LANDING. FOUND ENGINE OIL TANK EMPTY. SIGNS OF OIL GOING 	OUT THE EXHAUST. AS-350 IPC, CHAPTER 71.10.11, ITEM 20B.				1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995072100506	19950721	00506	NM 	1995	7	21	95ZZZX3427 	1	19950621	G	2821	RHCAZ611	DRAIN VALVE 			ROBSIN	R22 	R22BETA 		NM 										GASCOLATOR	DETACHED 	A			S4HA	A				UNSCHED LANDING 				R	K		PARTIAL RPM/PWR LOSS 	FLUID LOSS 		CR	CRUISE 	1			SW	05	8141L	7774 				2413				DRAIN VALVE CAME OUT. AIRCRAFT WAS IN-FLIGHT. POWER LOSS WAS NOTED. PILOT LANDED SAFELY, NO DAMAGE TO PERSONS, AIRCCR	AFT, OR PROPERTY. SUBMITTER RECOMMENDS CURRENT VALVES BE RE-TORQUED AND TORQUE STRIPE. FUTURE VALVES TO BE DRILLED TO 	FACILITATE SAFETY WIRE.				1	G	7	1 	3O				H10WE 					 
1995072100508	19950721	00508	SO 	1995	7	21	95ZZZX3429 	1	19950623	G	3610	1159AC2005551	DUCT 			GULSTM	G1159 	G1159A 	3970109	SO 										TAIL COMPARTMENT	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	105Y	5736 				412				ON ROUTINE INSPECTION, FOUND APU DUCT CRACKED AT 'Y' JUNCTION. CRACK WAS APPROXIMATELY .50 INCH LONG AND HAD OPENED UP 	TO APPROXIMATELY .1532 INCH ALLOWING EXTREMELY HOT BLEED AIR FROM APU TO BLOW THROUGH INSULATION ON THE DUCT INTO THE TA	IL COMPARTMENT OF THE AIRCRAFT.				2	L	7	2 	4F				A12EA 					 
1995072100509	19950721	00509	CE 	1995	7	21	95ZZZX3430 	1	19950622	G	7120	66003093	MOUNT 			LEAR 	35 	35LEAR 	5170600	CE 										ENGINE	FAILED 	B	P		AN3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	2FOR		21 			243				ISOLATOR COMING APART AND ISOLATOR SAGGING IN MOUNT. FOUND DURING ENGINE CHANGE. MOUNT INSTALLED BY THIS REPAIR STATIO	N 21.0 HRS AGO.					2	L	7	2 	4F				A10CE 					 
1995072100510	19950721	00510	CE 	1995	7	21	95ZZZX3431 	1	19950607	G	2910	2307006207	TUBE 			LEAR 	25 	25D 	5170514	CE 										AUX HYD SYS	CRACKED 	G				O				OTHER 				K	J		FLUID LOSS 	WARNING INDICATION 		CR	CRUISE 	1			GL	25	725DM	3891 				328				WHILE ENROUTE FROM FOSTORIA, OH TO SALISBURY, MD, AIRCRAFT EXPEREINCED HYDRAULIC SYSTEM PRESSURE LOSS. AIRCRAFT DIVERTE	D TO TOLEDO, OH, LANDED WITHOUT FURTHER INCIDENT. AUXILIARY HYDRUALIC SYSTEM PRESSURE TUBE (PN 2307006-207) FOUND CRACK	ED AT FITTING LOCKING COLLAR. TUBE REPLACED WITH UPDATED PART/HOSE ASSY (PN 2307006-211).				2	L	7	2 	4J				A10CE 					 
1995072100511	19950721	00511	CE 	1995	7	21	95ZZZX3432 	1	19950615	G	2742	99140563	PITCH TRIM ACT 			CESSNA	650 	650 	2076802	CE 										HORIZ STAB	FAILED 	B			IW1R	O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			EA	25	118CD				222	6500118				REPAIRED UNIT FROM CRS-BS4R087M. REINSTALLED. 6-8-95 - TEST FLIGHT AT ALTITUDE FAILED. UNIT STILL GOING INOP AFTER CO	LD SOAKING. REINSTALLED RENTAL UNIT AND RETURNED SN 222 TO VENDOR 6-14-95. CONDITION CAUSE UNKNOWN AT THIS TIME. THIS	 OPERATOR - 135 CERTIFIED.				2	L	7	2 	4F				A9NM 					 
1995072800205	19950728	00205	EA 	1995	7	28	95ZZZX3458 	2	19950616	G	8520		CRANKCASE 			PIPER 	PA31 	PA31P 	7103120	SO 	LYC 	O541 	TIGO541E1A 	41539	EA 					NR 2-3 MAIN	BOLTS LOOSE 	B			EKIR	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			WP	07	252MA	2566 	25 			31P33	RL12762			ENGINE OVERHAULED 2-3-94. INSTALLED IN AIRCRAFT 4-1-94. AT 1,800 RPM CRUISE POWER, OIL PRESSURE AT 55 PSI, 190 DEGREES	, OIL TEMPERATURE, WHICH IS ON THE TOP OF YELLOW ARC, BOTTOM OF GREEN ARC, AT HIGHER OIL TEMP, OIL PRESSURE WOULD DROP I	NTO YELLOW ARC. REMOVED ENGINE TO DISASSEMBLE, FOUND SEVERAL CASE-THROUGH BOLTS NOT TORQUED. DISASSEMBLED, FOUND EVIDE	NCE OF NR 2 AND NR 3 MAIN BEARINGS WORKING. MEASURED, FOUND WITHIN LIMITS. REASSEMBLED WITH NEW BEARINGS, OPS CHECKED 	GOOD, OIL PRESSURE 63 PSI AT 1,800 190 DEGREES.		1	L	7	2 	3O	3	O		A8EA 	E19EA				 
1995072800206	19950728	00206	SO 	1995	7	28	95ZZZX3459 	1	19950620	G	3246	756665	WHEEL 	PARKERHANFIN		PIPER 	PA34 	PA34200T 	7103406	SO 										BEAD RIM	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	8377C	5271 			4090A	34760133				A 6 INCH CRACK WAS DISCOVERED ON THE LEFT MAIN GEAR OUTER WHEEL HALF WHERE THE TIRE BEAD RIDES. IT WAS DISCOVERED DURIN	G AN 100-HOUR INSPECTION.					1	L	7	2 	3O				A7SO 					 
1995072800207	19950728	00207	SO 	1995	7	28	95ZZZX3460 	1	19950623	G	3230	9603L	BUSHING 		126281 	GRUMAV	G21 	G21A 	3951204	SO 										RT MLG	WORN 	B			GFER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	67DF					1059				AFTER DEPRESSURIZATION OF THE RIGHT MLG SHOCK STRUT FOR SERVICE, EXCESSIVE FREEPLAY WAS NOTED AT THE UPPER AND LOWER DRA	G LINK BUSHINGS. WITH THE STRUT PRESSURIZED, THIS CONDITION WAS IMPOSSIBLE TO DETECT. REPLACEMENT OF THE BUSHINGS WAS 	ALL THAT WAS REQUIRED TO RETURN THE AIRCRAFT TO SERVICE. THE LEFT SIDE WAS UNAFFECTED. PERIODIC DEFLATION OF THE STRUT	S AND CAREFUL INSPECTION OF ATTACH HARDWARE WILL PREVENT FUTURE OCCURRENCES.			1	H	7	2 	3R				TC654 					 
1995072800208	19950728	00208	SO 	1995	7	28	95ZZZX3461 	1	19950623	G	3230	9602L	BUSHING 		126281 	GRUMAV	G21 	G21A 	3951204	SO 										RT MLG	WORN 	B			GFER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	67DF					1059				AFTER DEPRESSURIZATION OF THE RIGHT MLG SHOCK STRUT FOR SERVICE, EXCESSIVE FREEPLAY WAS NOTED AT THE UPPER AND LOWER DRA	G LINK BUSHINGS. WITH THE STRUT PRESSURIZED, THIS CONDITION WAS IMPOSSIBLE TO DETECT. REPLACEMENT OF THE BUSHINGS WAS 	ALL THAT WAS REQUIRED TO RETURN THE AIRCRAFT TO SERVICE. THE LEFT SIDE WAS UNAFFECTED. PERIODIC DEFLATION OF THE STRUT	S AND CAREFUL INSPECTION OF ATTACH HARDWARE WILL PREVENT FUTURE OCCURRENCES.			1	H	7	2 	3R				TC654 					 
1995072800209	19950728	00209	EA 	1995	7	28	95ZZZX3462 	2	19950615	G	8520		CRANKCASE 			PIPER 	PA36 	PA36285 	7103610	SO 	LYC 	O720 	IO720A1B 	41546	EA 					NR 1 CYL PAD	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	269JW	1700 				367560063	L137454A			WHILE ASSISTING THE OWNER/OPERATOR WITH A PREVENTIVE MAINTENANCE OPERATION, A CRACK WAS DISCOVERED ON THE FRONT SIDE OF 	THE NR 1 CYLINDER MOUNT PAD AREA. THE CRACK, ALTHOUGH CLEARLY VISIBLE, WAS CONFIRMED WITH DYE PENETRANT. THE CRACK DID	 NOT APPEAR TO BE LEAKING OIL. THE CAUSE IS UNKNOWN AT THIS TIME.				1	L	7	1 	3O	3	O		A10SO 	1E15				 
1995072800210	19950728	00210	CE 	1995	7	28	95ZZZX3463 	1	19950609	G	5712		RIB 			CESSNA	182 	R182 	2072734	CE 										RT FLAP TRACK	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	9292R	4187 				R18200681				CRACK NOTED IN INBOARD RT FLAP TRACK RIB IN LOWER CORNER WHERE RIB SECURES TO REAR SPAR WITH FOUR .1875 INCH FASTENERS. 	 UPON REMOVAL, DISCOVERED THE TWO .1875 FASTENERS WERE SHEARED WITH NO WAY OF DETECTING VISUALLY. FOUND .1250 INCH RIVE	T SECURING THE REINFORCEMENT ANGLES, SHEARED WITH BOTH ENDS STILL PRESENT. CHECKED OUTBOARD RIB AND FOUND 3 MORE RIVETS	 SHEARED, BUT BOTH ENDS PRESENT. FOUND BY TURNING AND PRYING TO CHECK FOR LOOSENESS.			1	H	7	1 	3O			RT	3A13 					 
1995072800211	19950728	00211	CE 	1995	7	28	95ZZZX3464 	1	19950608	G	2436	D4FF10316	REGULATOR 			CESSNA	172 	172M 	2072418	CE 										DC SYSTEM	FAILED 	G				K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			NM	01	80534	3844 				17266691				VOLTAGE REGULATOR FAILED AND OVERVOLTAGE CONDITION DAMAGED AVIONICS. AS VOLTAGE CLIMBED AND CIRCUIT (50A) BREAKER OPENE	D, AN ARC DEVELOPED WHICH MELTED THE BI-METAL ELEMENT TO .1250 INCH BACK FROM CONTACT CAUSING SMOKE IN COCKPIT. VERY HI	GH VOLTAGE IS REQUIRED TO DO THIS TYPE OF DAMAGE. PARTS NOT AVAILABLE UNTIL 9-30-95.				1	H	7	1 	3O			NT	3A12 					 
1995072800212	19950728	00212	CE 	1995	7	28	95ZZZX3465 	1	19950426	G	2140	3017	BLOWER MOTOR 	JANITROL 	B3040 	CESSNA	414 	414 	2075908	CE 										HEATER	SHORTED 	D				K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			NM	06	81JK	680 				4140027				COMBUSTION HEATER SWITCH TRIPPED WHEN PILOT ATTEMPTED TO TURN ON AIRCRAFT HEATER. PILOT RESET SWITCH AND HEATER OPERATE	D. PILOT NOTICED VOLTAGE METER PEGGED AND A HIGH RATE OF DISCHARGE FROM BATTERY. PILOT SMELLED ELECTRICAL BURNING SMEL	L AND TURNED OFF AIRCRAFT'S ELECTRICAL SYSTEM. INSPECTION REVEALED THE JANITROL HEATER COMBUSTION AIR BLOWER MOTOR HAD 	SHORTED TO GROUND INTERNALLY, AND CAUSED EXCESSIVE OVERHEATING AND FAILURE OF MOTOR.			1	L	7	2 	3O			RT	A7CE 					 
1995072800213	19950728	00213	CE 	1995	7	28	95ZZZX3466 	1	19950626	G	3230	50410015	BELLCRANK 			CESSNA	340 	340A 	2076405	CE 										LT MLG	BROKEN 	D	S			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	09	133CH	3000 				340A0272				LT MLG BELLCRANK BROKEN.						1	L	7	2 	3O				3A25 					 
1995072800214	19950728	00214	CE 	1995	7	28	95ZZZX3467 	1	19950622	G	3222	084120031	SHIM 			CESSNA	414 	414A 	2075907	CE 										NLG STRUT	DEFORMED 	H				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			WP	01	6604C					414A0030				NOSE STRUT ASSY FAILED TO EXTEND. STUCK WITH APPROXIMATELY 6 INCHES OF PISTON AREA SHOWING. STRUT ASSY WAS DISASSEMBLE	D AND INSPECTED FOR DAMAGE. SHIM WAS FOUND DEFORMED. IT IS BELIEVED THE SHIM BECAME WEDGED BETWEEN THE CHROME AREA OF 	THE PISTON AND BEARING ASSY, PN 084121101, STRUT ASSY WAS REPACKED, SHIM REPLACED, AND SERVICED IAW CESSNA SM.				1	L	7	2 	3O				A7CE 					 
1995072800216	19950728	00216	SW 	1995	7	28	95ZZZX3469 	1	19950622	G	7922	75944	VALVE 			BBAVIA	7 	7GCB 	2110130	SW 										THERMO BYPASS	LOOSE CRIMP NUT 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	5027J	2101 				117579				FOUND BAD THERMOSTAT VALVE DURING ANNUAL INSPECTION IN COMPLIANCE WITH SB 518C. NUT ON END OF VALVE WAS NOT CRIMPED COR	RECTLY AND THE THREADS WERE WORN FROM THE NUT MOVING. IT WAS READY TO COME APART.					1	H	7	1 	3O				A759 					 
1995072800217	19950728	00217	CE 	1995	7	28	95ZZZX3470 	1	19950601	G	8120	4066105	TURBOCHARGER 	AIRESRCH 		CESSNA	210 	T210N 	2073456	CE 	CONT 	O520 	TSIO520R 	17040	SO 					BEARINGS	FAILED 	B			BTSR	A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			GL	23	5244A	357 			TJR6449	21063324	517272			FOLLOWING DEPARTURE FROM AIRPORT WHILE IN A CRUISE CLIMB AT 8,500 FEET MSL, THE AIRCRAFT'S ENGINE LOST POWER, THEN SURGE	D. AN IMMEDIATE RETURN TO AIRPORT WAS MADE AND ON THE DESCENT, THE ENGINE WAS INTERMITTENTLY SURGING. MANIFOLD PRESSUR	E VARIATIONS FROM 18 INCHES UP TO 27 INCHES DURING POWER SURGES. PART OF THE TIME ENGINE WOULD RUN SMOOTHLY. LANDED WI	THOUT INCIDENT WITH SURGING POWER OUTPUT.			1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995072800218	19950728	00218	SO 	1995	7	28	95ZZZX3471 	2	19950626	G	8530		CYLINDER 			CESSNA	170 	170B 	2072306	CE 	CONT 	C145 	C1452 	17012	SO 					NR 3 EXHAUST	FAILED 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			AL	03	3143A		85 			25787				STUDENT PILOT REPORTED ENGINE RAN ROUGH ON RUN-UP. FOUND NR 3 EXHAUST VALVE STUCK OPEN. ALSO, FOUND INTAKE ROCKER ARM 	(WITH NO OIL ORIFICE) INSTALLED ONE EXHAUST SIDE - POSSIBLY CONTRIBUTING TO STUCK VALVE. SEE CONT SB M77-19. OTHER AIR	CRAFT HAVE BEEN FOUND WITH ROCKER ARMS INCORRECTLY INSTALLED, NOT UNUSUAL.				1	H	7	1 	3O	3	O		A799 	E253				 
1995072800219	19950728	00219	SO 	1995	7	28	95ZZZX3472 	1	19950628	G	7810		HEAT MUFF 			PIPER 	PA46 	PA46350P 		SO 										RT ENG EXHAUST	CRACKED 	B	S	A	LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	1225R					4622102				DURING AN INSPECTION, THE RIGHT TAILPIPE/HEAT MUFF ASSEMBLY WAS FOUND CRACKED AROUND CIRCUMFERENCE OF WELD. ALSO, THE M	UFF HAD WORN THROUGH THE FLANGE AND WAS NOT SEALING AGAINST TAILIPE. THIS IS PROBABLY CAUSED BY THE DESIGN OF THE TAILP	IPE SUPPORT. THE SUPPORT USES THIS MUFF WHICH SEEMS TO STRESS THE WELD, ETC. THIS CONDITION COULD ALLOW EXHAUST GAS, E	TC., IN ENGINE COMPARTMENT TO ENTER CABIN. SUPPORT NEEDS REDESIGNED.			1	L	7	1 	3O			RT	A25SO 					 
1995072800220	19950728	00220	SO 	1995	7	28	95ZZZX3473 	1	19950621	G	2434	643008	CASTING 	PRESTOLITE 	ALX9425GB 	PIPER 	PA34 	PA34200T 	7103406	SO 										ALTERNATOR	CRACKED 	B	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	5384F	1311 			924600020	347770013				FOUND FORWARD CASTING OF ALTERNATOR CRACKED ADJACENT TO MOUNTING FLANGE SUPPORT BRACE. SUBMITTER KNOWS OF OTHER INSTANC	ES OF CRACKS IN THIS AREA ON SAME MAKE AND MODEL ALTERNATORS. FRAME IS CRACKED FROM FORWARD TO AFT ENDS ALL THE WAY THR	OUGH.				1	L	7	2 	3O				A7SO 					 
1995072800221	19950728	00221	SO 	1995	7	28	95ZZZX3474 	2	19950620	G	8550		ADAPTER 			CESSNA	207 	T207A 	2073614	CE 	CONT 	O520 	TSIO520M 	17040	SO 					OIL PUMP	THREAD DAMAGE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	9629M	1394 				20700712	520424			DURING COMPLIANCE WITH SEB 92-1R1 (CESSNA). ADAPTER WAS REMOVED FROM PUMP HOUSING AND THREAD DAMAGE WAS EVIDENT. 3OX M	AGNIFICATION OF DAMAGE APPEARED TO BE A MANUFACTURING DEFECT. NO DAMAGE DUE TO MISUSE IS SUSPECTED. SEB 93-1R1 IS TO C	HECK THREAD DAMAGE DUE TO IMPROPER TORQUE AND SUBSEQUENT LOOSENESS. THIS CONDITION DID NOT EXIST AND SEB 93-1R1 DOES NO	T APPLY TO THIS AIRCRAFT BY SERIAL NUMBER, HOWEVER, ENGINE AND PART IN QUESTION ARE SAME AS SERIAL NUMBER AIRCRAFT IN EF	FECTIVITY CLAUSE.		1	H	7	1 	3O	3	O		A16CE 	E8CE				 
1995072800222	19950728	00222	SO 	1995	7	28	95ZZZX3475 	1	19950607	G	2701		YOKE 			PIPER 	PA28 	PA28161 	7102803	SO 										PILOT'S	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	8334Y	5913 				288116151				DURING 100-HOUR INSPECTION, NOTICED ALOT OF PLAY WAS IN PILOT'S SIDE YOKE. UPON INVESTIGATION, FOUND UNIVERSAL JOINT WA	S EXCESSIVELY WORN AND AILERON SPROCKET STOP PIN HAD CRACKED ALMOST COMPLETELY OFF. AIRCRAFT WAS REPAIRED WITH NEW PART	S.				1	L	7	1 	3O				2A13 					 
1995072800223	19950728	00223	CE 	1995	7	28	95ZZZX3476 	1	19950601	G	2434	DOFF10300B	ALTERNATOR 			CESSNA	172 	172 	2072402	CE 										CASE BOLT	FAILED 	D				K				NONE 				B	O		SMOKE/FUMES/ODORS/SPARKS 	OTHER 		IN	INSP/MAINT 	1			SW	17	739CD				9121087	17270429				INSTRUCTOR NOTED NOISE AND SMOKE FROM ALTERNATOR. UPON INSPECTION, ALL BOLTS AND SAFETY WIRES WERE IN PLACE. BELT LOOK	ED GOOD ALONG TOTAL SURFACE. BEFORE RUN-UP, DECIDED TO GRAB AND SHAKE IT, NOTICED FRONT HALF OF ALTERNATOR MOVING AWAY 	FROM REAR HALF. CASE BOLTS HAD BROKEN RIGHT AT FEMALE THREAD CONTACT. SAFETY WIRE HELD THEM IN PLACE, AND SEEMED TO BE	 GOOD AT VISUAL INSPECTION.			1	H	7	1 	3O			NT	3A12 					 
1995072800224	19950728	00224	CE 	1995	7	28	95ZZZX3477 	1	19950614	G	5511	04320016	RIB 			CESSNA	150 	152 	2071835	CE 										HORIZ STAB LE	CRACKED 	B			IKBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	350SU	7804 				15295152				HORIZONTAL STABILIZER LEADING EDGE INBOARD. RIBS ARE BEING FOUND WITH CRACKS OR BROKEN TABS. DEFECT IS PRIMARILY FOUND	 ON RT SIDE PROBABLY DUE TO ELEVATOR TRIM BEING ON THAT SIDE. THIS IS A HIGH TIME AIRCRAFT USED IN A TRAINING FLEET.					1	H	7	1 	3O			NT	3A19 					 
1995072800225	19950728	00225	CE 	1995	7	28	95ZZZX3478 	1	19950614	G	5511	043200146	RIB 			CESSNA	150 	152 	2071835	CE 										HORIZ STAB LE	CRACKED 	B			IKBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	350SU	7804 				15295152				HORIZONTAL STABILIZER LEADING EDGE INBOARD. RIBS ARE BEING FOUND WITH CRACKS OR BROKEN TABS. DEFECT IS PRIMARILY FOUND	 ON RT SIDE PROBABLY DUE TO ELEVATOR TRIM BEING ON THAT SIDE. THIS IS A HIGH TIME AIRCRAFT USED IN A TRAINING FLEET.					1	H	7	1 	3O			NT	3A19 					 
1995072800226	19950728	00226	SO 	1995	7	28	95ZZZX3479 	1	19950613	G	3242		LINE 			PIPER 	PA15 	PA15 	7101502	SO 										RT MASTER CYL	LEAKAGE 	D				K				NONE 				O			OTHER 			LD	LANDING 	1			AL	03	4492H					15280				AIRCRAFT CRASHED ON LANDING. UPON EXAMINATION, DETERMINED THE RIGHT BRAKE HOSE SWEDGE, METAL-TO-RUBBER, WAS LEAKING FLU	ID. THE MASTER CYLINDER WAS EMPTY OF FLUID (RIGHT). THE LEAKAGE WAS IN A PLACE BELOW THE FLOORBOARDS WHERE THE PILOT C	OULD NOT INSPECT DURING A PRE-FLIGHT INSPECTION.				1	H	7	1 	3O				A800 					 
1995072800227	19950728	00227	EA 	1995	7	28	95ZZZX3480 	2	19950606	G	7322	CF2541803	DIAPHRAGM STEM 	BENDIX 	RSA10ED1 						LYC 	O540 	IO540K1A5 	41532	EA 					FUEL SERVO	FAILED 	B			PB4R	A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			SO	13					59361					ENGINE FAILURE CAUSING FORCED LANDING. FUEL DIAPHRAGM STEM FAILED (PN CF2541803). BROKE AT BALL SWAGE AREA INTERRUPTIN	G FUEL FROM SERVO TO ENGINE.										3	O			1E4				 
1995072800228	19950728	00228	CE 	1995	7	28	95ZZZX3481 	1	19950705	G	2720	04310074	HORN 			CESSNA	150 	150 	2071802	CE 										RUDDER CONTROL	CRACKED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	19	22155					15068103				NEW PART FROM CESSNA PARTS DISTRIBUTOR. VISUAL INSPECTION REVEALED CRACKS, SUSPECT DUE TO IMPERFECTIONS IN FORGING AND 	DUE TO BENDING DURING MANUFACTURE. PART RETURNED TO PARTS SUPPLIER. SUGGEST BETTER QUALITY CONTROL DURING INSPECTION P	ROCESS FROM CESSNA.				1	H	7	1 	3O			NT	3A19 					 
1995072800229	19950728	00229	CE 	1995	7	28	95ZZZX3482 	1	19950620	G	7160	24500233	AIR BOX 			CESSNA	172 	172RG 	2072438	CE 										CARBURETOR AIR	CRACKED 	B	P		EN4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6530R	597 				172RG0199				DISCOVERED CRACK AROUND OUTER EDGE OF WELD OF CARBURETOR AIR INTAKE ELBOW TUBE TO CARBURETOR HEAT VALVE BODY, THROUGH 24	0 DEGREES ARC, DURING ANNUAL/100-HOUR VISUAL INSPECTION OF ENGINE. SUSPECT CAUSE IS POOR MANUFACTURING/WELDING TECHNIQU	ES. SUBMITTER RECOMMENDATION TO PREVENT RECURRENCE, CORRECT MANUFACTURING PROCESS.				1	H	7	1 	3O				3A17 					 
1995072800230	19950728	00230	CE 	1995	7	28	95ZZZX3483 	1	19950607	G	3230	AN386214A	TAPER PIN 			CESSNA	337 	337A 	2075704	CE 										LT MLG	SHEARED 	D	L	A		O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			EA	01	6384F	2487 				3370384				UPON SELECTING GEAR DOWN, THE LEFT MAIN GEAR DANGLED IN AN INTERMITTENT POSITION. ALL ATTEMPTS TO DOWN AND LOCK THE LEF	T GEAR WERE UNSUCCESSFUL. RT MAIN AND NOSE DOWN AND LOCKED NORMALLY. AIRCRAFT LANDED WITH RT MAIN AND NOSE GEAR DOWN. 	 DAMAGE TO BOTH LEFT MAIN GEAR DOORS, LEFT WING TIP AND LEFT VERTICAL STABILIZER BASE. INVESTIGATION REVEALED THE TWO T	APER PINS, WHICH ATTACHED THE LEFT GEAR UNIVERSAL JOINT TO THE GEAR ACTUATOR, SHEARED. SUSPECT ONE PIN PREVIOUSLY FRACT	URED AND THE SECOND SHEARED DUE TO INCREASED LOAD. NOTE: THAT EVEN AFTER FAILURE, EXTERNALLY, THE PINS APPEARED INTACT	 UNTIL PROBED WITH A PAIR OF PLIERS.	1	H	7	2 	3O				A6CE 					 
1995072800231	19950728	00231	CE 	1995	7	28	95ZZZX3484 	1	19950506	G	3230	2214	RETRACT NUT 			BEECH 	18 	E18S 	1151006	CE 										NLG	BOLT FAILED 	D	L			A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			GL	03	8711					BA384				THE AIRCRAFT RETURNED TO BASE AFTER TAKEOFF BECAUSE THE LANDING GEAR WOULD NOT RETRACT. THE PILOT REPORTED 3 GREEN DOWN	 AND LOCKED LIGHTS UPON LANDING. SHORTLY AFTER LANDING, THE NOSE GEAR COLLAPSED. INSPECTION SHOWED THE BOLTS THAT HOLD	 THE NOSE GEAR RETRACT NUT AND TUBE PUSH/PULL HAD FAILED.				1	L	7	2 	3R				A765 					 
1995072800232	19950728	00232	CE 	1995	7	28	95ZZZX3485 	1	19950506	G	3230	2212	PUSH/PULL TUBE 			BEECH 	18 	E18S 	1151006	CE 										NLG	BOLT FAILED 	D				A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			GL	03	8711					BA384				THE AIRCRAFT RETURNED TO BASE AFTER TAKEOFF BECAUSE THE LANDING GEAR WOULD NOT RETRACT. THE PILOT REPORTED 3 GREEN DOWN	 AND LOCKED LIGHTS UPON LANDING. SHORTLY AFTER LANDING, THE NOSE GEAR COLLAPSED. INSPECTION SHOWED THE BOLTS THAT HOLD	 THE NOSE GEAR RETRACT NUT AND TUBE PUSH/PULL HAD FAILED.				1	L	7	2 	3R				A765 					 
1995072800233	19950728	00233	NM 	1995	7	28	95ZZZX3486 	1	19950601	G	7120		MOUNT 			PIPER 	PA60 	PA60601P 	7106012	NM 										RT ENGINE	CORRODED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	700FP					61P068979633				DURING PERFORMANCE OF UNSCHEDULED MAINTENANCE, THE RIGHT\LEFT ENGINE MOUNT FRAME TUBING WAS FOUND SEVERELY CORRODED IN A	REAS COVERED BY HEAT PROTECTIVE SHIELDS. THE STAINLESS STEEL SHIELDS ARE LINED WITH A FIBROUS MATERIAL WHICH IS IN DIRE	CT CONTACT WITH THE TUBING. IT IS PRESSUMED THAT MOISTURE HAD ACCUMULATED IN THE COVERING CAUSING THE CORROSION. THIS 	INSTALLATION IS APPROVED UNDER STC SE978NW AND INSTALLED IN 1981. THERE IS NO KNOWN SPECIFIC REQUIREMENT TO REMOVE THE 	SHIELDS FOR PERIODIC INSPECTION.		1	M	7	2 	3O			RT	A17WE 					 
1995072800234	19950728	00234	NE 	1995	7	28	95ZZZX3487 	1	19950525	G	3231	24103021	TRUNNION 			CONAER	LA4 	LA4200 	5110310	NE 										LT/RT MLG	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	8001N	722 				995				ANNUAL INSPECTION REVEALED SEVERE CORROSION INSIDE OF THE MLG TRUNNION TUBES (THE LANDING GEAR PIVOT TUBES EXTENDING FRO	M THE GEAR LEG FORWARD INTO THE LEADING EDGE). THE TUBES WERE REMOVED AND REPLACED WITH NEW TUBES. THE OLD TUBES WERE 	CUT IN TWO AND THE DEPTH OF THE CORROSION WAS DETERMINED TO BE .042 INCH, APPROXIMATELY ONE-THIRD OF THE WAY THROUGH THE	 .120 INCH WALL THICKNESS OF THE TUBE. THE AIRCRAFT HAD A LONG HISTORY OF SALT WATER OPERATION.			1	H	7	1 	3O				1A13 					 
1995072800352	19950728	00352	NE 	1995	7	28	95ZZZX3488 	2	19950626	G	7414	SF14LN3	MAGNETO 	BENDIX 		DOUG 	DC3 	DC3 	3021401	WP 	PWA 	R1830 	R183092 	52020	NE 					RT ENG RT MAG	LOOSE 	D				E				ENGINE SHUTDOWN 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SW	11	24320				028394	20197	CP313794			RIGHT ENGINE STARTED RUNNING ROUGH IN-FLIGHT. ENGINE SHUT DOWN AND FEATHERED. FOUND RIGHT MAG HAS COME LOOSE. RE-TIME	D AND TORQUED RIGHT MAG. OPS CHECKED SATISFACTORY.					2	L	7	2 	4R	4	R		A669 	5E4				 
1995072800353	19950728	00353	CE 	1995	7	28	95ZZZX3489 	1	19950627	G	7120	04511141	MOUNT 			CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					CROSS BRACE	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	13552	4170 				17262844	L2015527A			FOUND ENGINE MOUNT CROSS BRACES CRACKED. SUBMITTER RECOMMENED CHECK AT 100 HOURS ANNUAL.						1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995072800354	19950728	00354	CE 	1995	7	28	95ZZZX3490 	1	19950601	G	7120	04511141	MOUNT 			CESSNA	172 	172M 	2072418	CE 										CROSS BRACE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	21690	6620 				17263987				FOUND ENGINE MOUNT CRACKED AT CROSS BRACES. RECOMMEND CHECK AT 100 HOURS AT ANNUALS.						1	H	7	1 	3O			NT	3A12 					 
1995072800355	19950728	00355	CE 	1995	7	28	95ZZZX3491 	1	19950601	G	7120	04511141	MOUNT 			CESSNA	172 	172C 	2072408	CE 										CROSS BRACE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	7698G	3114 				17259398				FOUND ENGINE MOUNT CRACKED AT CROSS BRACES. SUBMITTER RECOMMENDED CHECK AT 100 HOURS AND ANNUALS.						1	H	7	1 	3O			NT	3A12 					 
1995072800356	19950728	00356	SO 	1995	7	28	95ZZZX3492 	1	19950618	G	8120	07A19870	BRACKET 			PIPER 	PA46 	PA46350P 		SO 	LYC 	O540 	TIO540AE2A 	41532	EA 					LT TURBOMOUNT	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	61FL	1110 				4622037	L897161A			LEFT TURBOMOUNT BRACKET BROKE AT SUMP ATTACH POINT. THIS BRACKET SUPPORTS THE TURBOCHARGER.						1	L	7	1 	3O	3	O	RT	A25SO 	E14EA				 
1995072800357	19950728	00357	SO 	1995	7	28	95ZZZX3493 	1	19950622	G	3213	20829000	STUD 			PIPER 	PA24 	PA24250 	7102404	SO 										MLG STRUT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	5365P	2985 				24414				WHILE PERFORMING INSPECTION PER AD 77-13-21, FOUND STRUT STUD BENT AND CRACKED. BOTH WERE WORN BEYOND LIMITS. FOUND OT	HER SIDE TO HAVE THE LARGER STUD, BUSHINGS, AND MOUNTING CASTING AS USED ON THE LATER SINGLES. INSTALLED CORRECT PARTS.					1	L	7	1 	3O				1A15 					 
1995072800358	19950728	00358	EA 	1995	7	28	95ZZZX3494 	2	19950628	G	8530	15F1995736	PUSH ROD 								LYC 	O360 	IO360A3B6 	41514	EA 					ENGINE	CORRODED 	B			IBIR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	27										RECEIVED 3 EACH PUSH ROD ASSEMBLIES FROM DISTRIBUTOR. PUSH ROD ASSEMBLY HAS EXCESSIVE WEATHERING CORROSION AND PITTING 	ON THE OUTER SURFACE ON THE RODS. REFERENCED TO THE VENDOR FOR INSPECTION AND DISPATCH. ROD ASSEMBLIES WERE NOT PRESER	VED IN ANY TYPE OF ANTI-CORROSION PACKING.									3	O			1E10				 
1995072800359	19950728	00359	SO 	1995	7	28	95ZZZX3495 	1	19950615	G	3260		SWITCH 			PIPER 	PA31 	PA31350 	7103110	SO 										LT MLG	OUT OF RIG 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	4083L					318152095				LEFT GEAR HAD INDICATED UNSAFE AND GEAR HANDLE DID NOT RETURN TO NEUTRAL POSITION. TROUBLESHOT SYSTEM BY DOING PIPER TI	ME CHECKS, AND PRESSURE CHECKS ON GEAR SYSTEM. FOUND OKAY. ADJUSTED BOTH LEFT AND RIGHT DOWNLOCK SWITCHES IAW PIPER MM	. ALSO, COMPLETED SL 755C. GEAR SWING CHECK GOOD. RECOMMEND DOING SL 755C.				1	L	7	2 	3O				A20SO 					 
1995072800360	19950728	00360	SO 	1995	7	28	95ZZZX3496 	1	19950609	G	3222	67054003	TRUNNION 			PIPER 	PA32 	PA32RT300T 	7103216	SO 										NLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	2168A	1323 				32R7987010				FOUND TRUNNION CRACKED. SUSPECT NOSE GEAR TURNED TOO FAR. LOWER REAR CASTING CRACKED WHERE EXTENSION LINK ATTACHES.						1	L	7	1 	3O				A3SO 					 
1995072800361	19950728	00361		1995	7	28	95ZZZX3497 	4	19950412	G	2562	DMELT61	ELT 			CESSNA	150 	152 	2071835	CE 										CASE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	48340	7748 			34558	15283326				WHILE PERFORMING THE INSPECTION PER FAR91.207D, AN INSPECTION OF THE CASE REVEALED A CORRODED AREA AT THE END OF THE BAT	TERY SECTION. THIS CORROSION HAD EATEN ALMOST COMPLETELY THROUGH THE CASE.					1	H	7	1 	3O			NT	3A19 					 
1995072800362	19950728	00362		1995	7	28	95ZZZX3498 	4	19950412	G	2562	DMETL61	ELT 	DORNEMARGLN 		CESSNA	150 	152 	2071835	CE 										G-SWITCH	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	46043	4519 			30205	15282988				WHILE PERFORMING THE OPERATIONAL CHECK PER 91.207D, NO SIGNAL OUTPUT WAS NOTED EITHER BY USING THE G-SWITCH TEST OR IN M	ANUAL ACTIVATION.					1	H	7	1 	3O			NT	3A19 					 
1995072800363	19950728	00363		1995	7	28	95ZZZX3499 	4	19950714	G	2562	7H2132	ELT 	LEIGH 	SHARC7 															SENSOR	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07		1943 			19014					DURING A 100-HOUR INSPECTION, THE ELT WAS REMOVED FOR BATTERY CHANGE AND TESTING PER FAR 91.207(D). THE CRASH SENSOR FA	ILED TO OPERATE. WHEN TESTED PER FAR 91.207(D), UNABLE TO MAKE SENSOR WORK EVEN WITH SHARP BLOW TO A HARD SURFACE.																		 
1995072800364	19950728	00364	CE 	1995	7	28	95ZZZX3500 	1	19950701	G	5610	50420066317	WINDOW 			BEECH 	100 	A100 	1152915	CE 										PILOT	FAILED 	D		A		O				OTHER 				O			OTHER 			CR	CRUISE 	1			GL	09	711RE	7321 				B233				AIRCRAFT CRUISING AT 17,000 FEET. CABIN PRESSURIZED TO 4.4. PILOTS SIDE WINDOW BLEW OUT. AD 85-01-01 IS NOT APPLICABL	E PER AIRCRAFT SERIAL NUMBER.					1	L	7	2 	3T				A14CE 					 
1995072800365	19950728	00365	EU 	1995	7	28	95ZZZX3501 	1	19950403	G	5753		FLAP 			GROB 	G115 	G115C 	1660303	EU 										CONTROL ATTACH	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	216AR	108 				82013C				DURING REGULAR MAINTENANCE AND LUBRICATION OF THE FLAP CONTROL ROD ENDS, A CRACK WAS NOTICED IN THE FLAP ITSELF. THE CR	ACK IS AROUND THE BASE OF THE BRACKET FOR THE ROD END ATTACHMENT, THROUGH THE FLAPS SPAR. THERE IS NO SUPPORT ON THE BA	CK SIDE OF THE SPAR FOR THE 4 BOLTS THAT HOLD THE BRACKET IN PLACE. A BEEF-UP OF THIS AREA WILL BE NEEDED TO PRECLUDE T	HIS HAPPENING. SUSPECT CAUSE DUE TO EXTENSION OF FLAPS AT A HIGHER THAN NORMAL SPEED.			1	L	7	1 	3O			NT	A57EU 					 
1995072800366	19950728	00366	EU 	1995	7	28	95ZZZX3502 	1	19950403	G	7160		AIR BOX 			GROB 	G115 	G115C 	1660303	EU 										CARBURETOR	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	216AR	108 				82013C				THE CARBURETOR AIR BOX WAS FOUND CRACKED AT FORWARD UPPER AND LOWER CORNERS. THIS WAS FOUND WITH ONLY 95 FLIGHT HOURS O	N THE AIRFRAME. THESE CRACKS WERE STOP DRILLED AND A NEW BOX PUT ON ORDER. SINCE THIS TIME, THE PLANE HAS ANOTHER 68 H	OURS. THE HEAT VALVE SHAFT END BEARINGS ARE NOW LOOSE DUE TO SHEARED RIVETS. THE BOX IS TIGHTLY FITTED TO THE COWL AND	 HAS BEEN RUBBING. CAUSE OF THE LOOSE END BEARINGS IS UNKNOWN. INSUFFICIENT CLEARANCE HAS BEEN PROVIDED FOR THE ALTERN	ATOR AS WELL. THE HEAT FROM THE EXHAUST HAS ALSO ALREADY STARTED TO DELAMINATE THE COWL AND SKINS.		1	L	7	1 	3O			NT	A57EU 					 
1995072800367	19950728	00367	SO 	1995	7	28	95ZZZX3503 	1	19950607	G	3230	20846000	BUNGEE ARM 			PIPER 	PA24 	PA24250 	7102404	SO 										RETAIN PIN	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	6903P					242037				FOUND BUNGEE ARMS CRACKED IN RADIUS FOR RETAINING PIN UPON REMOVAL. THIS WAS THE THIN WALL AREA.						1	L	7	1 	3O				1A15 					 
1995072800368	19950728	00368	SO 	1995	7	28	95ZZZX3504 	2	19950524	G	8530	630046	PISTON PIN 			BEECH 	58 	58 	1152740	CE 	CONT 	O550 	IO550C 		SO 					NR 5 CYLINDER	FRACTURED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	91WM	1314 				TH1396	676056H			WHEN REMOVING NR 2 AND NR 5 CYLINDERS TO CORRECT LOW COMPRESSION (LEAKING PAST RINGS), BOTH PISTON PINS WERE FOUND BROKE	N IN TWO.					1	L	7	2 	3O	3	O		3A16 	E3SO				 
1995072800369	19950728	00369	SO 	1995	7	28	95ZZZX3505 	2	19950524	G	8530	630046	PISTON PIN 			BEECH 	58 	58 	1152740	CE 	CONT 	O550 	IO550C 		SO 					NR 2 CYLINDER	FRACTURED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	91WM	1314 				TH1396	676056H			WHEN REMOVING NR 2 AND NR 5 CYLINDERS TO CORRECT LOW COMPRESSION (LEAKING PAST RINGS), BOTH PISTON PINS WERE FOUND BROKE	N IN TWO.					1	L	7	2 	3O	3	O		3A16 	E3SO				 
1995072800370	19950728	00370	SO 	1995	7	28	95ZZZX3506 	1	19950518	G	2810	3360500	FUEL CELL 			PIPER 	PA23 	PA23250 	7102308	SO 										LT INBD	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	54MV	3100 				277654043				DURING ROUTINE PRE-FLIGHT, FUEL TANK SUMP TESTING AND WATER IN AMOUNTS OF 3 OUNCES OR MORE WOULD BE FOUND. FUEL CAP O-R	INGS WERE INSPECTED AND FOUND SATISFACTORY. TOP OF FUEL CELL/ACCESS COVER WAS REMOVED ON LEFT INBOARD CELL. WATER IN T	HE AMOUNT OF 3 CUPS WAS FOUND TRAPPED IN WRINKLES AND AGAINST ZIPPERED IN BAFFLE JUST BELOW SWING CHECK VALVE. REMOVAL 	OF COVER AND SWABBING IS ONLY WAY TO REMOVE WATER.			1	L	7	2 	3O				1A10 					 
1995072800371	19950728	00371	CE 	1995	7	28	95ZZZX3507 	1	19950511	G	2434	DOFF10300B	ALTERNATOR 	FORD 		CESSNA	150 	152 	2071835	CE 										ENGINE	FAILED 	D				O				OTHER 				H			ELECT. POWER LOSS-50 PC 			NR	NOT REPORTED 	1			GL	17	6598B				2574	15283957				ALTERNATOR FAILED IN-FLIGHT. LANDED AND REPLACED. NO OBVIOUS DAMAGE.						1	H	7	1 	3O			NT	3A19 					 
1995072800372	19950728	00372	SO 	1995	7	28	95ZZZX3508 	2	19950711	G	8530	SA6291171	ROTOR COIL 								CONT 	O470 	O470* 	17026	SO 					NR 6 CYL EXH	FAILED 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11		34 					462596			SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 6 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION.											3	O			E273				 
1995072800373	19950728	00373	SO 	1995	7	28	95ZZZX3509 	2	19950711	G	8530	SA6291171	ROTOR COIL 								CONT 	O470 	O470* 	17026	SO 					NR 2 CYL EXH	FAILED 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11		34 					462596			SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 2 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION.											3	O			E273				 
1995072800374	19950728	00374	EA 	1995	7	28	95ZZZX3510 	2	19950612	G	7310	6390107	HOSE ASSY 			PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E2A 	41508	EA 					ENGINE CARB	BROKE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	43224	3207 				287425346				AT ANNUAL, NOTED ENGINE HOSES DATED 1974. UPON REMOVAL OF FUEL PRESSURE LINE FOR REPLACEMENT, FLEX HOSE BROKE NEAR SOCK	ET. HOSE WAS VERY BRITTLE AND INNER LINER WAS CRACKED. SUBMITTER RECOMMENDED AD TO ESTABLISH LIFE LIMIT ON FLEXIBLE HO	SES AT 5 YEARS OR ENGINE OVERHAUL, WHICHEVER COMES FIRST.				1	L	7	1 	3O	3	O		2A13 	E274				 
1995072800375	19950728	00375	SO 	1995	7	28	95ZZZX3511 	1	19950612	G	2701	7927600	WHEEL ASSY 			PIPER 	PA28 	PA28140 	7102802	SO 										LT CONTROL	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	43224	3207 				287425346				DURING ANNUAL INSPECTION, NOTED LEFT CONTROL WHEEL LOOSE ON SHAFT. IT APPEARS THE RETAINING PIN BECAME LOOSE ALLOWING T	HE CONTROL WHEEL TO MOVE ON THE SHAFT WHICH PROGRESSIVELY ENLARGED THE HOLE IN THE CONTROL WHEEL WHERE THE SHAFT IS INSE	RTED.				1	L	7	1 	3O				2A13 					 
1995072800376	19950728	00376	SO 	1995	7	28	95ZZZX3512 	1	19950612	G	3242	09102300	CYLINDER ASSY 	PARKERHANFIN		PIPER 	PA28 	PA28140 	7102802	SO 										LT MLG BRAKE	CORRODED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	09	4210J	2689 				2822556				DURING ANNUAL INSPECTION, NOTED WHEEL CYLINDER LEAKING FLUID. UPON DISASSEMBLY, FOUND SEVERE CORROSION IN CYLINDER BORE	 AND SEVERE PITTING CORROSION ON COMPLETE CYLINDER. SUGGEST CLOSE ATTENTION TO INSPECTION OF EXPOSED COMPONENTS.					1	L	7	1 	3O				2A13 					 
1995072800377	19950728	00377	SO 	1995	7	28	95ZZZX3513 	1	19950612	G	2820	6390115	HOSE ASSY 			PIPER 	PA28 	PA28140 	7102802	SO 										LT TANK	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	4643R	1802 				2821397				DURING ANNUAL INSPECTION, NOTED CORROSION ON FUEL LINE AT LEFT FUEL TANK. CORROSION WAS BETWEEN HOSE AND ALUMINUM SOCKE	T. HOSE WAS DATED 2Q67 (ORIGINAL). UPON HOSE DISASSEMBLY, SOCKET WAS FOUND CORRODED 75 PERCENT OF ITS THICKNESS. SUBM	ITTER SUGGESTS DUE TO FREQUENCY OF OLD, DETERIORATED HOSES BEING FOUND ON DIFFERENT AIRCRAFT, RECOMMEND AD TO LIMIT TIME	 IN SERVICE ON FLEXIBLE HOSES ON ALL AIRCRAFT OF 5 YEARS OR ENGINE OVERHAUL, WHICHEVER COMES FIRST.			1	L	7	1 	3O				2A13 					 
1995072800378	19950728	00378	CE 	1995	7	28	95ZZZX3514 	1	19950713	G	7603	S122219	CONTROL CABLE 	FACET 	MA4SPA 	CESSNA	177 	177 	2073704	CE 										THROTTLE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	2942X	1413 			A1212310	17700342				DURING A SCHEDULED INSPECTION, FOUND THROTTLE CABLE BENT AND CRACKED AT THE BEND LOCATED AT THE THREADED END WHERE THE R	OD END ATTACHES TO THE CABLE. IT APPEARED WHEN THE THROTTLE HIT ITS STOP, THE THROTTLE CABLE CONTINUED TO BE PUSHED. T	HE CABLE HAD TO BE REPLACED WHICH IS VERY COSTLY.				1	H	7	1 	3O			NT	A13CE 					 
1995072800379	19950728	00379	CE 	1995	7	28	95ZZZX3515 	1	19950701	G	3260	S13771	SWITCH 			CESSNA	210 	T210L 	2073449	CE 										RT MLG DOWNLOCK	FAILED 	D				O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			EA	25	15US					21060676				UPON SELECTING GEAR DOWN, COULD NOT GET GREEN INDICATION FOR DOWN AND LOCKED AND PUMP CONTINUED TO RUN. UPON LANDING, G	REEN LIGHT CAME ON. FOUND BAD SWITCH ON RT GEAR DOWNLOCK.					1	H	7	1 	3O				3A21 					 
1995072800380	19950728	00380	SO 	1995	7	28	95ZZZX3516 	2	19950711	G	8530	SA6291171	ROTOR COIL 								CONT 	O520 	IO520BA 	17032	SO 					NR 3 CYL EXH	BROKEN 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11		560 					232563R			SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 3 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION.											3	O			E5CE				 
1995072800381	19950728	00381	SO 	1995	7	28	95ZZZX3517 	2	19950711	G	8530	SA6291171	ROTOR COIL 								CONT 	O470 	O470* 	17026	SO 					NR 3 CYL EXH	FAILED 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11		34 					462596			SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 3 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION.											3	O			E273				 
1995072800382	19950728	00382	SO 	1995	7	28	95ZZZX3518 	2	19950711	G	8530	SA6291171	ROTOR COIL 								CONT 	O520 	IO520BA 	17032	SO 					NR 5 CYL EXH	BROKEN 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11		560 					232563R			SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 5 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION.											3	O			E5CE				 
1995072800383	19950728	00383	SO 	1995	7	28	95ZZZX3519 	1	19950511	G	3230		DOWNLOCK 			PIPER 	PA34 	PA34200T 	7103406	SO 										NLG	LINK BROKE 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			GL	09	209RR					347870267				DOWNLOCK BROKE ON LANDING, RESULTING IN COLLAPSE OF NOSE GEAR. INCIDENT OCCURRED DURING CROSSWIND CONDITION, SUSPECT HA	RDER THAN NORMAL LANDING. POSSIBLY, MORE OVERCENTER TRAVEL IN THE KNEE JOINT WOULD CAUSE SOME PRESSURE ON THE LINK.					1	L	7	2 	3O				A7SO 					 
1995072800386	19950728	00386	CE 	1995	7	28	95ZZZX3522 	1	19950710	G	3221	12134251	BRACE FITTING 			CESSNA	210 	210 	2073402	CE 										NLG DRAG	PULLED 	B			FE4R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			AL	03	9525X	2256 				21057825				RIVETS HOLDING NOSE GEAR DRAG BRACE FITTING IN PLACE WORKED LOOSE OVER YEARS OF OPERATION CAUSING FITTING TO PULL LOOSE 	FROM AIRCRAFT STRUCTURE. THIS, IN TURN, CAUSED NOSE GEAR TO RETRACT ON GROUND. SUBMITTER SUGGESTS THE ABOVE DESCRIBED 	AREA NEEDS CLOSE INSPECTION AT 100-HOUR ANNUAL INSPECTIONS.				1	H	7	1 	3O			RT	3A21 					 
1995072800387	19950728	00387	SO 	1995	7	28	95ZZZX3523 	1	19950619	G	2810	3140	FUEL TANK 			PIPER 	PA18 	PA18 	7101802	SO 										RT TANK TOP FWD	DAMAGED 	B			OAER	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			AL	03					388					TOP FORWARD INBOARD CORNER BASHED IN CAUSING A SEAM TO LEAK. ALSO, FOUND LARGE WELD AROUND VENT. THIS WAS CUT OUT AND 	A NEW VENT INSTALLED. PRESSURE TESTED AT 1 PSI - OK.					1	H	7	1 	3O				1A2 					 
1995072800388	19950728	00388	SO 	1995	7	28	95ZZZX3524 	2	19950525	G	8530	639272A1	CYLINDER 			CESSNA	206 	P206D 	2073338	CE 	CONT 	O520 	IO520A 	17032	SO 					NR 5	HEAD SEPARATED 	D				A				UNSCHED LANDING 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	CR	CRUISE 	1			AL	03	8735Z		818 			P2060535	1112534R			PILOT REPORTED A LOUD 'BANG' AND IMMEDIATE ROUGH RUNNING ENGINE 10 MILES OUT FROM LANDING. AIRPORT AND LANDING WERE MAD	E WITHOUT INCIDENT. INSPECTION FOUND NR 5 CYLINDER HEAD HAD SEPARATED FROM CYLINDER BARREL. ANNUAL INSPECTION HAD BEEN	 COMPLETED 11 HOURS PRIOR AND NR 5 COMPRESSION WAS 72/80 WITH NO EVIDENCE OF CRACKS. ENGINE WAS A TCM FACTORY OVERHAUL 	WITH 818 HOURS TSMOH. NOTE: AD 86-13-04 DID NOT APPLY.			1	H	7	1 	3O	3	O		A4CE 	E5CE				 
1995072800389	19950728	00389	CE 	1995	7	28	95ZZZX3525 	1	19950701	G	5540		POST 			BEECH 	55 	95B55 	1152706	CE 										RUDDER	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	3811X	1370 				TC2368				RUDDER POST REMOVED FOR INTERNAL RUST AND LOOSE FITTING TO BELLCRANK. BOLTS LOOSE CAUSING ELONGATION OR HOLES IN RUDDER	 POST. RUST INTERNALLY IS STRANGE BECAUSE PLANE HAS ALWAYS BEEN HANGARED.					1	L	7	2 	3O				3A16 					 
1995072800390	19950728	00390	SO 	1995	7	28	95ZZZX3526 	2	19950524	G	8550	CH48108	OIL FILTER 			BEECH 	58 	58 	1152740	CE 	CONT 	O550 	IO550C 		SO 					SEAL	DEFECTIVE 	D	S			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	01	91WM	65 			F11D301	TH1396	676056H			RUBBER SEAL FOUND PROTRUDING FROM CENTER HOLE WHEN FILTER WAS REMOVED:						1	L	7	2 	3O	3	O		3A16 	E3SO				 
1995072800391	19950728	00391	CE 	1995	7	28	95ZZZX3527 	1	19950527	G	3244	110012	TIRE 	GOODYEARAERO		BEECH 	18 	E18S 	1151006	CE 										MLG	CAP FAILED 	D				A				UNSCHED LANDING 				O			OTHER 			TO	TAKEOFF 	1			WP	05	202GW		306 		90270405	BA321				ON TAKEOFF ROLL, A THUMP WAS HEARD ACCOMPANIED BY BUMPING. PILOT IMMEDIATELY LIFTED OFF. PILOT FLEW AROUND FOR ABOUT 3	 HOURS TO BURN OFF FUEL AND THEN RETURNED. AFTER UNEVENTFUL LANDING (TIRE STILL HOLDING PRESSURE), FOUND CENTER SECTION	 OF RETREAD CAP HAD PEALED OFF. THE ORIGINAL RUBBER UNDERNEATH WAS SMOOTHER THAN THAT ALONG SIDES AS THOUGH IT WAS NOT 	SCUFFED ENOUGH SINCE ITS INSTALLATION. ONE PILOT REPORTED THE TIRE AS VERY OUT OF BALANCE ON MULTIPLE OCCASIONS.			1	L	7	2 	3R				A765 					 
1995072800392	19950728	00392	EA 	1995	7	28	95ZZZX3528 	2	19950705	G	7322		PUMP 	BENDIX 		PIPER 	PA24 	PA24260 	7102406	SO 	LYC 	O540 	IO540D4A5 	41532	EA 					INJ PUMP	DAUBER FOD 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	9155P					244641				ON 100-HOUR INSPECTION, DISCOVERED LARGE MUDDAUBERS' NESTS IN THE INLET TO THE FUEL INJECTION PUMP. THIS WEBCO KIT WAS 	INSTALLED IN RESPONSE TO AN AD NOTE FOR AN ALTERNATE ENGINE INLET AIR SOURCE. (CARBURETOR HEAT BOX TYPE DEVICE). THIS 	AREA IS AFTER THE AIR INTAKE FILTER AND CANNOT BE DISCOVERED ON PRE-FLIGHT.				1	L	7	1 	3O	3	O		1A15 	1E4				 
1995072800393	19950728	00393	CE 	1995	7	28	95ZZZX3529 	1	19950614	G	2410	632018	DRIVE GEAR 	DELCO 	632590 	BEECH 	55 	D55 	1152730	CE 										ALTERNATOR	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	7503N	1300 			110072355A	TE680				FOUND ALTERNATOR HUB ASSEMBLY AND ALTERNATOR DRIVE GEAR BROKEN, CAUSE UNKNOWN.						1	L	7	2 	3O				3A16 					 
1995072800394	19950728	00394	CE 	1995	7	28	95ZZZX3530 	1	19950414	G	3246	10D26841	ARM 	FLUIDYNE 	3200 	CESSNA	185 	185F 	2072820	CE 										SKI	FAILED 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			EA	27	205NR				G127L	18503910				ON LANDING, LEFT SKI ARM FITTING FAILED. UPPER BUSHING WELD FAILED CAUSING ARM TO SEPARATE IN TWO, SKI FOLDED UP UNDER 	AIRCRAFT ON LANDING HELD ONLY BY SAFETY CABLES. AIRCRAFT GROUND LOOPED CAUSING EXTENSIVE DAMAGE TO RIGHT WING, HORIZONT	AL STABILIZER.				1	H	7	1 	3O				3A24 					 
1995072800395	19950728	00395	SO 	1995	7	28	95ZZZX3531 	1	19950726	G	3230	20829000	SWIVEL STUD 			PIPER 	PA24 	PA24250 	7102404	SO 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	5365P	2985 				24414				DYE PENETRANT INSPECTED AT ANNUAL DUE TO QUESTIONS BY FAA AND OTHERS ON THESE PARTS. FOUND 1 CRACKED, OTHER WORN.						1	L	7	1 	3O				1A15 					 
1995072800396	19950728	00396		1995	7	28	95ZZZX3532 	4	19950120	G	2211	CE2150H16FF22	COMPUTER 	CENTURY 	C2000 	MOONEY	M20 	M20J 	5870219	SW 										AUTOPILOT	MALFUNCTIONED 	B			JW5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	210WE				2K9545	293352				AUTOPILOT CLIMBS IN ALTITUDE HOLD WHEN TRANSMITTING ON LOWER FREQUENCY BAND ON BOTH COMMS. CHECKED COMPUTER FOR SL CSL9	5-02. IT WAS INSTALLED. NOTIFIED FACTORY FOR CORRECTIVE ACTION.					1	L	7	1 	3O				2A3 					 
1995072800397	19950728	00397	SO 	1995	7	28	95ZZZX3533 	1	19950515	G	3246	153003	GREASE SEAL 	PARKERHANFIN	40120 	PIPER 	PA32 	PA32RT300 	7103215	SO 											WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	23	222PP					32R7985013				GREASE SEAL PN 153003 WILL NOT ALLOW AXLE SPACER TO PASS THROUGH ON TO BEARING. ASSEMBLY AS IS CAUSES SHIM TO CUT THROU	GH GREASE SEAL AND DOES NOT ALLOW CORRECT PRESSURE ON BEARING. PN 153-004 WOULD BE CORRECT.					1	L	7	1 	3O				A3SO 					 
1995072800398	19950728	00398	CE 	1995	7	28	95ZZZX3534 	1	19950711	G	2730	NAS314027	CONTROL CABLE 			CESSNA	305 	305A 	2074002	CE 										ELEVATOR	FAILED 	H		A		A				UNSCHED LANDING 				O			OTHER 			NR	NOT REPORTED 	1			NE	05	5204G	19110			1374	22496				THE ELEVATOR CABLE FAILED AT THE BULKHEAD PULLEY AT STA 110, BEHIND REAR SEAT DUE TO CABLE WEAR AND POSSIBLE PULLEY BIND	ING. CHECK OF SIMILAR AIRCRAFT SHOWED SAME PROBLEM IN 5 OUT OF 6 INSPECTED. IN-FLIGHT FAILURE RESULTED IN DESTROYED AI	RCRAFT. PILOT RECEIVED MINOR INJURY. CORRECTIVE ACTION: INSPECT, REMOVE AND REPLACE AS NEEDED/REQUIRED.				1	H	7	1 	3O			 	5A5 					 
1995072800399	19950728	00399	CE 	1995	7	28	95ZZZX3535 	1	19950711	G	2730	NAS314027	CONTROL CABLE 			CESSNA	305 	305A 	2074002	CE 										ELEVATOR	FAILED 	H				A				UNSCHED LANDING 				O			OTHER 			NR	NOT REPORTED 	1			NE	05	5204G	19110			1933	22496				THE ELEVATOR CABLE FAILED AT THE BULKHEAD PULLEY AT STA 110, BEHIND REAR SEAT DUE TO CABLE WEAR AND POSSIBLE PULLEY BIND	ING. CHECK OF SIMILAR AIRCRAFT SHOWED SAME PROBLEM IN 5 OUT OF 6 INSPECTED. IN-FLIGHT FAILURE RESULTED IN DESTROYED AI	RCRAFT. PILOT RECEIVED MINOR INJURY. CORRECTIVE ACTION: INSPECT, REMOVE AND REPLACE AS NEEDED/REQUIRED.				1	H	7	1 	3O			 	5A5 					 
1995072800400	19950728	00400	CE 	1995	7	28	95ZZZX3536 	1	19950605	G	5523		TRIM TAB 			CESSNA	210 	P210N 	2073454	CE 										RT ELEVATOR	EXCESS CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	6504P	3402 				P21000183				TRIM TAB BADLY CORRODED. TAB FILLED WITH FOAM, HOLDS WATER, AND CORRODES. BAD DESIGN, BUT CESSNA STILL HAS SAME TRIM T	AB.					1	H	7	1 	3O				3A21 					 
1995080400519	19950804	00519	NE 	1995	8	4	95ZZZX3566 	1	19950621	G	3230	1945F302	CYLINDER 		1945G200 	SKRSKY	S76 	S76A 	8143006	NE 										MLG RETRACT	CRACKED 	B		A	B8FR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	25		6290 			CPC0662JK					CHEVON USA CONTACTED BFG THAT THEY FOUND A CRACK IN A RETRACT ACTUATOR CYLINDER, OUTSIDE DIAMETER. THIS WAS FOUND BY HY	DRAULIC FLUID LEAK AND VERIFIED BY FL. PENETRANT INSPECTION. PART WAS REQUESTED AND CHEVRON COMPLIED. REF: PART HAS A	 LIMITED LIFE AND WOULD HAVE BEEN RETIRED AT 7,110.0 HRS. EVALUATION CONCLUDED A PURE FATIGUE FAILURE, NO MFG'S DEFECTS	.			1	G	7	2 	3U				H1NE 					 
1995080400520	19950804	00520	SW 	1995	8	4	95ZZZX3567 	1	19950622	G	2730		BOLT 			SWRNGN	SA26 	SA26AT 	8780112	SW 										RT ELEVATOR	CORRODED 	B			GFER	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	09	124PS					T26135				DURING FLIGHT CONTROL REMOVAL IN PREPARATION FOR PAINT, A LOOSE BOLT WAS DISCOVERED AT THE RT OUTBOARD ELEVATOR ATTACH P	OINT. INVESTIGATION REVEALED IN ADDITON TO BEING SEVERELY CORRODED, THE BOLT WAS THE WRONG LENGTH, THE WRONG P/N, AND T	HE NUT USED TO RETAIN THE BOLT WAS TOO LARGE AND WAS HELD ON ONLY BY THE REMNANT OF A COTTER PIN. THIS INSTALLATION HAS	 EVIDENTLY BEEN IN SERVICE FOR A LONG PERIOD OF TIME.			1	L	7	2 	4T				A5SW 					 
1995080400521	19950804	00521		1995	8	4	95ZZZX3568 	4	19950428	G	6122	8210212D	GOVERNOR 	WOODWARD 		BEECH 	300 	300BEECH 	1152930	CE 										MOUNT BASE	MISOVERHAULED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	09	100Y				2328410	FA68				RECEIVED A ZERO TIME SINCE OVERHAUL PROP GOVERNOR FROM PRATT & WHTINEY. FOUND GOVERNOR MOUNT BASE WARPED, SO GOVERNOR W	OULD NOT SEAT. ALSO, FOUND SPINDLE MOVEMENT ROUGH, SENT BACK TO PRATT & WHITNEY.					2	L	7	2 	4T				A24CE 					 
1995080400522	19950804	00522	EU 	1995	8	4	95ZZZX3569 	1	19950620	G	5520	25TE243A	HINGE ASSY 		267TE1A 	BRAERO	DH125 	HS125700A 	4230170	EU 										LT ELEVATOR	BEARING LOOSE 	D		A		K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			SW	99	369G				DHB249	NA0289				PILOT REPORTED HE FELT RESTRICTION IN ELEVATOR CONTROLS UPON LANDING. RESTRICTION COULD BE FELT ON THE GROUND AT APPROX	 ONE-THIRD AND TWO-THIRDS TRAVEL. ON EXAMINATION, LEFT ELEVATOR INBD BEARING RETAINING RING (P/N AGIY) FOUND LAYING IN	 BULLET FAIRING. THIS ALLOWED BEARING AND ELEVATOR TO MOVE APPROX .50 INCH INBOARD. (BEARING MOVED WITHIN HINGE ASSY.)	 AS A RESULT, MASS BALANCE HORN WAS CONTACTING HORIZ STABILIZER CAUSING THE RESTRICTION. IF THE ELEVATOR WAS AT MAX TR	AVEL IN EITHER DIRECTION AND MOVED TO ITS EXTREME INBOARD POSITION, IT WAS IMPOSSIBLE TO MOVE ELEVATOR INTO STREAMLINED 	POSITION. HINGE ASSY REPLACED AS PRECAUTION. SUBMITTER RECOMMENDS MORE POSITIVE METHOD OF BEARING RETENTION BE USED.	2	L	7	2 	4F				A3EU 					 
1995080400523	19950804	00523	CE 	1995	8	4	95ZZZX3570 	1	19950628	G	7897		WIRE 			CESSNA	500 	560CESSNA 	2076750	CE 										TR STOW SWITCH	CHAFED 	B	L		EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	60GL	964 				5600187				FOUND CHAFED WIRE ON LEFT THRUST REVERSER FOR STOW SWITCH. THIS WAS CAUSING CIRCUIT BREAKER TO TRIP EACH TIME EMERGENCY	 STOW WAS SELECTED.					2	L	7	2 	4F			RT	A22CE 					 
1995080400524	19950804	00524	CE 	1995	8	4	95ZZZX3571 	1	19950706	G	3240	238000213	STOP SCREW 		238000218 	LEAR 	35 	35A 	5170602	CE 										POWER BRK VALVE	BACKED OUT 	B	S	A	TJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	94GP	8333 				094				NO BRAKE PRESSURE ON PILOT'S PEDALS. TROUBLESHOT TO A LOOSE STOP SCREW ON RIGHT POWER BRAKE VALVE. THE SCREW HAD BACKE	D OUT ONE AND ONE-HALF TURNS WHICH CAUSED BRAKE PRESSURE FLUID BYPASS. ADJUSTED STOP SCREW AND RETORQUED NUT. SUBMITTE	R RECOMMENDS A MEANS TO SAFETY WIRE THE STOP SCREW AND JAM NUT.				2	L	7	2 	4F				A10CE 					 
1995080400525	19950804	00525	SO 	1995	8	4	95ZZZX3572 	2	19950711	G	7414	6220	MAGNETO 	SLICK 		PIPER 	PA46 	PA46310P 	7104605	SO 	CONT 	O520 	TSIO520BE 	17040	SO 					LT SIDE	LEAD BROKEN 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	888HL	535 			89030035	468508081	273621R			OWNER COMPLAINED OF A 'DEAD' LT MAGNETO. CHECKED TIMING AND FOUND POINTS OPENING PROPERLY. REMOVED MAGNETO AND DISASSE	MBLED. FOUND INSIDE OF MAGNETO CORRODED AND COIL GROUND LEAD BROKEN. SUSPECT LEAD BROKE DUE TO THE CORROSION. SLICK S	B1-88 REFERS TO INSPECTING MAGNETOS EVERY 100 HRS FOR MOISTURE CONTAMINATION. THIS WAS DONE ON THIS AIRCRAFT WITHIN 130	 HRS. THIS IS A VERY IMPORTANT BULLETIN BASED ON THE FACT THAT THESE MAGNETOS ARE PRESSURIZED AND WILL TEND TO HOLD MOI	STURE. SUBMITTER RECOMMENDS MAKING THIS A MANDATORY INSPECTION.		1	L	7	1 	3O	3	O		A25SO 	E8CE				 
1995080400526	19950804	00526	NE 	1995	8	4	95ZZZX3573 	3	19950701	G	6111		SNAP RING 			PIPER 	PA28 	PA28R200 	7102811	SO 						MCAULY	C3D36C	C3D36C41582 	NE 	NR 2 PROPELLER	LOOSE 	D				K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			GL	07	3057R	42 				28R35618		911787		A NEW PROP WAS INSTALLED 8-15-94 AFTER ENGINE OVERHAUL AND A REPAIR TO AIRFRAME. PROP REPORTED VIBRATING BY PILOTS. RP	M HAD TO BE ABOVE 2500 TO LESSEN VIBRATION. ON 10-12-94, A SNAP RING AND SHIMS WERE FOUND LOOSE ON NR 2 BLADE AND BLADE	 WAS LOOSE IN HUB. CONDITION DID NOT EXIST THE DAY BEFORE. PROP WAS REMOVED FOR DELIVERY TO MCCAULEY.				1	L	7	1 	3O				2A13 		5	N	SA645NE	 
1995080400527	19950804	00527	CE 	1995	8	4	95ZZZX3574 	1	19950626	G	5620	51116052	WINDOW 			CESSNA	421 	421C 	2076016	CE 										CABIN	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	43H	3065 				421C0443				AIRCRAFT HAD PROBLEMS WITH HOLDING PRESSURIZATION. FOUND 5 CABIN WINDOWS WITH CRACKS GOING THROUGH 50 PERCENT OF THE SC	REW HOLES. CRACKS FOUND AFTER PRESSURIZING THE AIRCRAFT AND PUT SOAP ON WINDOWS. AFTER REMOVING RETAINERS, CRACKS WERE	 WHERE THEY WERE MARKED FOR LEAKS. WINDOWS NEED TO HAVE CLOSER INSPECTION WITH A PRISM, WITH HIGH TIME ON THEM.				1	L	7	2 	3O				A7CE 					 
1995080400528	19950804	00528	CE 	1995	8	4	95ZZZX3575 	1	19950626	G	5620	51116059	WINDOW 			CESSNA	421 	421C 	2076016	CE 										SCREW HOLES	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	43H	3065 				421C0443				AIRCRAFT HAD PROBLEMS WITH HOLDING PRESSURIZATION. FOUND 1 WINDOW WITH 50 PERCENT OF THE SCREW HOLES WITH CRACKS. CRAC	KS WERE FOUND AFTER PRESSURIZING THE AIRCRAFT AND PUTTING SOAP ON WINDOWS. AFTER REMOVING RETAINERS, CRACKS WERE FOUND 	WHERE MARKED. WINDOWS NEED TO HAVE CLOSER INSPECTION WITH A PRISM, WHEN THEY HAVE HIGH TIME.				1	L	7	2 	3O				A7CE 					 
1995080400529	19950804	00529	CE 	1995	8	4	95ZZZX3576 	1	19950626	G	5620	511160510	WINDOW 			CESSNA	421 	421C 	2076016	CE 										SCREW HOLES	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	43H	3065 				421C0443				AIRCRAFT HAD PROBLEMS WITHHOLDING PRESSURIZATION. FOUND 1 WINDOW WITH 50 PERCENT OF THE SCREW HOLES WITH CRACKS. CRACK	S WERE FOUND AFTER PRESSURIZING THE AIRCRAFT AND PUTTING SOAP ON WINDOWS. AFTER REMOVING THE RETAINERS, CRACKS WERE FOU	ND WHERE MARKED. WINDOWS NEED TO HAVE CLOSER INSPECTION WITH A PRISM, WITH HIGH TIME ON THEM.				1	L	7	2 	3O				A7CE 					 
1995080400530	19950804	00530	CE 	1995	8	4	95ZZZX3577 	1	19950623	G	2750	08615584	GEAR 		556517531 	CESSNA	500 	550 	2076604	CE 										LT FLAP GEARBOX	FAILED 	B	S	A	EBVR	L				ABORTED APPROACH 				O	J		OTHER 	WARNING INDICATION 		AP	APPROACH 	1			GL	09	80AW	6801 	799 		91888	5500186				DURING FINAL APPROACH, FLAPS WERE SELECTED TO FULL DOWN FROM APPROACH POSITION. PILOT HEARD A LOUD BANG AND AIRCRAFT 'S	ETTLED'. A GO-AROUND WAS PERFORMED. PILOT NOTICED THE FLAP POSITION INDICATOR SHOWED FLAPS UP WITH SELECTOR IN THE FUL	L DOWN POSITION. A NO-FLAP LANDING WAS PERFORMED. DURING TAXI, PILOT NOTED FLAP INDICATOR MOVING TOWARD FULL DOWN POSI	TION. FLAPS WERE FULLY DOWN AT ENGINE SHUT-DOWN. FLAP GEARBOXES WERE REMOVED AND DISASSEMBLED. FOUND THE SMALL GEAR T	EETH SHEARED OFF OF BOTH TRANSFER GEARS. BOTH GEARBOXES WERE OVERHAULED AND REINSTALLED. PILOT ALSO NOTED FLAP MOTORS 	CONTINUED TO RUN AFTER GEARBOX FAILURE UNTIL CIRCUIT BREAKER WAS OPENED.	1	L	7	2 	4F				A22CE 					 
1995080400531	19950804	00531	CE 	1995	8	4	95ZZZX3578 	1	19950623	G	2750	08615584	GEAR 		556517531 	CESSNA	500 	550 	2076604	CE 										RT FLAP GEARBOX	FAILED 	B			EBVR	L				ABORTED APPROACH 				O	J		OTHER 	WARNING INDICATION 		AP	APPROACH 	1			GL	09	80AW	6801 	799 		92088	5500186				DURING FINAL APPROACH, FLAPS WERE SELECTED TO FULL DOWN FROM APPROACH POSITION. PILOT HEARD A LOUD BANG AND AIRCRAFT 'S	ETTLED'. A GO-AROUND WAS PERFORMED. PILOT NOTICED THE FLAP POSITION INDICATOR SHOWED FLAPS UP WITH SELECTOR IN THE FUL	L DOWN POSITION. A NO-FLAP LANDING WAS PERFORMED. DURING TAXI, PILOT NOTED FLAP INDICATOR MOVING TOWARD FULL DOWN POSI	TION. FLAPS WERE FULLY DOWN AT ENGINE SHUT-DOWN. FLAP GEARBOXES WERE REMOVED AND DISASSEMBLED. FOUND THE SMALL GEAR T	EETH SHEARED OFF OF BOTH TRANSFER GEARS. BOTH GEARBOXES WERE OVERHAULED AND REINSTALLED. PILOT ALSO NOTED FLAP MOTORS 	CONTINUED TO RUN AFTER GEARBOX FAILURE UNTIL CIRCUIT BREAKER WAS OPENED.	1	L	7	2 	4F				A22CE 					 
1995080400532	19950804	00532	NE 	1995	8	4	95ZZZX3579 	2	19950530	G	7200		ENGINE 			LEAR 	24 	24D 	5170311	CE 	GE 	CJ610 	CJ6106 	30006	NE 					NR 1	FLAME-OUT 	D				O				OTHER 				X			ENGINE FLAMEOUT 			CR	CRUISE 	1			GL	25	888FA	9078 	4483 			257	251357A			AT CRUISE ALTITUDE OF 45,000 FEET, ABOUT 1.5 HOURS INTO FLIGHT, BOTH ENGINES FLAMED OUT AT EXACTLY THE SAME TIME. THE F	IRST INDICATION WAS A SLIGHT BUMP, THEN THE RPM GAUGES STARTED ERODING FROM 95 PERCENT. THE CREW WAS ABLE TO EXECUTE A 	RE-LIGHT ON BOTH ENGINES AT 25,000 FEET. BOTH ENGINES WERE CHECKED FOR FOD DAMAGE. FUEL FILTERS WERE CHECKED. P AND D	 VALVES WERE LOOKED AT. NO REASON FOR FLAME-OUT WAS FOUND AT THIS TIME.			2	L	7	2 	4J	4	J		A10CE 	1E16				 
1995080400533	19950804	00533	NE 	1995	8	4	95ZZZX3580 	2	19950530	G	7200		ENGINE 			LEAR 	24 	24D 	5170311	CE 	GE 	CJ610 	CJ6106 	30006	NE 					NR 2	FLAME-OUT 	D				O				OTHER 				X			ENGINE FLAMEOUT 			CR	CRUISE 	1			GL	25	888FA	9122 	4483 			257	251358A			AT CRUISE ALTITUDE OF 45,000 FEET, ABOUT 1.5 HOURS INTO FLIGHT, BOTH ENGINES FLAMED OUT AT EXACTLY THE SAME TIME. THE F	IRST INDICATION WAS A SLIGHT BUMP, THEN THE RPM GAUGES STARTED ERODING FROM 95 PERCENT. THE CREW WAS ABLE TO EXECUTE A 	RE-LIGHT ON BOTH ENGINES AT 25,000 FEET. BOTH ENGINES WERE CHECKED FOR FOD DAMAGE. FUEL FILTERS WERE CHECKED. P AND D	 VALVES WERE LOOKED AT. NO REASON FOR FLAME-OUT WAS FOUND AT THIS TIME.			2	L	7	2 	4J	4	J		A10CE 	1E16				 
1995080400534	19950804	00534	NM 	1995	8	4	95ZZZX3581 	1	19950707	G	2730	8817001001	SOLENOID VALVE 		1536400503 	DOUG 	MD11 	MD11 	3023602	NM 										ELEV PCU	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99										CORROSION OF PINS IN SOLENOID CONNECTOR CAUSING ARCING AND BURNING OFF PINS RESULTING IN LOSS OF AUTOMATIC CONTROL OF EL	EVATOR SURFACE, PCU IS LOCATED IN A RECESS OF THE FUEL TANK IN THE TAIL SECTION. A SAFETY CONCERN SINCE ARCING IS OCCUR	RING IN THE PROXIMITY OF THE FUEL TANK. SUSPECT CAUSE: FAULTY MATERIALS OR FAULTY SEALING PROTECTION.				2	L	7	3 	4F			RT	A22WE 					 
1995080400535	19950804	00535	WP 	1995	8	4	95ZZZX3582 	1	19950426	G	7110	5910298514	NOSE COWL 			DOUG 	DC9 	DC9 	3022002	WP 	PWA 	JT8 	JT8D9A 	52048	NE 					DEICE DUCT	BOLTS CHAFED 	B			TW3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27					M36382					INSPECTION OF NOSE COWL FOR UNRELATED REPAIR REVEALED THE NAS6404U12 BOLTS, 4 EACH, WERE WORN MORE THAN 50 PERCENT THROU	GH IN THE GRIP AREA DUE TO LACK OF LUBRICATION OF THE BEARINGS.					2	L	7	2 	4F	4	F		A6WE 	E2EA				 
1995080400537	19950804	00537	SW 	1995	8	4	95ZZZX3584 	1	19950622	G	5330		FUSELAGE 			SWRNGN	SA226 	SA226T 	8780122	SW 										PROPELLER LINE	SKIN DAMAGE 	B			GFER	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	09	105BB					T229				AFTER AIRCRAFT WAS STRIPPED IN PREPARATION FOR PAINT, A LARGE AMOUNT OF PLASTIC FILLER WAS DISCOVERED ON THE FUSELAGE IN	 LINE WITH THE PROPELLER ROTATIONAL PLANES. REMOVAL OF THE FILLER REVEALED EXTENSIVE GRINDING TO ENSURE THE FILLER WOUL	D STICK AND GOUGES FORM A 'CHEESE GRATER' TYPE FILE, NO ALODINE WAS APPLIED, ALTHOUGH NO CORROSION WAS NOTED. THE DAMAG	E IS CURRENTLY BEING EVALUATED FOR THE DEVELOPMENT OF A REPAIR SCHEME. SUBMITTER SUGGESTS CAREFUL ADHERENCE TO PROPER M	AINTENANCE TECHNIQUES AND MM REQUIREMENTS WOULD HAVE PREVENTED THIS DAMAGE.		1	L	7	2 	4T				A5SW 					 
1995080400538	19950804	00538	CE 	1995	8	4	95ZZZX3585 	1	19950706	G	3246	5030001087	WHEEL 			BEECH 	90 	C90A 	1152911	CE 										LT/RT MLG	CRACKED 	B		A	HBKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	1564P	1375 				LJ1230				THIS PART NUMBER WHEEL HALF CRACKED ON LEFT AND RIGHT MAIN WHEELS. THIS SAME PART NUMBER WHEEL HALF FOUND CRACKED ON AN	OTHER AIRCRAFT LAST WEEK.					1	L	7	2 	3T			RT	3A20 					 
1995080400539	19950804	00539	CE 	1995	8	4	95ZZZX3588 	1	19950613	G	3230	017A38511	EMERGENCY EXT 	BRACKETT 		MTSBSI	MU2 	MU2B25 	5780409	CE 										EXT SYSTEM	JAMMED 	B			HI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	264KW					264				DURING 100 HOUR INSPECTION, FOUND EMERGENCY GEAR EXTENSION SYSTEM PARTIALLY JAMMED. FURTHER INVESTIGATION REVEALED LOWE	R STOP PIN BROKEN OUT OF FRAME ALLOWING SECTOR GEAR TO PARTIALLY DISENGAGE ITS MATING GEAR AND JAM. THIS COULD PREVENT 	GEAR EXTENSION IN AN EMERGENCY.				1	H	7	2 	3T				A2PC 					 
1995080400540	19950804	00540	EU 	1995	8	4	95ZZZX3589 	1	19950621	G	3230	25UM9551K2	LINK 			BRAERO	DH125 	HS125700A 	4230170	EU 										RT MLG	DAMAGED 	B			WLCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	34RE	7864 				257022				LINK ASSY FOUND NICKED ON BOTH SIDES BECAUSE OF OVERTRAVEL OF THE LANDING GEAR INBD DOOR SEQUENCE VALVE MECHANISM BEING 	OUT OF RIG. SUBMITTER RECOMMENDS RIGGING BE CHECKED MORE THOROUGHLY AND THIS ITEM BE INSPECTED VISUALLY FOR POSSIBLE DA	MAGE. FOUND DURING SCHEDULED REMOVAL OF FORWARD HINGE FITTINGS FOR TIME (HRS) WITH NEW.				2	L	7	2 	4F				A3EU 					 
1995012000479	19950120	00479	WP 	1995	1	20	95ZZZX359 	2	19950108	G	7321	89541015	FUEL CONTROL 			MTSBSI	MU2 	MU2B35 	5780411	CE 	GARRTT	TPE331	TPE33125AA 	01514	WP 					LT ENGINE	CLOGGED 	D				E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			CR	CRUISE 	1			SW	15	121BA		650 		316850	599				INTERNAL ORIFICE CLOGGED CAUSING ENGINE TO GO TO MAXIMUM POWER AND MAXIMUM R.P.M., IN-FLIGHT SHUT DOWN. FUEL CONTROL HA	D BEEN REPAIRED AT BENDIX FACTORY 50 HOURS PRIOR TO FAILURE.					1	H	7	2 	3T	3	T	RT	A10SW 	E2WE				 
1995080400541	19950804	00541	EU 	1995	8	4	95ZZZX3590 	1	19950621	G	2910	257SF491PT1	LINE 			BRAERO	DH125 	HS125700A 	4230170	EU 										AFT COMPT HYD	CHAFED 	B			WLCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	34RE	7828 				257022				LINE ASSEMBLIES FOUND CHAFING THROUGH AT ATTACHMENT BRACKETS, LONGERON, AND FORMERS (FRAMES) BECAUSE OF CRACKING AND SUB	SEQUENT FAILURE OF ATTACH BRACKETS. SUSPECT CAUSE WAS MAINTENANCE PERSONNEL LYING ON TOP OF THESE LINES TO GAIN ACCESS 	TO FRONT SIDE OF APU. ALSO, THESE LINES ARE COVERED BY INSULATION BLANKETS SO DAMAGE MAY NOT BE APPARENT. SUBMITTER SU	SPECTS THE AFT COMPARTMENT INSPECTION SHOULD BE REVISED TO STRESS MORE THOROUGH INSPECTION OF THIS AREA.			2	L	7	2 	4F				A3EU 					 
1995080400542	19950804	00542	EU 	1995	8	4	95ZZZX3591 	1	19950621	G	2910	257SF77	LINE 			BRAERO	DH125 	HS125700A 	4230170	EU 										AFT COMPT HYD	CHAFED 	B			WLCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	34RE	7828 				257022				LINE ASSEMBLIES FOUND CHAFING THROUGH AT ATTACHMENT BRACKETS, LONGERON, AND FORMERS (FRAMES) BECAUSE OF CRACKING AND SUB	SEQUENT FAILURE OF ATTACH BRACKETS. SUSPECT CAUSE WAS MAINTENANCE PERSONNEL LYING ON TOP OF THESE LINES TO GAIN ACCESS 	TO FRONT SIDE OF APU. ALSO, THESE LINES ARE COVERED BY INSULATION BLANKETS SO DAMAGE MAY NOT BE APPARENT. SUBMITTER SU	SPECTS THE AFT COMPARTMENT INSPECTION SHOULD BE REVISED TO STRESS MORE THOROUGH INSPECTION OF THIS AREA.			2	L	7	2 	4F				A3EU 					 
1995080400543	19950804	00543	WP 	1995	8	4	95ZZZX3592 	2	19950621	G	7310	YA001295	LINE 			BRAERO	DH125 	HS125700A 	4230170	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					RT ENGINE	DAMAGED 	B			WLCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	34RE					257022				LINE ASSEMBLY FOUND KINKED AT LOWER END. THIS PART IS AN ENGINE MAIN FUEL SUPPLY LINE (FLEXIBLE). THIS LINE MUST BE DI	SCONNECTED IN ORDER TO ALLOW CERTAIN DEFUELING OPERATIONS. CARE MUST BE EXERCISED WHEN DISCONNECTING THE LOWER FITTING;	 OTHERWISE, KINKING WILL OCCUR RESULTING IN DIMINISHED FUEL SUPPLY TO THE ENGINE. SUBMITTER SUGGESTS MECHANICS SHOULD B	E ADVISED TO USE MORE CARE WHEN DISTURBING THIS LINE ASSEMBLY. ACFT TT 3,223 HOURS.			2	L	7	2 	4F	4	F		A3EU 	E6WE				 
1995080400544	19950804	00544	EA 	1995	8	4	95ZZZX3593 	1	19950707	G	4920	GTCP100E	AUXILIARY POWER 	GARRTT 		CNDAIR	CL601 	CL6013A 	8070802	EA 										TAIL COMPT	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	399CF	1450 	1215 		P370	5084				POPPING SOUND HEARD WHEN APU LOAD CONTROL VALVE OPENED ON FIRST START OF DAY. INSPECTED/FOUND TURBINE NOZZLE BLADE TIPS	 MISSING MATERIAL. REMOVED APU, INSTALLED LOANER UNIT. TT 1,450 HRS. TSO 1,215 HRS. CSN 1,146.					2	L	7	2 	4F			RT	A21EA 					 
1995080400545	19950804	00545	EA 	1995	8	4	95ZZZX3594 	1	19950705	G	7603	601906011035	THROTTLE 			CNDAIR	CL601 	CL6013A 	8070802	EA 										NR 2 QUADRANT	EXCESS PLAY 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	399SW		6 		152	5009				NR 2 ENGINE THROTTLE LEVER HAS EXCESSIVE PLAY AND FRICTION KNOB MALFUNCTIONING. REPLACED THROTTLE QUADRANT IAW 73-00/76	-1101. RUN-UP AND OPS CHECK NORMAL.					2	L	7	2 	4F			RT	A21EA 					 
1995080400546	19950804	00546	EA 	1995	8	4	95ZZZX3595 	1	19950703	G	7603	600906011035	SOLENOID SWITCH 			CNDAIR	CL601 	CL6013A 	8070802	EA 										RT QUADRANT	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	399SW		7 		137	5009				RIGHT THRUST REVERSER STUCK AT IDLE AFTER GREEN LIGHT DURING DEPLOYMENT. FOUND SOLENOID NOT PULLING. REPLACED THROTTLE	 QUADRANT. OPS CHECK NORMAL, ENGINE POWER RUNS GOOD.					2	L	7	2 	4F			RT	A21EA 					 
1995080400547	19950804	00547	CE 	1995	8	4	95ZZZX3596 	1	19950701	G	2820	W901B16DE	CLAMP 		174026701 	LEAR 	55 	55C 	5170706	CE 										RT ENG FUEL	OPENED 	B		A	NV1R	O				OTHER 				K	X		FLUID LOSS 	ENGINE FLAMEOUT 		NR	NOT REPORTED 	1			GL	05	40CR					144				MAIN FUEL LINE SUPPLY FROM RT WING TO RT ENGINE CLAMP OPENED UP WHILE AIRCRAFT WAS IN FLIGHT CAUSING FUEL LOSS. FUEL IM	BALANCE AND RIGHT ENGINE FLAME-OUT AFTER LANDING. THIS CLAMP IS EASILY OPENED BY JUST BUMPING IT. RIGHT MAIN FUEL LINE	 HAS NO STAND-OFF TO KEEP IT FROM MOVING, ALSO, NO SAFETY WIRE HOLES ON CLAMP HOUSING. SUBMITTER SUGGESTS WRAPPING ALL 	CLAMPS WITH SAFETY WIRE UNTIL CLAMP CAN BE REDESIGNED.			2	L	7	2 	4F			RT	A10CE 					 
1995080400548	19950804	00548	CE 	1995	8	4	95ZZZX3597 	1	19950612	G	3246	503000101109	WHEEL 			BEECH 	90 	E90 	1152914	CE 										MLG OTBD HALF	SPLIT 	D				C				ABORTED TAKEOFF 				O			OTHER 			TO	TAKEOFF 	1			NM	03	63BV				G5750	LW256				DURING TAKEOFF ROLL, PILOT HEARD A LOUD BANG. WHEN AIRCRAFT CAME TO A STOP, THE OUTBOARD WHEEL HALF HAD SPLIT IN HALF S	TARTING AT INBOARD WHEEL HALF MATING FLANGE AND CRACK WORKING ITS WAY TOWARD WHEEL BEAD AREA.					1	L	7	2 	3T				3A20 					 
1995080400550	19950804	00550	CE 	1995	8	4	95ZZZX3599 	1	19950612	G	2720	5052432610	ARM ASSY 		50524402613 	BEECH 	90 	C90 	1152913	CE 										PILOT RT RUD PED	BROKEN 	D	P			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	02	6723Y	4020 			533233	LJ1013				THE RIGHT PILOT'S SIDE RUDDER BROKE LOOSE FROM THE ARM ASSY WHERE IT BOLTS ON THIS ARM ASSY. ALL OTHER PEDALS AND ARMS 	ON THIS AIRCRAFT WERE FOUND OKAY. IT APPEARS THE BUSHING IN THE ARM WORKED LOOSE AND WORE ITS WAY THROUGH THE ARM UNTIL	 IT FINALLY BROKE THROUGH.				1	L	7	2 	3T				3A20 					 
1995080400551	19950804	00551	EU 	1995	8	4	95ZZZX3601 	1	19950621	G	5210	25FC61893	HINGE SUPPORT 			HWKSLY	DH125 	HS125600A 	4230158	EU 										CABIN DOOR	DAMAGED 	B			WLCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	777SA	7742 				256015				THIS PART FOUND BROKEN AT STOPS AFTER PILOTS REPORTED MAIN DOOR ASSY 'LOOSE' WHEN OPEN AND PERSON STEPS ON DOOR STEPS (	UNSTABLE). CAUSE HAS BEEN DETERMINED AS RAPID OR HARSH OPERATION OF THE DOOR LOCKING HANDLES WHEN CLOSING THE DOOR. SU	BMITTER SUGGESTS CARE BE EXERCISED, WHEN OPERATING THE DOOR, BY FLIGHT CREWS AND GROUND PERSONNEL.				2	L	7	2 	4J				A3EU 					 
1995080400552	19950804	00552	EU 	1995	8	4	95ZZZX3602 	2	19950621	G	7310	YA001295	LINE 			HWKSLY	DH125 	HS125600A 	4230158	EU 	RROYCE	VIPER 	VIPER60122 	54551	EU 					RT ENGINE	KINKED 	B			WLCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	777SA	7742 				256015				LINE ASSEMBLY FOUND KINKED AT LOWER END. THIS PART IS AN ENGINE MAIN FUEL LINE (FLEXIBLE). THIS LINE MUST BE DISCONNEC	TED IN ORDER TO ALLOW CERTAIN DEFUELING OPERATIONS. CARE MUST BE EXERCISED WHEN DISCONNECTING THE LOWER FITTING; OTHERW	ISE, KINKING WILL OCCUR RESULTING IN DIMINISHED FUEL SUPPLY TO THE ENGINE. SUBMITTER SUGGESTS MECHANICS SHOULD BE ADIVS	ED TO USE MORE CARE WHENEVER THIS LINE ASSEMBLY IS DISTURBED. ACFT TT 2,952 HRS.			2	L	7	2 	4J	4	J		A3EU 	E15EU				 
1995080400553	19950804	00553	NM 	1995	8	4	95ZZZX3603 	1	19950307	G	5320	65C3449036	FITTING 			BOEING	737 	737205 		NM 										BS 695 RT	CRACKED 	B			EE4Y	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	23	73TH					21729				FOUND BS 695, RIGHT FRAME LOWER FITTINGS WITH CRACKS ON WEB RADIUS AND ON THE OUTBOARD VERTICAL FLANGE. NOTE: THIS FIT	TING ATTACHES TO MAIN LANDING GEAR LINK SUPPORT BEAM TO BODY FRAME.					2	L	7	2 	4F				A16WE 					 
1995080400556	19950804	00556	CE 	1995	8	4	95ZZZX3606 	1	19950502	G	5522	11561001087	DOUBLER 			BEECH 	100 	B100 	1152919	CE 										ELEV STA 124.9	CRACKED 	B		A	HI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	87XX	3692 				BE105				AT ELEVATOR STATION 124.910, WHERE LEADING EDGE SKIN JOINS EXTENDED BALANCE AREA OF ELEVATOR, JOINER-DOUBLER THAT ATTACH	ES LEADING EDGE SKIN TO OUTBOARD LEADING EDGE RIB WAS FOUND CRACKED BOTH IN A FORE AND AFT AND ALSO A SIDE-TO-SIDE DIREC	TION. BOTH ELEVATORS ON THIS AIRCRAFT HAD SIMILAR CRACKS. SUSPECT CAUSED BY AERODYNAMIC LOADS ON ELEVATOR BALANCE TABS	 OR GUST LOADS.			1	L	7	2 	4T				A14CE 					 
1995080400609	19950804	00609	NM 	1995	8	4	95ZZZX3607 	1	19950718	G	5315		FLOOR BEAM 			BOEING	727 	727225 	1384077	NM 										FS 1130	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8840E					20383				CORROSION FOUND ON FLOOR BEAM STA 1130, BL 20 RT T0 BL 24 RT. SUSPECT CAUSE OF DAMAGE: MOISTURE TRAPPED BETWEEN TAPE U	SED ON BEAM AND CLIP NUT.					2	L	7	3 	4F				A3WE 					 
1995080400610	19950804	00610	NM 	1995	8	4	95ZZZX3608 	1	19950718	G	5315		FLOOR BEAM 			BOEING	727 	727225 	1384077	NM 										FS 344	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8840E					20383				CORROSION FOUND ON FLOOR BEAM STA 344, BL 12 LT TO BL 18 LT. SUSPECT CAUSE OF DAMAGE: MOISTURE TRAPPED BETWEEN TAPE US	ED ON BEAM AND CLIP NUT.					2	L	7	3 	4F				A3WE 					 
1995080400611	19950804	00611	GL 	1995	8	4	95ZZZX3609 	2	19950629	G	7310	219216	FILTER 			CESSNA	525 	525 	2076601	CE 	WILINT	FJ44 	FJ44 	66000	GL 					LT ENGINE	WARN LIGHT 	B			IW1R	L				ABORTED APPROACH 				J			WARNING INDICATION 			AP	APPROACH 	1			EA	25	94MZ	33 				5250094	1206			LEFT FUEL FILTER BYPASS INDICATOR LIGHT ILLUMINATED (ANNUNCIATING PENDING FILTER BYPASS) DURING 'GO-AROUND'. AIRCRAFT L	ANDED WITHOUT PROBLEMS. LEFT ENGINE FUEL FILTER ELEMENT WAS REPLACED. NO OBVIOUS FAULTS NOTED. RIGHT ENGINE FILTER EL	EMENT WAS ALSO REPLACED. IT, TOO, HAD NO OBVIOUS FAULTS.				1	L	7	2 	4F	4	F	RT	A1WI 	E3GL				 
1995080400612	19950804	00612	SO 	1995	8	4	95ZZZX3610 	2	19950710	G	7310	641032148	VALVE 			CESSNA	404 	404CESSNA 	2075901	CE 	CONT 	O520 	GTSIO520M 	17032	SO 					ENGINE FUEL	GASKET FAILED 	D				O				OTHER 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SO	17	2FOR					4040628	276446R			NEWLY INSTALLED OVERHAULED ENGINE AFTER 20 HOURS OF FLYING TIME. FUEL DISTRIBUTION VALVE ON TOP OF ENGINE HAD A BLOWN G	ASKET WHICH SPRAYED RAW FUEL ALL OVER THE ENGINE WHILE IN FLIGHT. ENGINE OVERHAULED BY TELEDYNE CONTINENTAL MOTORS.					1	L	7	2 	3O	3	O		A25CE 	E7CE				 
1995080400613	19950804	00613	CE 	1995	8	4	95ZZZX3611 	1	19950717	G	5541	3363000017	SPAR 			BEECH 	33 	35C33 	1151408	CE 										RUDDER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	6142V	4695 				CD874				PERFORMING AD 93-24-03 FOUND UPPER RUDDER SPAR CRACKED.						1	L	7	1 	3O				3A15 					 
1995080400614	19950804	00614	CE 	1995	8	4	95ZZZX3612 	1	19950628	G	3260	1SE13	SWITCH 			CESSNA	310 	310R 	2074245	CE 										LT MLG DOWNLOCK	FAILED 	D				K				NONE 				P			NO WARNING INDICATION 			IN	INSP/MAINT 	1			GL	07	8521G					310R0931				LEFT MAIN GEAR DOWN AND LOCK LIGHT INOP. JACKED AIRCRAFT, FOUND DOWN AND LOCK SWITCH DEFECTIVE. REMOVED AND REPLACED S	WITCH ASSY. OPS GOOD.					1	L	7	2 	3O				3A10 					 
1995080400615	19950804	00615	EU 	1995	8	4	95ZZZX3613 	1	19950613	G	3231	T700A3230050000	ACTUATOR 			SOCATA	TBM 	TBM700 	8682000	EU 										RT MLG DOOR	OUT OF RIG 	H		A		O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			GL	25	84HS	712 				50				'LDG DOOR AMBER LITE ON IN-FLIGHT.' FOUND RT DOORS NOT COMPLETELY CLOSED WITH GEAR RETRACTED. FOUND GEAR ACTUATOR ROD 	END HAD TURNED OUT. (PISTON ROD TURNED OUT OF ROD END) AFFECTING DOOR RIGGING. RIGGED DOOR AND ROD END IAW 32-30-01. S	ECURED ROD END. OPS CHECKED GOOD. SUBMITTER SUGGESTS ROD END NEEDS A LOCKING KEY WAY CUT IN IT TO PREVENT ACTUATOR PIS	TON AND ROD FROM TURNING.			1	L	7	1 	3T			RT	A60EU 					 
1995080400616	19950804	00616	CE 	1995	8	4	95ZZZX3614 	1	19950713	G	5511	053200198	SPAR 			CESSNA	172 	172M 	2072418	CE 										HORIZ STAB	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	1261U	3801 				17266956				DURING ANNUAL INSPECTION, THE FRONT SPAR AND SKID OF THE HORIZONTAL STABILIZER WERE FOUND SEVERELY CRACKED AND BUCKLED. 	 NEW PARTS FROM CESSNA WERE REINFORCED AND MUCH STRONGER THAN ORIGINAL. SUSPECT IMPROPER GROUND HANDLING OR SEVERE TURB	ULENCE.				1	H	7	1 	3O			NT	3A12 					 
1995080400617	19950804	00617	CE 	1995	8	4	95ZZZX3615 	1	19950713	G	5512	053200123	SKIN 			CESSNA	172 	172M 	2072418	CE 										HORIZ STAB	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	1261U	3801 				17266956				DURING ANNUAL INSPECTION, THE FRONT SPAR AND SKID OF THE HORIZONTAL STABILIZER WERE FOUND SEVERELY CRACKED AND BUCKLED. 	 NEW PARTS FROM CESSNA WERE REINFORCED AND MUCH STRONGER THAN ORIGINAL. SUSPECT IMPROPER GROUND HANDLING OR SEVERE TURB	ULENCE.				1	H	7	1 	3O			NT	3A12 					 
1995080400618	19950804	00618	CE 	1995	8	4	95ZZZX3616 	1	19950714	G	5541	3363000017	SPAR 			BEECH 	33 	G33 	1151435	CE 										RUDDER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	9220Q	5000 				CD1255				PERFORMING AD 93-24-0, FOUND UPPER RUDDER SPAR CRACKED.						1	L	7	1 	3O				3A15 					 
1995080400619	19950804	00619	SO 	1995	8	4	95ZZZX3617 	1	19950627	G	5311	6852500	FRAME 			PIPER 	PA32 	PA32R300 	7103213	SO 										FS 73	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	31SW	11074				32R7680311				FOUND STA 73 FRAME ASSY CRACKED ON RIGHT SIDE. PIPER SB NR 946 DATED 3-4-91, REQUIRES INSPECTION AND GIVES REPAIR INSTR	UCTIONS FOR LEFT SIDE ONLY. CRACK FOUND IN SAME AREA AS STATED IN SB 946 EXCEPT ON RIGHT SIDE. SUSPECT RIGHT WING AFT 	ATTACH BOLT LOOSE ALLOWING MOVEMENT IN WING AND MAY HAVE CAUSED CRACKS. SUBMITTER RECOMMENDS INSPECTING RIGHT SIDE THE 	SAME AS THE LEFT AS STATED IN PIPER SB NR 946.			1	L	7	1 	3O				A3SO 					 
1995080400620	19950804	00620	EA 	1995	8	4	95ZZZX3618 	1	19950316	G	2710	A285510	BELLCRANK 			SCWZER	G164 	G164B 	3952802	EA 										AILERON	BUSHING LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	7503L	1484 				826B				AILERON BELLCRANK ASSY. AD 82-13-06 APPLIES TO THIS PROBLEM, BUT DOES NOT INCLUDE THIS SERIAL NUMBERED AIRCRAFT. SUBMI	TTER SUGGESTS AD SHOULD READ (SN 1B AND UP).					1	Q	7	1 	3R				1A16 					 
1995080400621	19950804	00621	SW 	1995	8	4	95ZZZX3619 	1	19950711	G	7922	53E19600	VALVE 			GULSTM	114 	114B 	O145001	SW 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	6022C	100 				14603				VALVE WAS REMOVED BECAUSE UNABLE TO READ S/N WHILE INSTALLED ON ENGINE. ONCE VALVE REMOVED, NUT WAS CHECKED FOR LOOSENE	SS AND FOUND VERY LOOSE. THIS VALVE, ACCORDING TO LYCOMING SB 518C, IS NOT EVER SUPPOSED TO BE APPLICABLE. LYCOMING WA	S NOTIFIED OF THIS FINDING.				1	L	7	1 	3O			RT	A12SO 					 
1995080400622	19950804	00622	CE 	1995	8	4	95ZZZX3620 	1	19950701	G	3230	35815109	UPLOCK CABLE 			BEECH 	35 	S35 	1151532	CE 										MLG UPLOCK	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	6810Q	3446 				D7594				FOUND LANDING GEAR UPLOCK CABLE BROKEN. SUBMITTER STATED TENSION MUST BE CHECKED EACH ANNUAL WITH LANDING GEAR IN UP AN	D LOCKED POSITION.					1	L	7	1 	3O			 	3A15 					 
1995080400623	19950804	00623	CE 	1995	8	4	95ZZZX3621 	1	19950707	G	2840		INDICATOR 			BEECH 	58 	58 	1152740	CE 										FUEL QTY	MALFUNCTION 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	07	696BD					TH352				BOTH FUEL GAUGES WENT TO ZERO. FOUND BOTH P.C. BOARDS INTERMITTENT. REMOVED AND REPLACED P.C. BOARDS, CALIBRATED, OPS 	CHECKS GOOD.					1	L	7	2 	3O				3A16 					 
1995080400624	19950804	00624	EA 	1995	8	4	95ZZZX3622 	2	19950703	G	7310	60100040544	HOSE 			CESSNA	172 	R172K 	2072431	CE 	LYC 	O320 	O320E2D 	41508	EA 					ENGINE FUEL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	09	3315V					R1722248				FUEL HOSE RUNS ACROSS THE TOP OF THE ENGINE. WHEN PRESSURE CHECKED, IT LEAKED ALONG THE ENTIRE LENGTH. TAG ON HOSE HAS	 THE FOLLOWING DATA: PAW 601000-4-0544. PT10-89. A4Q89. 1000 PSI. RUBBER. 00624. TSO - 053A. SEE AEROQUIP SBAA13	5 - THESE HOSES ARE STILL OUT THERE.				1	H	7	1 	3O	3	O		3A17 	E274				 
1995080400625	19950804	00625	CE 	1995	8	4	95ZZZX3623 	1	19950522	G	2430	S19151	FILTER 			CESSNA	172 	172P 	2072436	CE 										ALTERNATOR	MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	216AF					17274165				UPON INSPECTION OF ALTERNATOR, RADIO NOISE FILTER FOUND MISSING. SUBMITTER SUGGESTS LARGER MOUNT LUG ALLOWING LARGER AT	TACH NUT (HIGHER TORQUE).					1	H	7	1 	3O			NT	3A12 					 
1995080400626	19950804	00626	CE 	1995	8	4	95ZZZX3624 	1	19950522	G	5330		SKIN 			CESSNA	172 	172N 	2072434	CE 										LT FUSELAGE	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	215AF	8918 				17270844				FOUND LEFT FUSELAGE SKIN CRACKED AT REFUELING STEP. CRACK RADIATED UP AND FORWARD FROM UPPER FORWARD STEP ATTACH WASHER	 (DISPLACMENT TYPE). SUBMITTER SUGGESTS REGULAR CLOSE INSPECTION OF AREA AND CONSTRUCTION OF A STURDY DOUBLER REDUCING 	SKIN TENSION.				1	H	7	1 	3O			NT	3A12 					 
1995080400627	19950804	00627	CE 	1995	8	4	95ZZZX3625 	1	19950713	G	5511	053200198	SPAR 			CESSNA	172 	172P 	2072436	CE 										HORIZ STAB	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	52440	6552 				17274523				DURING 100-HOUR INSPECTION, THE FRONT SPAR OF THE HORIZONTAL STABILIZER WAS FOUND CRACKED AT THE CENTER SECTION LIGHTING	 HOLE. SUBMITTER SUGGESTS THE CAUSE WAS METAL FATIGUE CAUSED BY PROPELLER PULSES, TURBULENCE, AND VIBRATION.					1	H	7	1 	3O			NT	3A12 					 
1995080400628	19950804	00628	EU 	1995	8	4	95ZZZX3626 	1	19950719	G	7810	D68013000	CLAMP 			WSK 	M18 	M18DROMADER 	9810102	EU 										EXH OUTLET	FAILED 	G			SDIG	A				UNSCHED LANDING 				R	D		PARTIAL RPM/PWR LOSS 	INFLIGHT SEPARATION 		NR	NOT REPORTED 	1			SW	03	7070U					1200920				PILOT NOTICED AN OBJECT FLY PAST HIS RIGHT LOWER FIELD OF VISION. THE ENGINE LOST POWER SECONDS LATER. UPON EXAMINATIO	N OF THE AIRCRAFT, THE EXHAUST PIPE OUTLET'S UPPER AND LOWER CLAMPS WERE MISSING. THE OEM CLAMP IS A MUCH HEAVIER CLAMP	 THAN THE ONE THAT IS BEING USED.				1	L	7	1 	3O				A47EU 					 
1995080400629	19950804	00629	CE 	1995	8	4	95ZZZX3627 	1	19950721	G	2840		INDICATOR 			CESSNA	150 	152 	2071835	CE 										FUEL QTY	WILL NOT CALIB 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	01	757UR					15280018				AFTER INSTALLING REPLACEMENT FUEL QUANTITY GAUGES AND TRANSMITTERS PER SK152-21A, THE TRANSMITTERS COULD NOT BE CALIBRAT	ED, THE GAUGES READ FULL WITH TANKS LESS THAN HALF FULL. THERE IS A RESISTOR, PN 20 OHM 5W, INSTALLED BY THE FACTORY, A	T THE TRANSMITTER, ON THIS S/N AIRCRAFT. THIS RESISTOR MUST BE REMOVED FOR THE NEW SYSTEM TO OPERATE PROPERLY, BUT IS N	OT CALLED OUT IN THE INSTRUCTIONS PROVIDED WITH THE KIT. A CALL TO CESSNA'S TECHNICAL DEPARTMENT CONFIRMED THIS.			1	H	7	1 	3O			NT	3A19 					 
1995080400630	19950804	00630	CE 	1995	8	4	95ZZZX3628 	1	19950630	G	5712	00011013322	RIB 			BEECH 	200 	B200 	1152922	CE 										WING ROOT	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	18CM	2880 				BB1167				DURING PRE-BUY INSPECTION, FOUND BOTH LEADING EDGE RIBS IN WING ROOT BY NACELLE CRACKED. ALSO, FOUND THE SCREWS INSIDE 	THE PANEL THAT SECURE THIS AREA WERE LOOSE. THE END RESULT CAN LEAD TO A CRACKED LEADING EDGE IF NOT FOUND. SUBMITTER 	SUGGESTS A FLEET INSPECTION AND NOTIFICATION OF MANUFACTURER.				1	L	7	2 	4T				A24CE 					 
1995080400631	19950804	00631	CE 	1995	8	4	95ZZZX3629 	1	19950630	G	5712	00011013321	RIB 			BEECH 	200 	B200 	1152922	CE 										WING ROOT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	18CM	2880 				BB1167				DURING PRE-BUY INSPECTION, FOUND BOTH LEADING EDGE RIBS IN WING ROOT BY NACELLE CRACKED. ALSO, FOUND THE SCREWS INSIDE 	THE PANEL THAT SECURE THIS AREA WERE LOOSE. THE END RESULT CAN LEAD TO A CRACKED LEADING EDGE IF NOT FOUND. SUBMITTER 	SUGGESTS A FLEET INSPECTION AND NOTIFICATION OF MANUFACTURER.				1	L	7	2 	4T				A24CE 					 
1995080400632	19950804	00632	NE 	1995	8	4	95ZZZX3630 	2	19950607	G	7260	208312604	LOCK PIN 		208325023 	SEMCO 	CLNGER	CHALLENGER 	8070802	NM 	LYC 	ALF502	ALF502L2 	41580	NE 					ASSORY DR GR BOX	FAILED 	B	L		SH5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	733CF	1486 			82G004	1041	LF03089S			OIL ANALYSIS, FINDING AN INCREASE IN METAL CONTAMINATION, INVESTIGATION REVEALED THE ACCESSORY DRIVE GEARBOX DRIVESHAFT 	LOCK ASSY POST SB ALF502L 72-0175, HAD DROPPED DOWN ONTO THE STARTER DRIVESHAFT MACHINING AWAY AT THE DRIVESHAFT WHICH C	AUSED THE REPLACEMENT OF THE FOLLOWING COMPONENTS: ACCESSORY DRIVE GEARBOX MODULE, FUEL/OIL HEAT EXCHANGER, THE ENGINE 	DRIVEN OIL PUMP ASSY AND THE NR 12 BEARING. SUSPECT CAUSED BY FAILURE OF THE DRIVESHAFT LOCK PIN (PN 2-083-126-04). RE	COMMEND ASAP (ESPECIALLY IF NOT ON ACTIVE OIL ANALYSIS PROGRAM) TO REMOVE ACCESSORY DRIVE GEARBOX DRIVESHAFT LOCK ASSY A	ND INSPECT DRIVESHAFT LOCK PIN (PN 2-083-126-04) FOR BEING ANYTHING LESS THAN STRAIGHT WITH EVENLY CUT ENDS.	1	B	0	0 		4	F		A13SO 	E6NE				 
1995080400634	19950804	00634	GL 	1995	8	4	95ZZZX3632 	2	19950701	G	7250		WHEEL 								ALLSN 	250C 	250C20 	03013	GL 					TURBINE	SHAFT MISMFG 	B			UP9R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	07										FACTORY NEW WHEEL SPLINED ADAPTER SHAFT PILOT MEASURES 0.566 INCH WHICH IS APPROXIMATELY 0.010 INCH LARGER THAN MAXIMUM.	 WHEEL RETURNED TO ALLISON.										3	U			E4CE				 
1995080400635	19950804	00635	NM 	1995	8	4	95ZZZX3633 	1	19950616	G	2820	10605368	HOSE 			BOEING	727 	727225 	1384077	NM 										FS 900-910	DETERIORATED 	B			VG5R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	07	354PA					20624				DURING STRUCTURAL INSPECTION, DISCOVERED FUEL SHROUD LEAK AT BS 900 - BS 910. UPON FURTHER INSPECTION, FOUND NR 2 ENGIN	E FUEL FEED LINE DETERIORATED AND SEEPING AT SLEEVE FITTING. HOSE AGE OVER 22 YEARS.					2	L	7	3 	4F				A3WE 					 
1995080400636	19950804	00636	CE 	1995	8	4	95ZZZX3634 	1	19950613	G	7170	1003890161	SWITCH 		909200343 	BEECH 	90 	C90 	1152913	CE 										FUEL DRAIN	MISINSTALLED 	B			QMZR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	05	91TJ					LJ714				AT INSPECTION, THE ENGINE FUEL COLLECTOR TANK WAS REMOVED. IT WAS NOTED AT DISASSEMBLY, THE FLOAT SWITCH WAS INSTALLED 	UPSIDE DOWN, HOWEVER, IT WAS FUNCTIONING CORRECTLY. A NEW FLOAT SWITCH WAS PULLED FROM STOCK AND IT ALSO WOULD HAVE TO 	BE INSTALLED UPSIDE DOWN TO FUNCTION CORRECTLY. IF INSTALLED AS MARKED WITHOUT READING THROUGH THE SWITCH WIRING WITH A	 VOM, THE COLLECTOR TANK WOULD NOT FUNCTION PROPERLY. THE FLOAT SWITCH IN THE OPPOSITE ENGINE WAS CORRECT.			1	L	7	2 	3T				3A20 					 
1995080400637	19950804	00637		1995	8	4	95ZZZX3635 	1	19950330	G	2622	A1200	EXTINGUISHER 	SABER 																BOTTLE NECK	MOUNT WRONG 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	21					S835218					ON REPLACEMENT OF FIRE EXTINGUISHER DURING INSPECTION, FOUND NEW HALON 1211/1301 INCERDEX, INC., MODEL A1200, CAME WITH 	A MOUNT BRACKET WHICH WOULD NOT FIT AROUND NECK. VENDOR SAID BOTTLE MUST BE MOUNTED BACKWARDS IN BRACKET TO FIT. ON AI	RCRAFT WITH BOTTLE MOUNTS FORE AND AFT ON FLOOR, THE INSTALLATION MAY NOT CONFORM TO STATIC LOADS PER AC 43-13-2A, CHAPT	ER 1. INSTALLATION INSTRUCTION WITH UNIT DID NOT HAVE ENOUGH INFORMATION FOR PROPER AIRCRAFT INSTALLATION. EACH INSTAL	LATION SHOULD BE TESTED PER AC 43-13-2A OR WITH MOUNT BRACKET THAT FITS.															 
1995080400638	19950804	00638	GL 	1995	8	4	95ZZZX3636 	3	19950112	G	6110		COUNTERWEIGHT 			SLNSBY	T67 	T67M260 	8323006	EU 						HOFMAN	HOV123	HOV123KV 	GL 	PROPELLER	SLIPPED 	D				O				OTHER 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			SW	17	3045S	124 				2142		B704		COUNTERWEIGHTS ON PROPELLER BLADES SLIPPING. AIR CREW NOTICED INSTRUMENT'S VIBRATION DURING FLIGHT. ON GROUND, MAINTEN	ANCE CREW COULD NOT BALANCE PROPELLER. NOTICED COUNTERWEIGHTS HAD SLIPPED OUT OF ORIGINAL POSITION.					1	L	7	1 	3O			NT	A73EU 		5	C	P5EU2	 
1995080400639	19950804	00639		1995	8	4	95ZZZX3637 	4	19950706	G	6113	D4247	BULKHEAD 			BEECH 	23 	C23 	1151242	CE 										SPINNER	CRACKED 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	3829X	5 				M2306				DURING PROPELLER REMOVAL FOR ALTERNATOR BELT REPLACEMENT, FOUND CRACKS AT EACH BULKHEAD MOUNT BOLT HOLE. THIS REPAIR ST	ATION HAS REPLACED NUMEROUS D4247 BULKHEADS AT LOW INSTALL TIMES. SUBMITTER SUGGESTS CRACKS DUE TO POOR DESIGN AND MANU	FACTURE.				1	L	7	1 	3O				A1CE 					 
1995080400640	19950804	00640	GL 	1995	8	4	95ZZZX3638 	3	19950621	G	6111		BLADE 			CESSNA	150 	150L 	2071826	CE 						MCAULY	1A101	1A101DCM 	GL 	PROPELLER	TIP BROKEN 	G				A				UNSCHED LANDING 				E	D		VIBRATION/BUFFET 	INFLIGHT SEPARATION 		CR	CRUISE 	1			GL	03	6820G	3862 				15072320		9344		APPROXIMATELY 6 INCHES OF PROPELLER BLADE TIP SEPARATED FROM PROPELLER DURING FLIGHT. AIRCRAFT EXECUTED AN EMERGENCY LA	NDING. NO DAMAGE TO AIRCRAFT. A REVIEW OF AIRCRAFT MAINTENANCE RECORDS SHOWS HISTORY OF SUDDEN PROPELLER STOPPAGE.					1	H	7	1 	3O				3A19 		5	N	P918	 
1995080400641	19950804	00641	NE 	1995	8	4	95ZZZX3639 	2	19950525	G	7414	SB9RU3	MAGNETO 	BOSCH 		AIRTRC	AT300 	AT301 	0390103	SW 	PWA 	R1340 	R1340* 	52016	NE 					RT ENGINE	SHORTED 	D				K				NONE 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			SW	11	36552		900 			3010299				MAGNETO COVER ON RIGHT MAGNETO VIBRATED SCREWS LOOSE CAUSING COVER TO GROUND COIL KILLING MAGNETO WHICH CAUSED ENGINE FA	ILURE.					1	L	7	1 	3R	3	R		A9SW 	5E2				 
1995080400642	19950804	00642	EU 	1995	8	4	95ZZZX3640 	1	19950626	G	3230	GA543392	RAMP ASSY 		A237171 	AMD 	FALC20	FALCON20FS 	2730105	EU 										NLG DRG	CORRODED 	B			IY2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	20AE					258				DURING ROUTINE SERVICING/LUBE OF NLG DRAG STRUT, NOTICED AFTER LUBE, RAMP ASSY WAS PROTRUDING FROM PIN. DISASSEMBLED UN	IVERSAL JOINT OF DRAG STRUT AND FOUND RAMP ASSY CORRODED IN 2 PIECES. IN TURN, ALL PINS, UNIVERSAL JOINT, AND RAMP ASSY	'S WERE REPLACED DUE TO CORROSION. SUSPECT WATER INGRESS THROUGH RETAINING BOLT. RECOMMEND SEALING BOLT ENDS AND PERIO	DIC INSPECTIONS OF PINS AND RAMPS.			2	L	7	2 	4F			RT	A7EU 					 
1995080400643	19950804	00643	SW 	1995	8	4	95ZZZX3641 	1	19950712	G	2131	1306202EX	CONTROLLER 			GULSTM	560 	560 	0141402	SW 										CABIN	INOPERATIVE 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	60RD	721 			73B0002	5600244				PRESSURE CONTROLLER INOP. REPLACED CONTROLLER, SYSTEM OPERATES NORMALLY. NO FURTHER PROBLEMS.						1	H	7	2 	3O				6A1 					 
1995080400644	19950804	00644	CE 	1995	8	4	95ZZZX3642 	1	19950703	G	2410	08507299	BOLT 			BEECH 	35 	P35BEECH 	1151530	CE 										ALT MOUNT	BROKEN 	B			DSCR	K				NONE 				H			ELECT. POWER LOSS-50 PC 			IN	INSP/MAINT 	1			GL	25	32AB					D6974				ALCOR ALTERNATOR INSTALLATION, FIA/W STC SA334SW, MOUNTING BOLT BROKE AT THREADED AREA. BOLT APPEARS TO BE TOO SHORT FO	R APPLICATION, LOAD BEARING IS ON PORTION OF THREADED AREA RATHER THAN BOLT GRIP. SUGGEST STC BE AMENDED TO CALL OUT LO	NGER BOLT. FAILURE CAUSED TOTAL ACFT ELECTRICAL FAILURE.				1	L	7	1 	3O				3A15 					 
1995080400646	19950804	00646	CE 	1995	8	4	95ZZZX3644 	1	19950607	G	3230	08421022	BELLCRANK 			CESSNA	310 	310L 	2074230	CE 										GEAR RETRACT	BROKE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	3276X					310L0226				IDLER BELLCRANK BROKE FOR REASONS UNKNOWN AT THIS TIME.						1	L	7	2 	3O				3A10 					 
1995080400647	19950804	00647	CE 	1995	8	4	95ZZZX3645 	1	19950607	G	3230	08421211	BELLCRANK 			CESSNA	310 	310L 	2074230	CE 										GEAR RETRACT	BROKE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	3276X					310L0226				IDLER BELLCRANK BROKE FOR REASONS UNKNOWN AT THIS TIME.						1	L	7	2 	3O				3A10 					 
1995080400648	19950804	00648		1995	8	4	95ZZZX3646 	1	19950623	G	2922	53E19600	VALVE 								LYC 	O320 	O320E2D 	41508	EA 					THERMO BYPASS	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25										THE THERMOSTATIC OIL COOLER BYPASS VALVE WAS REPLACED AT OVERHAUL OF THE ENGINE BY CLYDESDALE AIRCRAFT. THE ENGINE WAS 	INSTALLED IN A CESSNA 172 SKYHAWK. A TEST FLIGHT SHOWED VERY HIGH OIL TEMP. THE OIL COOLER WAS COLD TO THE TOUCH. THE	 OIL BYPASS VALVE DID NOT OPEN. A NEW VALVE WAS INSTALLED, OIL TEMP WAS SATISFACTORY. THE DEFECTIVE VALVE WAS INK-STAM	PED, A1Q95. THE DEFECTIVE PART WAS RETURNED TO CLYDESDALE AIRCRAFT FOR WARRANTY. THIS VALVE IS USED ON OTHER LYC ENGIN	ES.							3	O			E274				 
1995080400649	19950804	00649	SO 	1995	8	4	95ZZZX3647 	1	19950627	G	8120	LW1277885	WASTEGATE 	GARRTT 	4708183 	PIPER 	PA31 	PA31350 	7103110	SO 										ACTUATOR DRAIN	OIL LOSS 	H				E				ENGINE SHUTDOWN 				K			FLUID LOSS 			NR	NOT REPORTED 	1			AL	01	3536B		2 		NLR0212	317952205				OIL LEAK FROM WASTEGATE ACTUATOR DRAIN. LOSS OF OIL NECESSITATED ENGINE SHUT-DOWN.						1	L	7	2 	3O				A20SO 					 
1995080400650	19950804	00650	CE 	1995	8	4	95ZZZX3648 	1	19950703	G	2841	813192	INDICATOR 	STWARNER 		CESSNA	206 	P206 	2073304	CE 										RT FUEL	FAILED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	4678F	27218				P2060278				INVESTIGATION OF THE PROBLEM WITH THE RIGHT FUEL GAUGE SHOWING FULL ALL THE TIME, REVEALED THE GAUGE ITSELF IS INOP. RE	PLACEMENT OF THE GAUGE ONLY, CORRECTED THE PROBLEM. THE GAUGE IS ORIGINAL EQUIPMENT AND THE AIRCRAFT IS A 1966 MODEL.					1	H	7	1 	3O				A4CE 					 
1995080400651	19950804	00651	SO 	1995	8	4	95ZZZX3649 	1	19950703	G	5230		LATCH 			PIPER 	PA34 	PA34200T 	7103406	SO 										BAG DOOR	DEFECTIVE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	36657					347870352				WHILE PERFORMING OTHER WORK ON THE AIRCRAFT, NOTED NOSE BAGGAGE DOOR LATCH WAS UNAIRWORTHY PER AD 88-04-05 WHICH HAD BEE	N P/C/W. LATCH MECHANISM WAS WORN TO EXTENT THAT LOCK WOULD TURN AND KEY COULD BE REMOVED EVEN WITH LATCH IN 'OPEN' POS	ITION. PIPER SB 633B AND SB 872 ADDRESS THIS. SUBMITTER RECOMMENDS REVISE AD NOTE TO REQUIRE REPETITIVE INSPECTIONS.				1	L	7	2 	3O				A7SO 					 
1995080400652	19950804	00652	EA 	1995	8	4	95ZZZX3650 	2	19950613	G	7414	K3823	DISTRIBUTOR 	SLICK 	6250 	PIPER 	PA32 	PA32* 		SO 	LYC 	O540 	IO540K1G5 	41532	EA 					MAG	BLOCK DESTROYED 	B			BF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05		30 								DISMANTLED MAG FOUND DISTRIBUTOR OR BEARING BLOCK DESTROYED BY ARCING FROM DEFECTIVE COIL.						1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995080400653	19950804	00653	CE 	1995	8	4	95ZZZX3651 	1	19950609	G	2410	76906	BRACKET 			CESSNA	172 	172L 	2072432	CE 										ALT MOUNT	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	7945G	4173 				17259645				UPON ROUTINE INSPECTION, FOUND BRACKET BROKEN COMPLETELY THROUGH ACROSS AFT BOLT HOLE. SUBMITTER SUGGESTS LYC MANUFACTU	RE BRACKET WITH GUSSETS ACROSS CORNERS. LYC NEW P/N 07A21443 STILL SAME AS OLD P/N 76906 DIMENSIONALLY.					1	H	7	1 	3O			NT	3A12 					 
1995080400654	19950804	00654	SO 	1995	8	4	95ZZZX3652 	1	19950703	G	3211	6704015	FITTING 			PIPER 	PA34 	PA34200T 	7103406	SO 										RT MLG TRUNNION	BOLTS LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	666HL	11400				347770235				FOLLOWING GEAR INDICATION PROBLEM, FOUND RIGHT FORWARD MAIN GEAR TRUNNION FITTING BOLTS LOOSE. RECURRING PROBLEM ADDRES	SED BY PIPER SB 956. SUBMITTER RECOMMENDS UPGRADE THIS BULLETIN TO AIRWORTHINESS DIRECTIVE.					1	L	7	2 	3O				A7SO 					 
1995080400655	19950804	00655	SO 	1995	8	4	95ZZZX3653 	2	19950703	G	8530		CYLINDER 			CESSNA	404 	404CESSNA 	2075901	CE 	CONT 	O520 	GTSIO520M 	17032	SO 					LT ENG NR 3	CRACKED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	41SA	1298 				4040023	276274R			LEFT ENGINE NR 3 CYLINDER CRACKED AT BOTH SPARKPLUG HOLES. SUBMITTER KNOWS OF MANY EXAMPLES OF IDENTICAL FAILURES THROU	GHOUT FLEET AIRCRAFT.					1	L	7	2 	3O	3	O		A25CE 	E7CE				 
1995080400656	19950804	00656	EA 	1995	8	4	95ZZZX3654 	2	19950712	G	7322	HA6	CARBURETOR VALVE			CESSNA	172 	172RG 	2072438	CE 	LYC 	O360 	O360F1A6 	41514	EA 					CONTROL ARM	SEIZED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	5210V		20 			172RG0471	L2854136A			PILOT REPORTED THROTTLE WOULD NOT MOVE FROM IDLE AFTER START. REMOVED CARBURETOR, FOUND CONTROL ARM SEIZED. REPLACED C	ARBURETOR UNDER WARRANTY. SENT CARBURETOR TO PRECISION AIRMOTIVE FOR WARRANTY/PROBLEM INSPECTION.					1	H	7	1 	3O	3	O		3A17 	E286				 
1995080400657	19950804	00657	EU 	1995	8	4	95ZZZX3655 	1	19950619	G	2432	106481	BATTERY 			HWKSLY	DH125 	HS125600A 	4230158	EU 										DC SYSTEM	COVER MELTED 	D				K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			CE	09	600G				830	256066				BATTERY PACK COVER MELTED AROUND TERMINAL POSTS. THIS CONDITION CAUSED BY LOOSE/HIGH RESISTANCE CONNECTION BETWEEN TERM	INAL POSTS AND CELL TABS. SUBMITTER RECOMMENDS MANUFACTURER USE THICKER MATERIAL FOR COVER PERHAPS OF A PHENOLIC AS THE	Y USED TO DO IN PREVIOUS YEARS. EARLIER PACKS ALSO INCORPORATED A SCREW AND JAM NUT CONFIGURATION TO MAINTAIN A SECURE 	CONNECTION.			2	L	7	2 	4J				A3EU 					 
1995080400658	19950804	00658	SO 	1995	8	4	95ZZZX3656 	1	19950628	G	5751	4019000	SPAR 			PIPER 	PA31 	PA31 	7103102	SO 										AILERON	CRACKED 	B			RMMR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	83RA	9970 				31638				DURING COMPLIANCE WITH PIPER SB 974, DYE PENETRANT INSPECTION OF THE INBOARD HINGE AREA OF THE LEFT AILERON SPAR INDICAT	ED A CRACK. INSPECTION WAS REPEATED WITH SAME RESULT. NOTE: THIS CRACK WAS NOT VISIBLE DURING VISUAL INSPECITON. SPA	R WAS REPLACED AND SERVICE BULLETIN COMPLETED.				1	L	7	2 	3O				A20SO 					 
1995080400744	19950804	00744	SO 	1995	8	4	95ZZZX3657 	2	19950627	G	8530		CYLINDER 			CESSNA	310 	310P 	2074238	CE 	CONT 	O470 	IO470VO 	17026	SO 					RT ENG NR 4	EXITED 	D				A	E			UNSCHED LANDING 	ENGINE SHUTDOWN 			E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			WP	25	5819M		8 			310P00119	1487209V			THE AIRCRAFT MADE AN EMERGENCY LANDING WITH THE RIGHT ENGINE FEATHERED. THE COPILOT HAD NOTED NR 4 CYLINDER EXIT THROUG	H THE SIDE COWLING IN A DOWNWARD DIRECTION. THE CONNECTING ROD WAS STILL ON THE CRANK, BENT SLIGHTLY AFT AND THE PISTON	 PIN BOSS WAS ELONGATED. ALL HOLD-DOWNS WERE BROKEN OFF.				1	L	7	2 	3O	3	O		3A10 	3E1				 
1995080400745	19950804	00745	EA 	1995	8	4	95ZZZX3658 	2	19950705	G	8530	73806	PUSHROD 			BEECH 	77 	77 	1153007	CE 	LYC 	O235 	O235L2C 	41505	EA 					ENGINE	FAILED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	17	38025	1491 				TH1208	L2167815			PUSHROD FAILED AND WAS NOT MARKED WITH THE PROPER P/N PER THE A.O. 80-25-02 LYCOMING ADVISED THAT THE PROPER PUSHRODS WE	RE INSTALLED DURING ORIGINAL ASSEMBLY. ALL PUSHRODS REMOVED AND INSPECTED. ALL FOUND TO HAVE THE WRONG P/N. NO RECORD	S OF THE PUSHRODS BEING REPLACED.				1	L	7	1 	3O	3	O		A30CE 	E223				 
1995080400746	19950804	00746	SO 	1995	8	4	95ZZZX3659 	1	19950622	G	5102		EYEBOLT 			BALWKS	FIREFY	FIREFLY* 		SO 										DEFLATE SYS	FAILED 	B	L		WD3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	2559V					F11002				DURING ATTEMPTED DEFLATION OF BALLOON AT CONCLUSION OF A PAID PASSENGER FLIGHT, THE EYEBOLT WHICH RETAINS ONE OF TWO DEF	LATION LINE PULLEYS BROKE. THE PILOT WAS DEPRIVED OF THE PULLEY'S EFFECT OF REDUCING THE EFFORT AND/OR STRENGTH REQUIRE	D TO DEFLATE THE BALLOON. DEFLATION WAS ACCOMPLISHED ONLY OVER A LONG PERIOD OF TIME, WITH THREE MEN. FORTUNATELY, WIN	DS WERE LIGHT. A HIGH-WIND LANDING WOULD BE DANGEROUS WITHOUT THE MECHANICAL ADVANTAGE OF THE PULLEY SYSTEM.			1	B	0	0 					A14SO 					 
1995080400747	19950804	00747	SO 	1995	8	4	95ZZZX3660 	2	19950628	G	8550	CH48108	FILTER 	CHAMPION 		CESSNA	340 	340A 	2076405	CE 	CONT 	O520 	TSIO520N 	17040	SO 					RT ENG OIL	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	4116G					340A0288				AFTER CUTTING OPEN FILTER FOR INSPECTION, DISCOVERED THE OUTLET END FATIGUED WITH 2 SECTIONS OF THE METAL LIP LODGED DOW	N INSIDE THE FILTER. THE REMAINING PORTION OF THE LIP WAS SPRINGY AND READY TO RELEASE (RIGHT ENGINE).					1	L	7	2 	3O	3	O		3A25 	E8CE				 
1995080400748	19950804	00748	SO 	1995	8	4	95ZZZX3661 	2	19950628	G	8550	CH48108	FILTER 			CESSNA	340 	340A 	2076405	CE 	CONT 	O520 	TSIO520N 	17040	SO 					LT ENG OIL	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	4116G					340A0288				AFTER CUTTING OPEN FILTER FOR INSPECTION, DISCOVERED THE OUTLET SEAL DEFORMED AND PARTIALLY DISLODGED FROM SEALING LIP (	LEFT ENGINE).					1	L	7	2 	3O	3	O		3A25 	E8CE				 
1995080400749	19950804	00749	EA 	1995	8	4	95ZZZX3662 	2	19950706	G	8530		CYLINDER 			PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E2A 	41508	EA 					NR 4	WORN 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	67WA	5724 	1247 			287125267	L2935627A			NR 4 CYLINDER FOUND TO HAVE CHOKE BORE OUT OF TOLERANCE. SUSPECT CAUSE FOUND TO BE 2 INCH SCAT HOSE COLLAPSED BLOCKING 	OFF COOLING AIR.					1	L	7	1 	3O	3	O		2A13 	E274				 
1995080400750	19950804	00750	EA 	1995	8	4	95ZZZX3663 	2	19950502	G	7322	105199	JET NOZZLE 	FACET 	MA3A 	PIPER 	PA38 	PA38112 	7103812	SO 	LYC 	O235 	O235L2C 	41505	EA 					CARBURETOR	CLOGGED 	H				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			SW	17	2482A	2141 			CR03272	3878A0706	L1711615			AIRCRAFT WAS FORCED TO MAKE AN EMERGENCY LANDING DUE TO LOSS OF POWER. UPON INSPECTION OF ENGINE, NOTED THE CARBURETOR 	WAS FOUND TO HAVE THE JET NOZZLE CLOGGED. SUBMITTER SUGGESTED THE LOSS OF POWER WAS DUE TO THE INSUFFICIENT FLOW OF FUE	L.				1	L	7	1 	3O	3	O		A18SO 	E223				 
1995080400751	19950804	00751	CE 	1995	8	4	95ZZZX3664 	1	19950516	G	2434	DOFF10300J	ALTERNATOR 	FORD 		CESSNA	185 	A185F 	2072821	CE 										ENG COMPT	BEARING FOILED 	G				O				OTHER 				A	H		FLAME/FIRE 	ELECT. POWER LOSS-50 PC 		NR	NOT REPORTED 	1			SW	03	1769R		151 		3061359	18502489				THE ALTERNATOR BEARING FAILED DURING FLIGHT AND FILLED THE COCKPIT WITH A SMOKE ODOR. THE ALTERNATOR HAD ACCUMULATED 25	1 HOURS SINCE OVERHAUL.					1	H	7	1 	3O				3A24 					 
1995080400752	19950804	00752	EA 	1995	8	4	95ZZZX3665 	2	19950626	G	7322		CONTROL BOLT 			CESSNA	177 	177 	2073704	CE 	LYC 	O320 	O320D2A 	41508	EA 					THROTTLE	DETACHED 	D				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			WP	23	3420T	3934 				17700720	L2095127AC			AT ABOUT 700 FEET ALTITUDE AFTER DEPARTURE, ENGINE WENT TO IDLE. AFTER A SUCCESSFUL OFF AIRPORT LANDING WAS MADE, BOLT 	AND HARDWARE CONNECTING THROTTLE CONTROL TO CARBURETOR WERE FOUND MISSING. INSTALLED NEW BOLT, NUT, SPACER, AND WASHERS	. AIRCRAFT TOWED TO A ROAD AND WITH CHP PERMISSION, RETURNED TO AIRPORT. SUBMITTER STATED BOLT AND CASTELLATED NUT HAD	 PROBABLY BEEN OVERTORQUED. MAYBE MANY TIMES IN PAST. SUBMITTER SUGGESTS REPLACING AT OVERHAUL AND DO NOT OVERTORQUE.			1	H	7	1 	3O	3	O	NT	A13CE 	E274				 
1995080400753	19950804	00753	SO 	1995	8	4	95ZZZX3666 	1	19950614	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	NUT MISSING 	B			APJR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	35551		892 			318052063				DURING ANNUAL INSPECTION, LYCOMING SB 518C WAS C/W. UPON REMOVAL OF THERMOSTATIC BYPASS VALVE ON THE RIGHT ENGINE, THE 	CRIMP NUT HAD SEPARATED FROM THE VALVE ASSEMBLY. A SEARCH WAS CONDUCTED AND THE CRIMP NUT WAS LOCATED IN THE INLET SIDE	 OF THE OIL COOLER. THE NEW REPLACEMENT BYPASS VALVE, PN SL53E19600, NOW CONTAINS A ROLL PIN TO SECURE THE CRIMP NUT IN	 PLACE. THE BYPASS VALVE ON THE LEFT ENGINE WAS INSPECTED AND FOUND SERVICEABLE. DUE TO BACKORDERS ON THIS VALVE, THE 	LEFT VALVE HAS NOT BEEN CHANGED AT THIS TIME.		1	L	7	2 	3O				A20SO 					 
1995080400754	19950804	00754	GL 	1995	8	4	95ZZZX3667 	3	19950531	G	6114	D5892C93	HUB 													MCAULY	3AF32C	3AF32C93 	GL 	NR 2 SOCKET	CRACKED 	B			ME4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19								797439		DISASSEMBLED PROPELLER HUB RECEIVED FOR OVERHAUL. AFTER INSPECTION, HUB CRACKED IN NR 2 HUB SOCKET FROM 3:00 TO 6:00 PO	SITION. CRACK DISCOVERED USING A 10X POWER MICROSCOPE. HUB SCRAPPED.															5	C	P22EA	 
1995080400755	19950804	00755	NM 	1995	8	4	95ZZZX3668 	1	19950706	G	7922	759444	VALVE 			PIPER 	PA60 	PA60601P 	7106012	NM 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	73PT				96123	61P063579632				INSPECTION OF BYPASS VALVE IAW SB 518C REVEALED THE CRIMP NUT WAS LOOSE. VALVE WAS REPLACED. RECOMMEND MANDATORY REPLA	CEMENT OF DEFECTIVE VALVES.					1	M	7	2 	3O			RT	A17WE 					 
1995080400756	19950804	00756	NM 	1995	8	4	95ZZZX3669 	1	19950705	G	7922	75944	VALVE 			PIPER 	PA60 	PA60601P 	7106012	NM 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	73PT				94296	61P063579632				INSPECTION OF BYPASS VALVE IAW SB 518C REVEALED THE CRIMP NUT WAS LOOSE. VALVE REPLACED. RECOMMEND MANDATORY REPLACEME	NT OF DEFECTIVE VALVES.					1	M	7	2 	3O			RT	A17WE 					 
1995080400757	19950804	00757	GL 	1995	8	4	95ZZZX3670 	3	19950531	G	6114	D5892C93	HUB 													MCAULY	3AF32C	3AF32C93 	GL 	NR 1 SOCKET	CRACKED 	B			ME4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19								752264		DISASSEMBLED PROPELLER HUB RECEIVED FOR OVERHAUL. AFTER INSPECTION, HUB FOUND CRACKED IN NR 1 HUB SOCKET FROM 1:00 TO 3	:00 POSITION. CRACK DISCOVERED USING A 10X POWER MICROSCOPE. HUB SCRAPPED.															5	C	P22EA	 
1995080400758	19950804	00758	GL 	1995	8	4	95ZZZX3671 	3	19950531	G	6114	D5892C93	HUB 													MCAULY	3AF32C	3AF32C93 	GL 	NR 2 SOCKET	CRACKED 	B			ME4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19								783310		DISASSEMBLED PROPELLER HUB RECEIVED FOR OVERHAUL. AFTER INSPECTION, HUB FOUND CRACKED IN NR 2 HUB SOCKET, FROM 2:00 TO 	4:00 POSITION. CRACK DISCOVERED USING A 10X POWER MICROSCOPE. HUB SCRAPPED.															5	C	P22EA	 
1995080400759	19950804	00759	GL 	1995	8	4	95ZZZX3672 	3	19950607	G	6114	D5892C87	HUB 			CESSNA	402 	402B 	207590P	CE 						MCAULY	3AF32C	3AF32C87 	GL 	NR 1 SOCKET	CRACKED 	B			ME4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	9063M		1486 			402B0245		792461		PROPELLER WAS RECEIVED FOR 5-YEAR OVERHAUL. AFTER A HUB INSPECTION, NR 1 BLADE SOCKET, BETWEEN 2 AND 4 O'CLOCK POSITION	, 5 THREADS IN, WAS DISCOVERED CRACKED APPROXIMATELY 3 INCHES LONG. THE CRACK WAS DISCOVERED USING A 20X POWERED MICROS	COPE. HUB WAS SCRAPPED.				1	L	7	2 	3O				A7CE 		5	C	P22EA	 
1995080400760	19950804	00760	CE 	1995	8	4	95ZZZX3673 	1	19950609	G	2730	NAS561P38	PIN 			CESSNA	185 	185 	2072802	CE 										TRIM WHEEL	SHEARED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	93943	1489 				18503267				NOTED TRIM WHEEL COULD BE TURNED WITHOUT CHAIN OR SPROCKET MOVEMENT APPROXIMATELY 2 CLICKS OF TENSIONER. DISASSEMBLED W	HEEL, SHAFT, AND SPROCKET AND FOUND ROLL PIN SECURING SPROCKET TO SHAFT IN 3 PIECES. SAFETY WIRE WAS HOLDING TOGETHER E	NOUGH THAT TRIM STILL WORKED. SUBMITTER SUGGESTED CLOSE ATTENTION NEEDS TO BE USED TO DETECT PROBLEM.				1	H	7	1 	3O			NC	3A24 					 
1995080400761	19950804	00761	SO 	1995	8	4	95ZZZX3674 	2	19950716	G	8520		CRANKCASE 			BEECH 	55 	E55 	1152732	CE 	CONT 	O520 	IO520C 	17032	SO 					ENGINE	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	99	91WC	3016 	300 			TE909	231829R			AIRCRAFT HAS SEVERAL OIL LEAKS ON RT ENGINE FINALLY RESULTING IN CRACKED CASE. SUSPECT THAT WHEN TEAR DOWN IS DONE, CRA	NK HAS COUNTERWEIGHT PROBLEM. THIS IS THE THIRD ENGINE THIS YEAR TO REJECT DUE TO CRANK PROBLEMS. SUBMITTER STATED MAY	BE ENGINE OVERHAUL SHOULD REQUIRE CLOSER CRANK OVERHAUL INSPECTION FOR BUSHING REPLACMENT, 300 TSO.				1	L	7	2 	3O	3	O		3A16 	E5CE				 
1995080400762	19950804	00762	SO 	1995	8	4	95ZZZX3675 	2	19950705	G	8520		CRANKCASE 			BEECH 	55 	95B55 	1152706	CE 	CONT 	O470 	IO470L 	17026	SO 					NR 6 CYL THRU	BOLT SEPARATED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	96NL					TC721	297553R			DURING A SCHEDULED INSPECTION, THE LOWER FORWARD CRANKCASE THROUGH-BOLT ON NR 6 CYLINDER WAS FOUND COMPLETELY SEPARATED.	 FURTHER INSPECTION FOUND THE BOLT IMPROPERLY INSTALLED. THE BOLT FAILED IN THE O-RING GROOVE LOCATED IN THE MIDDLE PO	RTION OF THE BOLT. THIS ENGINE WAS A FACTORY REMANUFACTURE WITH 77.2 HRS SINCE INSTALLED ON THIS AIRCRAFT, P/N 64193198	1.			1	L	7	2 	3O	3	O		3A16 	3E1				 
1995080400763	19950804	00763	CE 	1995	8	4	95ZZZX3676 	1	19950703	G	5711		SPAR 			BEECH 	58 	58 	1152740	CE 										REAR SPAR	UNMARKED 	B			SJ7R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	01	391MC					TH756				AIRCRAFT RECENTLY WAS PAINTED. FOUND AD 91-17-01 'PAINTING REAR SPAR' HAD BEEN PAINTED EVEN THOUGH PREVIOUSLY COMPLIED 	WITH. REPAINTED ACTUATORS AT REAR SPAR PER AD. ALSO, LOOKED AT AN A36 RECENTLY PAINTED (DIFFERENT PAINT SHOP) FOUND AL	SO UNMARKED. SUGGEST PAINT SHOPS BE ADVISED TO REMARK AS FOUND AND ADVISE ALL LICENSED PEOPLE RESPONSIBLE FOR SAID AIRC	RAFT TO BE ALERTED.			1	L	7	2 	3O				3A16 					 
1995080400764	19950804	00764	EA 	1995	8	4	95ZZZX3677 	2	19950509	G	7322	MA3A	CARBURETOR 	FACET 		PIPER 	PA22 	PA22108 	7102204	SO 	LYC 	O235 	O235C1B 	41505	EA 					METERING SLEEVE	CLOGGED 	D				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			NE	05	5967Z					229839				AIRCRAFT ENGINE EXPERIENCED POWER LOSS. PILOT ATTEMPTED TO REGAIN POWER BY SWITCHING FUEL TANKS, APPLYING CARBURETOR HE	AT AND STANDARD EMERGENCY PROCEDURES WERE FOLLOWED. A SAFE OFF AIRPORT LANDING WAS MADE. UPON DISASSEMBLY OF CARBURETO	R, VERY SMALL PIECE OF WHAT APPEARS TO BE GASKET MATERIAL WAS FOUND IN THE FUEL METERING SLEEVE. AIRCRAFT WAS STC'D AND	 APPROVED FOR AUTOMOTIVE FUEL. CARBURETOR WAS DRAINED DURING ANNUAL 5 MONTHS PREVIOUS. NO OTHER TRACES OF ANY FOREIGN 	DEBRIS WERE FOUND IN THE CARBURETOR OR FINGER SCREEN.		1	H	7	1 	3O	3	O		1A6 	E223				 
1995080400765	19950804	00765	SO 	1995	8	4	95ZZZX3678 	2	19950618	G	8550		PUMP 			BEECH 	36 	A36TC 	1151603	CE 	CONT 	O520 	TSIO520UB 	17040	SO 					ENGINE SCAVAGE	GEAR FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	25LR	1300 				EA196	515753			SCAVAGE PUMP DRIVE GEAR FRACTURED IN 4 LOCATIONS FOLLOWING HEAVY WEAR OF TOOTH PROFILE. TOTAL ENGINE FAILURE FOLLOWED. 	 AD 89-24-01R1 AND SB M90-6 PERTAIN TO THIS PUMP, BUT WERE NOT DUE YET.					1	L	7	1 	3O	3	O		3A15 	E8CE				 
1995080400766	19950804	00766	CE 	1995	8	4	95ZZZX3679 	1	19950613	G	5350		ROOT SEAL 			BEECH 	33 	F33A 	1151425	CE 										WING	DETACHED 	C		A		A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			EA	23	28SH					CE758				ON ROUTINE DAY IFR FLIGHT IN VFR CONDITIONS, A FEW MONTHS AFTER AIRCRAFT HAD BEEN REPAINTED, A LOUD DRUMMING NOISE AND V	IBRATION WAS FELT AND HEARD. IT WAS SIMILAR TO WHAT MIGHT BE EXPECTED IF A SEATBELT WAS CAUGHT OUTSIDE THE DOOR IN THE 	SLIPSTREAM OR WHEN AN OLD-STYLE ADF WIRE ANTENNA BREAKS IN-FLIGHT. AFTER A ROUTINE LANDING, THE CULPRIT WAS DISCOVERED 	TO BE THE WING ROOT RUBBER SEAL WHICH HAD DETACHED ITSELF FROM THE WING UNDERSIDE. IT IS NORMALLY CEMENTED IN PLACE UND	ER THE WING BUT HAD OBVIOUSLY BEEN POORLY RE-INSTALLED AFTER PAINTING. THE LOOSE END BEAT AGAINST THE AIRPLANE SKIN SO 	HARD THAT IT OPENED THE BELLY DRAIN DOOR AND BENT ITS HINGE, AS WELL AS LEAVING RUBBER SKID MARKS ALL OVER THE PAINT.	1	L	7	1 	3O				3A15 					 
1995080400767	19950804	00767	EA 	1995	8	4	95ZZZX3680 	2	19950619	G	7322	105135	CARBURETOR JET 	FACET 	MA4SPA 	CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					ENGINE	BLOCKED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	06	5415J		1248 		CT610931	17273785				TEAR DOWN OF CARBURETOR TO IDENTIFY REASON FOR FAILURE. MAIN JET ASSEMBLY WAS FOUND PARTIALLY BLOCKED. BLOCKAGE REMOVE	D USING A .040 INCH PIECE OF SAFETY WIRE PASSED THROUGH THE OUTLET END OF THE MAIN JET ASSEMBLY.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995080400768	19950804	00768	NM 	1995	8	4	95ZZZX3681 	1	19950727	G	5720	5723113022	FITTING 			BOEING	707 	707338C 	138367N	NM 										RT WING OTBD AFT	CRACKED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5265J					19621				WHILE PERFORMING NDT AS PRESCRIBED ON BOEING SB A3308R3 TO C/W AD81-06-51R1. FOUND FITTING WITH CORROSION AND CRACKS BE	YOND THE MAX ALLOWED LIMITS PER SB. REPLACED FITTING. ATT 55,690.7 AND ATC 19,388.					2	L	7	4 	4F				4A26 					 
1995080400769	19950804	00769	NM 	1995	8	4	95ZZZX3682 	1	19950727	G	5720	5723113028	FITTING 			BOEING	707 	707338C 	138367N	NM 										RT WING OTBD FWD	CORRODED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5265J					19621				WHILE PERFORMING NDT AS PRESCRIBED ON BOEING SB A3308R3 TO C/W AD81-06-51R1. FOUND FITTING WITH CORROSION AND CRACKS BE	YOND THE MAX ALLOWED LIMITS PER SB. REPLACED FITTING. ATT 55,690.7 AND ATC 19,388.					2	L	7	4 	4F				4A26 					 
1995080400770	19950804	00770	NM 	1995	8	4	95ZZZX3683 	1	19950727	G	5720	50822116	FITTING 			BOEING	707 	707338C 	138367N	NM 										RT WING INBD AFT	CRACKED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5265J					19621				WHILE PERFORMING NDT AS PRESCRIBED ON BOEING SB A3308R3 TO C/W AD81-06-51R1. FOUND FITTING WITH CORROSION AND CRACKS BE	YOND THE MAX ALLOWED LIMITS PER SB. REPLACED FITTING. ATT 55,690.7 AND ATC 19,388.					2	L	7	4 	4F				4A26 					 
1995080400771	19950804	00771	NM 	1995	8	4	95ZZZX3684 	1	19950727	G	5720	50822146	FITTING 			BOEING	707 	707338C 	138367N	NM 										RT WING INBD FWD	CORRODED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5265J					19621				WHILE PERFORMING NDT AS PRESCRIBED ON BOEING SB A3308R3 TO C/W AD81-06-51R1. FOUND FITTING WITH CORROSION AND CRACKS BE	YOND THE MAX ALLOWED LIMITS PER SB. REPLACED FITTING. ATT 55,690.7 AND ATC 19,388.					2	L	7	4 	4F				4A26 					 
1995080400772	19950804	00772	NM 	1995	8	4	95ZZZX3685 	1	19950727	G	5720	5723113021	FITTING 			BOEING	707 	707338C 	138367N	NM 										LT WING OTBD AFT	CORRODED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5265J					19621				WHILE PERFORMING NDT AS PRESCRIBED ON BOEING SB A3308R3 TO C/W AD81-06-51R1. FOUND FITTING WITH CORROSION AND CRACKS BE	YOND THE MAX ALLOWED LIMITS PER SB. REPLACED FITTING. ATT 55,690.7 AND ATC 19,388.					2	L	7	4 	4F				4A26 					 
1995080400773	19950804	00773	NM 	1995	8	4	95ZZZX3686 	1	19950727	G	5720	5723113027	FITTING 			BOEING	707 	707338C 	138367N	NM 										LT WING OTBD FWD	CRACKED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5265J					19621				WHILE PERFORMING NDT AS PRESCRIBED ON BOEING SB A3308R3 TO C/W AD81-06-51R1. FOUND FITTING WITH CORROSION AND CRACKS BE	YOND THE MAX ALLOWED LIMITS PER SB. REPLACED FITTING. ATT 55,690.7 AND ATC 19,388.					2	L	7	4 	4F				4A26 					 
1995080400774	19950804	00774	NM 	1995	8	4	95ZZZX3687 	1	19950727	G	5720	50822195	FITTING 			BOEING	707 	707338C 	138367N	NM 										LT WING OTBD FWD	CRACKED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5265J					19621				WHILE PERFORMING NDT AS PRESCRIBED ON BOEING SB A3308R3 TO C/W AD81-06-51R1. FOUND FITTING WITH CORROSION AND CRACKS BE	YOND THE MAX ALLOWED LIMITS PER SB. REPLACED FITTING. ATT 55,690.7 AND ATC 19,388.					2	L	7	4 	4F				4A26 					 
1995080400775	19950804	00775	NM 	1995	8	4	95ZZZX3688 	1	19950727	G	5720	50822115	FITTING 			BOEING	707 	707338C 	138367N	NM 										LT WING INBD AFT	CORRODED 	B			G2LR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5265J					19621				WHILE PERFORMING NDT AS PRESCRIBED ON BOEING SB A3308R3 TO C/W AD81-06-51R1. FOUND FITTING WITH CORROSION AND CRACKS BE	YOND THE MAX ALLOWED LIMITS PER SB. REPLACED FITTING. ATT 55,690.7 AND ATC 19,388.					2	L	7	4 	4F				4A26 					 
1995080400776	19950804	00776	SO 	1995	8	4	95ZZZX3689 	1	19950630	G	5730	1159WM30001	PLANK 			GULSTM	G1159 	G1159A 	3970109	SO 										RT WING	CORRODED 	B			BTVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	2FOR	5418 				304				DURING A ROUTINE 72-MONTH INSPECTION OF THE UPPER RIGHT WING SURFACE UNDER THE 'WING WEDGE', A FAIRLY LARGE (5.5 INCH BY	 1.0 INCH) AREA OF INTERGRANULAR, EXFOLIATION-TYPE CORRISION WAS FOUND. THIS AREA IS SUPPOSED TO BE TREATED WITH A CORR	OSION INHIBITING COMPOUND (COSMOLINE), HOWEVER, THIS AREA WAS DRY. SUBMITTER STATED THIS WOULD APPEAR TO BE THE APPAREN	T CAUSE OF THE PROBLEM. GULFSTREAM HAS BEEN NOTIFIED AND IS ASSISTING IN REPAIRS.			2	L	7	2 	4F				A12EA 					 
1995080400777	19950804	00777	CE 	1995	8	4	95ZZZX3690 	1	19950707	G	2913	66003013	PUMP 			LEAR 	55 	55C 	5170706	CE 										NR 1 ENG HYD	SHAFT STRIPPED 	B			NV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	40CR	1387 			250482	144				NR 1 ENGINE DRIVEN HYDRUALIC PUMP SHAFT WAS COMPLETELY STRIPPED OF ALL GEAR MATING SURFACE AREA RESULTING IN NO HYDRAULI	C OUTPUT FROM THAT ENGINE. FOUND ON INITIAL ENGINE HOT SECTION INSPECTION.					2	L	7	2 	4F			RT	A10CE 					 
1995081100081	19950811	00081		1995	8	11	95ZZZX3691 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14848					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100082	19950811	00082		1995	8	11	95ZZZX3692 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C18389					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100083	19950811	00083		1995	8	11	95ZZZX3693 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C14567					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100084	19950811	00084		1995	8	11	95ZZZX3694 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					25791					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100085	19950811	00085		1995	8	11	95ZZZX3695 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					11775					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100086	19950811	00086		1995	8	11	95ZZZX3696 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					13736					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100087	19950811	00087		1995	8	11	95ZZZX3697 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					55139					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100088	19950811	00088		1995	8	11	95ZZZX3698 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					15797					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100089	19950811	00089		1995	8	11	95ZZZX3699 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					53418					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100090	19950811	00090		1995	8	11	95ZZZX3700 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					33827					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100091	19950811	00091		1995	8	11	95ZZZX3701 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					94584					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100092	19950811	00092		1995	8	11	95ZZZX3702 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14532					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100093	19950811	00093		1995	8	11	95ZZZX3703 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					30525					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100094	19950811	00094		1995	8	11	95ZZZX3704 	4	19950619	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					13297					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100095	19950811	00095		1995	8	11	95ZZZX3705 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					42152					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100096	19950811	00096		1995	8	11	95ZZZX3706 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					11007					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100097	19950811	00097		1995	8	11	95ZZZX3707 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					98762					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100098	19950811	00098		1995	8	11	95ZZZX3708 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					37403					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100099	19950811	00099		1995	8	11	95ZZZX3709 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					29008					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100100	19950811	00100		1995	8	11	95ZZZX3710 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C15775					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100101	19950811	00101		1995	8	11	95ZZZX3711 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					33245					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100102	19950811	00102		1995	8	11	95ZZZX3712 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					55684					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100103	19950811	00103		1995	8	11	95ZZZX3713 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					17826					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100104	19950811	00104		1995	8	11	95ZZZX3714 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					CA23745					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100105	19950811	00105		1995	8	11	95ZZZX3715 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					90333					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100106	19950811	00106		1995	8	11	95ZZZX3716 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					12533					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100107	19950811	00107		1995	8	11	95ZZZX3717 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					55308					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100108	19950811	00108		1995	8	11	95ZZZX3718 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					77098					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100109	19950811	00109		1995	8	11	95ZZZX3719 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					45094					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100110	19950811	00110		1995	8	11	95ZZZX3720 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					67463					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100111	19950811	00111		1995	8	11	95ZZZX3721 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					15419					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100112	19950811	00112		1995	8	11	95ZZZX3722 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C16976					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100113	19950811	00113		1995	8	11	95ZZZX3723 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14674					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100114	19950811	00114		1995	8	11	95ZZZX3724 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A23590					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100115	19950811	00115		1995	8	11	95ZZZX3725 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					17542					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100116	19950811	00116	SO 	1995	8	11	95ZZZX3726 	1	19950622	G	2150	1159AC20073101	DOOR ASSY 			GULSTM	G1159 	G1159 	3953505	SO 										AIR COND RAM	CRACKED 	B			WLCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	7155P	7751 				169				FOUND HINGE ASSY CRACKED LONGITUDINALLY IN SEVERAL PLACES DURING PRE-FLIGHT INSPECTION. UPON FURTHER INVESTIGATION AND 	DISASSEMBLY, THE DOOR WAS FOUND CRACKED, ALSO, FROM A RIVET HOLE INWARDS TOWARD THE CENTER OF THE DOOR. THIS PART IS C	ALLED OUT AS PART OF THE TAIL COMPARTMENT ABOVE FLOOR INSPECTION. SUBMITTER SUGGESTS A MORE DETAILED INSPECTION SHOULD 	BE EMPHASIZED BY GAC. ALSO, A HEAVIER DUTY HINGE ASSY MIGHT BE THE CURE FOR THIS PROBLEM.			2	L	7	2 	4F			RT	A12EA 					 
1995081100117	19950811	00117	WP 	1995	8	11	95ZZZX3727 	2	19950630	G	7260	30753562	ADAPTER SPLINE 			CESSNA	650 	650 	2076802	CE 	GARRTT	TFE731	TFE731* 	01518	WP 					RT ENGINE	STRIPPED 	B			GMCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	5111	440 				6507011	102124			RIGHT ENGINE WOULD NOT ROTATE WHEN STARTER BUTTON ENGAGED. FOUND OUTER SPLINES ON ADAPTER STRIPPED. LEFT ENGINE SPLINE	 ADAPTER ALSO WORN EXCESSIVELY. MFG RECOMMENDS INSPECTION AT 2,100 HOUR INTERVALS. OPERATOR CONTROL NR 95-003.					2	L	7	2 	4F	4	F		A9NM 	E6WE				 
1995081100118	19950811	00118	EU 	1995	8	11	95ZZZX3728 	1	19950717	G	2780	F10A756209	LINE 			AMD 	FALC10	FALCON10 	2730101	EU 										RT SLAT ACTUATOR	RUPTURED 	B			GQRR	D				RETURN TO BLOCK 				K	J		FLUID LOSS 	WARNING INDICATION 		TX	TAXI/GRND HDL 	1			SW	05	12TX	9360 				90				RIGHT WING OUTBOARD SLAT INBOARD SLAT ACTUATOR, THE EXTEND HYDRAULIC LINE FRACTURED AT RADIUS LEADING TO SWIVEL FITTING 	DURING FUNCTION CHECK OF SLATS DURING TAXI OUT TO END OF RUNWAY. SLATS WOULD NOT RETRACT AND LOW QUANTITY OF HYDRAULIC 	FLUID AND LOW PRESSURE. TAXI RETURN TO GATE.				2	L	7	2 	4F				A33EU 					 
1995081100119	19950811	00119	WP 	1995	8	11	95ZZZX3729 	2	19950201	G	7210	30730371	WASHER 								GARRTT	TFE731	TFE7312 	01518	WP 					PLANETARY GEAR	CRACKED 	B			AN3D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05										DURING DETAILED INSPECTION OF PLANETARY ASSEMBLY, PN 3073037-1/2, WASHERS HAVE BEEN FOUND CRACKED ON SEVERAL TFE 731-2/3	 ENGINES. CURRENT MAINTENANCE MANUALS DO NOT REQUIRE REMOVING THIS BEARING CAGE TO ACCOMPLISH INSPECTION OF GEAR ASSEMB	LY. SEE LIGHT MM 72-02-41, PAGE 224C, AND MM 72-72-02, SECTION 2 INSPECTION. APPROXIMATELY 30 OF THESE WASHERS HAVE BE	EN FOUND CRACKED IN THE LAST 6 MONTHS. ALL HAVE BEEN SENT TO THE MANUFACTURER. PART TOTAL TIMES 3747.0 TO 6938.0.								4	F			E6WE				 
1995081100120	19950811	00120	EA 	1995	8	11	95ZZZX3730 	2	19950714	G	7532	310334601	DIAPHRAM 		310092205 	BEECH 	200 	200BEECH 	1152920	CE 	PWA 	PT6 	PT6A41 	52043	EA 					BLEED VALVE	RUPTURED 	B			LX5R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	19	971LL				9B540	BB572	PCE81368			DIAPHRAM RUPTURED RENDERING BLEED VALVE INOPERATIVE.						1	L	7	2 	4T	4	T		A24CE 	E4EA				 
1995081100122	19950811	00122	GL 	1995	8	11	95ZZZX3732 	3	19950721	G	6111	V8433	BLADE 			BEECH 	35 	S35 	1151532	CE 						HARTZL	HCA3V	PHCA3VF4 	GL 	SHANK	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	333SM		110 		E16593	D7616		BR450		DEFECT IS IN THE DOUBLE SHOULDER OF THE 3 BLADES WHERE IT IS RETAINED BY THE CLAMP.						1	L	7	1 	3O				3A15 		5	C	P6EA	 
1995081100123	19950811	00123	GL 	1995	8	11	95ZZZX3733 	3	19950721	G	6111	V8433	BLADE 			BEECH 	35 	S35 	1151532	CE 						HARTZL	HCA3V	PHCA3VF4 	GL 	SHANK	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	333SM		110 		D83795	D7616		BR450		DEFECT IS IN THE DOUBLE SHOULDER OF THE 3 BLADES WHERE IT IS RETAINED BY THE CLAMP.						1	L	7	1 	3O				3A15 		5	C	P6EA	 
1995081100124	19950811	00124	GL 	1995	8	11	95ZZZX3734 	3	19950721	G	6111	V8433	BLADE 			BEECH 	35 	S35 	1151532	CE 						HARTZL	HCA3V	PHCA3VF4 	GL 	SHANK	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	333SM		110 		D83882	D7616		BR450		DEFECT IS IN THE DOUBLE SHOULDER OF THE 3 BLADES WHERE IT IS RETAINED BY THE CLAMP.						1	L	7	1 	3O				3A15 		5	C	P6EA	 
1995081100125	19950811	00125		1995	8	11	95ZZZX3735 	4	19950721	G	6122		FLYWEIGHT 																	PROPELLER GOV	CRACKED 	B	P		LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17										REPAIR STATION REPORTS AS OF 6-24-95, THERE HAVE BEEN 10 FLYWEIGHT BASES FOUND CRACKED ON MCCAULEY, FULL FEATHER GOVERNO	RS. PN B20258, TOWER STYLE DISC AND, PN B20281, 2-PIECE SYTLE DISCS ARE BEING REPORTED.																		 
1995081100127	19950811	00127	EU 	1995	8	11	95ZZZX3737 	1	19950713	G	2435	150SG11037	SHAFT 		190SG122Q 	SNIAS 	350 	AS350BA 	8680817	EU 										START/GEN	SHEARED 	B			SZTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	911MV	4 			52862	2262				STARTER GENERATOR SHAFT SHEARED UPON START OF ENGINE.						1	G	7	1 	3U			NC	H9EU 					 
1995081100128	19950811	00128	EU 	1995	8	11	95ZZZX3738 	1	19950713	G	2435	150SG11037	SHAFT 		150SG122Q 	SNIAS 	350 	AS350BA 	8680817	EU 										START/GEN	SHEARED 	B			SZTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	911MV	97 			2691	2262				STARTER/GENERATOR SHAFT SHEARED AT GROUND IDLE AFTER FLIGHT.						1	G	7	1 	3U			NC	H9EU 					 
1995081100129	19950811	00129	WP 	1995	8	11	95ZZZX3739 	1	19950715	G	7722	369A45217	GAUGE 			HUGHES	369 	369D 	4470706	WP 										TOT	INOPERATIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V	4231 				490487D				TOT GAUGE - ON NEXT START OF THE AIRCRAFT THERE WAS NO INDICATION OF TOT. GAUGED CHECKED AND WAS FOUND INOPERATIVE. R	EPLACED GAUGE.					1	G	7	1 	3U				H3WE 					 
1995081100130	19950811	00130	GL 	1995	8	11	95ZZZX3740 	2	19950710	G	7321	23057344	FUEL CONTROL 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	MALFUNCTIONED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5313Y		68 			490496D	CAE831718			PART WAS RETURNED FROM REPAIR AND INSTALLED ON THE AIRCRAFT ONLY TO HAVE THE SAME SYMPTOMS 1.5 HOURS LATER. COMPONENT H	AS A FUEL SCHEDULING PROBLEM AND HAS BEEN SENT IN AGAIN ON ALLISON 250 REPORT NR A160211.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995081100131	19950811	00131	EU 	1995	8	11	95ZZZX3741 	1	19950713	G	6410	355A12004004	BLADE SPAR 			AEROSP	AS355 	AS355F1 	8680810	EU 										T/R	CRACKED 	B			SZTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	101UM	1402 			4256	5073				TAIL ROTOR REMOVED FOR DEBONDING OF STAINLESS STEEL LEADING EDGE. SENT TO AEC FOR EVALUATION AND REPAIR. TAIL ROTOR BL	ADE SCRAPPED BY AEC FOR SPAR CRACK AT REINFORCMENT AND LOWER SURFACE, BLADE NR 2 BEYOND REPAIR LIMITS.					1	G	7	2 	3U				H11EU 					 
1995081100132	19950811	00132	EU 	1995	8	11	95ZZZX3742 	1	19950712	G	6410	355A12004008	BLADE SPAR 			AEROSP	AS355 	AS355F1 	8680810	EU 										T/R	CRACKED 	B			SZTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	101UM	719 				5073				TAIL ROTOR REMOVED FOR DAMAGE PENETRATION OF ONE BLADE STAINLESS STEEL LEADING EDGE. SENT TO AEC FOR EVALUATION AND REP	AIR. AEC CONDEMNED FOR SPAR REINFORCEMENT PAD CRACK BEYOND LIMITS.					1	G	7	2 	3U				H11EU 					 
1995081100133	19950811	00133	GL 	1995	8	11	95ZZZX3743 	2	19950710	G	7250	68993737	WHEEL 		HX66921 	BELL 	206 	206B3 	1181506	SW 	ALLSN 	250C 	250C20B 	03013	GL 					3RD STAGE	CRACKED 	B			SZTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	206WP	2773 			CAT34702	2752	CAE830842			ENGINE WOULD NOT MAKE POWER. FOUND 3RD STAGE WHEEL CRACKED.						1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995081100134	19950811	00134	GL 	1995	8	11	95ZZZX3744 	2	19950414	G	7250	A6871505	BEARING 			BOLKMS	105 	BO105C 	5626005	EU 	ALLSN 	250C 	250C20B 	03013	GL 					TURBINE NR 5	FAILED 	B			HDNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	105SJ	153 			077	S104	CAT23301			NR 5 BEARING BALL RETAINER FLAKING OFF. THE BEARING MANUFACTURED BY SUPERIOR TURBINE.						1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995081100135	19950811	00135	WP 	1995	8	11	95ZZZX3745 	1	19950322	G	6720	369H75319	TORQUE TUBE 			HUGHES	369 	369E 	4470707	WP 										T/R CONTROL	HOLE ELONGATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05	234RF	3062 				255E				LOST MOTION NOTICED IN TAIL ROTOR CONTROLS. FOUND HOLE ELONGATED FOR FITTING (PN 369A7511) ATTACHMENT TO TORQUE TUBE. R	EPLACED TORQUE TUBE.					1	G	7	1 	3U				H3WE 					 
1995081100136	19950811	00136	NE 	1995	8	11	95ZZZX3746 	1	19950614	G	6720	41003934	SLEEVE 			SKRSKY	S76 	S76 	8143010	NE 										T/R SERVO	CRACKED 	B			TQLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03										SERVO SLEEVE MAGNETIC PARTICLE INSPECTION REVEALED STRESS CRACKS WHICH RADIATE OUT FROM THE 1.050 INCH DIAMETER TO THE 1	.235 INCH DIAMETER WITH EDGEBREAK. FOUR SUCH DEFECTIVE PARTS FOUND ON FOUR SEPARATE ASSEMBLIES.					1	G	7	2 	3U				H1NE 					 
1995081100137	19950811	00137	GL 	1995	8	11	95ZZZX3747 	2	19950714	G	7313	6890917	NOZZLE 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	8639F		189 			1280431D	CAE832846			AIRCRAFT WOULD DROOP RPM WHEN THE COLLECTIVE WAS LIFTED. REPLACEMENT OF THE FUEL NOZZLE CORRECTED THE PROBLEM. FCU WAS	 CHANGED AS PRECAUTION.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995081100138	19950811	00138	WP 	1995	8	11	95ZZZX3748 	1	19950706	G	6220	369A10045	BLADE PIN 			HUGHES	369 	369D 	4470706	WP 										M/R HUB	FRACTURED 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	8639F	1219 			0098849308	1280431D				AT 100-HOUR INSPECTION, THE PIN WAS DISCOVERED BROKEN WHERE THE CLIP LOCKS ON THE SHAFT. SEE MDHC SOR NR 300155.						1	G	7	1 	3U				H3WE 					 
1995081100139	19950811	00139	EA 	1995	8	11	95ZZZX3749 	2	19950707	G	8540	72230	IDLER SHAFT 			HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HIO360D1A 	41514	EA 					ENG REAR CASE	STUDS BROKE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	8377F	1120 				480680	L836851A			STUDS, .3125 INCH, IN REAR OF CRANKCASE THAT HOLDS IDLER GEAR SHAFT BROKE WHICH LET THE IDLER GEAR GET BETWEEN CRANK AND	 CAMSHAFT WHICH CAME LOOSE AND WAS VERY NEAR FAILURE. ENGINE HAD 1,120 HOURS TOTAL SINCE NEW. THE STUDS IN THE REAR OF	 THE CASE SHOULD BE .3750 INCH STUDS. HAVE HAD THIS SAME THING HAPPEN ON ANOTHER ENGINE OF SAME MAKE AND MODEL WITH 1,1	02 HOURS SINCE MOH AND TOTAL TIME OF 3,200 HOURS.			1	G	7	1 	3O	3	O		4H12 	1E10				 
1995081100140	19950811	00140	GL 	1995	8	11	95ZZZX3750 	2	19950703	G	7200		ENGINE 			BELL 	206 	206B3 	1181506	SW 	ALLSN 	250C 	250C20B 	03013	GL 					FUEL FILTER	FLAME OUT 	H		A		O				OTHER 				X			ENGINE FLAMEOUT 			HO	HOVERING 	1			GL	23	321JW	10309				3446	820486			ENGINE FLAMED OUT IN HOVER. EXPERIENCED SUCCESSFUL RESTART ON FIRST ATTEMPT. TWO MINUTES RUN AT 100 PERCENT N2 WITH BO	OST PUMPS OFF - CHECKED OKAY. SHUT DOWN ENGINE. BLED SYSTEM, FOUND AIR IN ENGINE MOUNTED FUEL FILTER HOUSING. RAN ENG	INE, SHUT DOWN, BLED FILTER AGAIN - NO AIR FOUND. AIRCRAFT RETURNED TO SERVICE. NOTE: AIRCRAFT WAS JUST RETURNED TO S	ERVICE AFTER APPROXIMATELY 5 WEEKS IN PAINT SHOP ABOUT TEN HOURS BEFORE FLAMEOUT.			1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995081100141	19950811	00141	SW 	1995	8	11	95ZZZX3751 	1	19950712	G	6310	20604001515	DRIVESHAFT 			BELL 	206 	206L1 	1182107	SW 										ENG/XMSN	SHEARED 	D		A		R				AUTOROTATION 				O			OTHER 			CR	CRUISE 	1			CE	03	119TA	7191 	1442 		AMN10200	45263				MAIN ROTOR DRIVESHAFT (INPUT DRIVESHAFT) SHEARED AT THE FLANGE ON THE TRANSMISSION FLEX COUPLING GEAR, AT THE TRANSMISSI	ON END OF SHAFT. THE FAILURE OCCURRED IN NORMAL CRUISE FLIGHT. AUTOROTATION LANDING MADE WITH NO DAMAGE TO AIRCRAFT. T	HE FLEX COUPLING SHOWED NO ABNORMAL WEAR OR DAMAGE. NOTE: THE DRIVESHAFT HAD ONE OVERTORQUE (110 PERCENT) INCIDENT. SH	AFT WAS REMOVED FOR OVERHAUL AT THAT TIME. TSO, 1,441.8 HOURS.			1	G	7	1 	3U				H2SW 					 
1995081100142	19950811	00142	WP 	1995	8	11	95ZZZX3752 	1	19950726	G	3213	269A309	PISTON 		269A3103 	HUGHES	269 	269B 	4470502	WP 										SHOCK STRUT	CORRODED 	G		A		K				NONE 				O			OTHER 			LD	LANDING 	1			EA	05	9483F					1260289				THIS HELICOPTER DEVELOPED GROUND RESONANCE AND SELF-DESTRUCTED. DURING THE ACCIDENT INVESTIGATION, NOTICED BOTH LEFT SH	OCK STRUT AND THE SKID ATTACH LUGS WERE SEVERELY CORRODED (EXFOLIATED) AND SEPARATED. SUGGEST REMOVAL OF ALL SHOCK STRU	TS DURING ANNUAL/100-HOUR INSPECTIONS TO ENSURE NO CORROSION EXITS.				1	G	7	1 	3O				4H12 					 
1995081100143	19950811	00143	GL 	1995	8	11	95ZZZX3753 	2	19950622	G	7240	23056130	BURNER LINER 			BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20B 	03013	GL 					COMB CAN	MISINSTALLED 	B		A	SNCD	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	17	455H		958 			3453	CAE833825			WHEN BURNER CAN LINER WAS ASSEMBLED, THE LOWER SKIRT WAS TURNED 90 DEGREES WHICH MISPLACED TWO LARGE COOLING HOLES. THI	S CAUSED THE ENGINE TO START SLOW (60 SECONDS), HANG AT 42 PERCENT, AND HAVE A DELAYED LIGHT OFF. THE PROBLEM ONLY SHOW	ED UP AFTER ABOUT 500 HOURS IN USE.				1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995081100363	19950811	00363		1995	8	11	95ZZZX3754 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					40103					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100364	19950811	00364		1995	8	11	95ZZZX3755 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					52929					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100365	19950811	00365		1995	8	11	95ZZZX3756 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					10873					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100366	19950811	00366		1995	8	11	95ZZZX3757 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					94888					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100367	19950811	00367		1995	8	11	95ZZZX3758 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A18174					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100368	19950811	00368		1995	8	11	95ZZZX3759 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					92273					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100369	19950811	00369		1995	8	11	95ZZZX3760 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					77533					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100370	19950811	00370		1995	8	11	95ZZZX3761 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A24946					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100371	19950811	00371		1995	8	11	95ZZZX3762 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					44787					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100373	19950811	00373		1995	8	11	95ZZZX3764 	4	19950315	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14992					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100398	19950811	00398	CE 	1995	8	11	95ZZZX3789 	1	19950626	G	3242	16415A	DISC 		4075B 	CESSNA	210 	T210N 	2073456	CE 										RT MLG	RUSTED 	B			VT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	6192N	2485 				21062963				DURING TIRE CHANGE, MAINTENANCE PERSONNEL NOTED THE RIGHT MLG BRAKE DISC RUSTED AND CRACKED APPROX 90 DEGREES AT WELDED 	FLANGE. NO RECORD OF THIS DISC HAD EVER BEEN REPLACED. PART TT 2,485.0 HRS. AIRCRAFT UNDERWENT AN ANNUAL INSPECTION 5	-8-95 AND HAD OPERATED 21 HOURS.				1	H	7	1 	3O				3A21 					 
1995012000499	19950120	00499	CE 	1995	1	20	95ZZZX379 	1	19950101	G	3231	24130831	DOOR 			CESSNA	172 	172RG 	2072438	CE 										NLG	HUNG UP 	D				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			SW	17	84AT					172RG0791				NOSE LANDING GEAR FAILED TO EXTEND RESULTING IN DAMAGE TO NOSE L/G DOORS, LOWER ENGINE COWL ASSY, AND PROPELLER. AFTER 	REPAIR, L/G OPERATES NORMALLY. BELIEVED THAT DOORS 'HUNG' ON LOWER COWL SKIN OR BUMPERS, PN 2452006-15, AND PN 2452006-	16. RECOMMEND INDUCING FORCE EQUAL TO MAXIMUM LANDING GEAR EXTENSION DURING OPERATIONAL INSPECTION OF L/G.				1	H	7	1 	3O				3A17 					 
1995081100399	19950811	00399	EU 	1995	8	11	95ZZZX3790 	1	19950117	G	7332	78704	TRANSDUCER 		9308704 	SOCATA	TBM 	TBM700 	8682000	EU 										FUEL PRESS	MALFUNCTIONED 	B			MZER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	300AE	155 				97				PILOT REPORTED NO FUEL PRESSURE INDICATION, TURNED BOOST PUMP ON, SAME RESULT. REPLACED FUEL PRESSURE TRANSDUCER WITH N	EW UNIT. FUEL PRESSURE INDICATING SYSTEM FUNCTIONED NORMALLY. OCCURRENCE 1-17-95. A/C TT 155.					1	L	7	1 	3T			RT	A60EU 					 
1995081100400	19950811	00400	SO 	1995	8	11	95ZZZX3791 	2	19950710	G	8530	630046	PISTON PIN 			CESSNA	404 	404CESSNA 	2075901	CE 	CONT 	O520 	GTSIO520M 	17032	SO 					NR 3 CYLINDER	BROKEN 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	41S	1298 				4040023	276274R			PISTON REMOVED ALONG WITH CYLINDER NR 3 DUE TO CYLINDER HEAD CRACKS. WHEN INSPECTING PISTON, FOUND PIN PLUG (NON-REMOVA	BLE, FORGED-IN TYPE) TO BE BROKEN IN MIDDLE WITH ONE END LOOSE. SUBMITTER STATES, OBSERVED THIS TWICE BEFORE ON SIMILAR	 ENGINES.				1	L	7	2 	3O	3	O		A25CE 	E7CE				 
1995081100401	19950811	00401	EA 	1995	8	11	95ZZZX3792 	2	19950428	G	8530	17540	VALVE 		LW12417 	CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					ENG EXH	FAILED 	G				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SO	16		610 					L3445027A			WHILE IN-FLIGHT CRUISE, THE HEAD OF THE EXHAUST VALVE BROKE OFF THE VALVE STEM CAUSING INTERNAL ENGINE DAMAGE. THE AIRC	RAFT MADE AN EMERGENCY LANDING ON A SHORT GRASS RUNWAY CAUSING SUBSTANTIAL DAMAGE TO AIRCRAFT. THIS INSPECTOR HAS WITNE	SSED THIS BEFORE ON LYCOMING O-320 AND O-540 NORMAL OPERATED ENGINES. SUGGEST MANUFACTURER COME OUT WITH A BETTER EXHAU	ST VALVE.			1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995081100402	19950811	00402	GL 	1995	8	11	95ZZZX3793 	3	19950612	G	6114		DOME 			PIPER 	PA34 	PA34200T 	7103406	SO 						HARTZL	HCC2Y	BHCC2YF2 	GL 	HUB	BLEW OFF 	H				K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SO	15		3707 	1 					AN5708		CUSTOMER INSTALLED PROPELLER TO ENGINE AND THE PRESSURE RELIEF VALVE IN THE GOVERNOR WAS STUCK AND TOO MUCH PRESSURE WAS	 CREATED IN PROP DOME AND BLEW THE DOME OFF THE HUB AND LEAKED OIL.					1	L	7	2 	3O				A7SO 		5	C	P920	 
1995081100403	19950811	00403	GL 	1995	8	11	95ZZZX3794 	3	19950612	G	6114		HUB 			CESSNA	210 	210 	2073402	CE 						MCAULY	3A32C	D3A32C90 	GL 	SOCKET NR 2	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17			1100 					743863		BLADE SOCKET NR 2 CRACKED.						1	H	7	1 	3O			RT	3A21 		5	C	P21EA	 
1995081100404	19950811	00404		1995	8	11	95ZZZX3795 	2	19950530	G	7414	M3975	COIL 	SLICK 	4370 															MAGNETO	FAILED 	B			TY5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03		80 			94050449					MAGNETO UNIT BECAME INOPERATIVE. DISASSEMBLED MAG AND REMOVED COIL. FOUND COIL CRACKED AND ARCING THROUGH TO HOUSING. 	 INSTALLED NEW COIL, CHECKED AND SET E-GAP, REASSEMBLED AND TEST RUN UNIT, ACCEPTABLE. COIL WAS OF NEW BLACK TYPE NR M3	975 (MFG DATE 5-11-94).																	 
1995081100405	19950811	00405		1995	8	11	95ZZZX3796 	2	19950712	G	7322	13662	FLOAT BRACKET 	FACET 	MA45 															CARBURETOR	CRACKED 	B			TY5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03					3961733					CARBURETOR UNIT DISASSEMBLED TO CHECK FOR SERVICEABLE FLOAT BRACKET AND FOUND IT HAD A CRACK STARTING IN THE RADIUS CORN	ER WHERE THE EARS WERE BENT UP. ONE CRACK ONLY WAS NOTICED. THE RADIUS FORMED BY THE FORMING DIES FOR BENDING UP THE E	ARS IS TOO SHARP. THIS WAS THE SECOND CONDITION FOUND WITH DEFECTIVE FLOAT BRACKET.																	 
1995081100406	19950811	00406		1995	8	11	95ZZZX3797 	2	19950712	G	7322	13662	FLOAT BRACKET 	FACET 	MA45 															CARBURETOR	BROKEN 	B			TY5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03					75021024					ENGINE RAN VERY RICH AND ERRATIC. DISASSEMBLED CARBURETOR AND FOUND FLOAT BRACKET EAR BROKEN OFF. IT HAD BROKEN IN THE	 RADIUS WHERE THE EAR WAS BENT UP AT A 90 DEGREE ANGLE. UNIT WAS A PRECISION AIRMOTIVE RECENT MANUFACTURE. APPEARS FOR	MING DIES CREATE TOO SHARP A RADIUS WHEN BENDING THE 2 EARS UP TO 90 DEGREES. FOUND ANOTHER OLDER UNIT WITH A CRACKED F	LOAT BRACKET IN THE SAME AREA, BUT IT HAD NOT BROKEN OFF YET.																 
1995081100407	19950811	00407	CE 	1995	8	11	95ZZZX3798 	1	19950712	G	5312	1694000191	BULKHEAD 			BEECH 	23 	B24R 	1151253	CE 										AFT FUSELAGE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	1942L	2354 				MC415				DURING AN ANNUAL INSPECTION NOTED BULKHEAD WAS CRACKED IN THE FLANGE WHERE HOLES HAD BEEN DRILLED FOR A FACTORY ANTENNA 	INSTALLATION (ANTENNA STILL INSTALLED). NO DOUBLER WAS INSTALLED AT THE FACTORY, AND WASHERS USED UNDER THE SECURING HA	RDWARE WERE NOT RADIUSED TO MATCH THE BEND RADIUS OF THE BULKHEAD. A CALL TO THE FACTORY REVEALED MOST AIRCRAFT OF THIS	 SERIES DID NOT RECEIVE DOUBLERS UNDER THE ANTENNAS, AND THIS IS A STANDARD FACTORY INSTALLATION.			1	L	7	1 	3O				A1CE 					 
1995081100408	19950811	00408	EA 	1995	8	11	95ZZZX3799 	2	19950621	G	7414		HOUSING 	BENDIX 	S4LN1209 	BEECH 	23 	B19 	1151215	CE 	LYC 	O320 	O320E2C 	41508	EA 					RT MAGNETO	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	24582	7195 	1550 		243050	MB540	L1803127A			DURING ANNUAL INSPECTION, THE RIGHT MAGNETO HOUSING WAS FOUND CRACKED IN SEVERAL PLACES. CRACKED ON BOTH SIDES OF THE M	AGNETO DOWN NEAR THE DRIVE END.					1	L	7	1 	3O	3	O		A1CE 	E274				 
1995012000500	19950120	00500	CE 	1995	1	20	95ZZZX380 	1	19950101	G	3231	24130832	DOOR 			CESSNA	172 	172RG 	2072438	CE 										NLG	HUNG UP 	D				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			SW	17	84AT					172RG0791				NOSE LANDING GEAR FAILED TO EXTEND RESULTING IN DAMAGE TO NOSE L/G DOORS, LOWER ENGINE COWL ASSY, AND PROPELLER. AFTER 	REPAIR, L/G OPERATES NORMALLY. BELIEVED THAT DOORS 'HUNG' ON LOWER COWL SKIN OR BUMPERS, PN 2452006-15, AND PN 2452006-	16. RECOMMEND INDUCING FORCE EQUAL TO MAXIMUM LANDING GEAR EXTENSION DURING OPERATIONAL INSPECTION OF L/G.				1	H	7	1 	3O				3A17 					 
1995081100409	19950811	00409	CE 	1995	8	11	95ZZZX3800 	1	19950414	G	5511	07326113	RIB 			CESSNA	182 	182J 	2072722	CE 										H STAB STA 27	BENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	2687F	2851 				18256787				HORIZONTAL STABILIZER LEADING EDGE RIBS FOUND BENT. DISCOVERED BY PINCHING THE LEADING EDGE AT EACH RIB. SUBMITTER SUG	GESTS POOR GROUND HANDLING MAY BE THE CAUSE OF THIS DAMAGE.					1	H	7	1 	3O			NT	3A13 					 
1995081100410	19950811	00410	CE 	1995	8	11	95ZZZX3801 	1	19950414	G	5511	07326114	RIB 			CESSNA	182 	182J 	2072722	CE 										H STAB STA 16	BENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	2687F	2851 				18256787				HORIZONTAL STABILIZER LEADING EDGE RIBS FOUND BENT. DISCOVERED BY PINCHING THE LEADING EDGE AT EACH RIB. SUBMITTER SUG	GESTS POOR GROUND HANDLING MAY BE THE CAUSE OF THIS DAMAGE.					1	H	7	1 	3O			NT	3A13 					 
1995081100411	19950811	00411	SO 	1995	8	11	95ZZZX3802 	1	19950511	G	5530	AN4266	RIVET 			PIPER 	PA34 	PA34200T 	7103406	SO 										VERT STAB	BROKEN 	B	S	A	APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4377X	16500				347670035				THE SHOP HEAD OF THE RIVET ON THE RIGHT SIDE OF THE VERTICAL STABILIZER, JUST ABOVE THE FUSELAGE THAT HOLDS THE AFT INNE	R CHANNEL TO THE SKIN, WAS BROKEN OFF. THIS MAY HAVE BEEN CAUSED BY VIBRATION. SUBMITTER KNOWS OF SEVERAL INSTANCES OF	 SAME RIVETS ON BOTH SIDES BREAKING ON FLEET AIRCRAFT.				1	L	7	2 	3O				A7SO 					 
1995081100412	19950811	00412	SO 	1995	8	11	95ZZZX3803 	1	19950712	G	2842	550697	SENSOR 			PIPER 	PA31 	PA31350 	7103110	SO 										OTBD AUX FUEL	CORRODED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	500EE					318052131				UNIT WAS SEVERELY CORRODED AND THE FLOAT MATERIAL WAS DETERIORATING INTO THE TANK. RECOMMEND MORE CORROSION PROTECTION 	AND A BETTER MATERIAL FOR THE FLOAT.					1	L	7	2 	3O				A20SO 					 
1995081100413	19950811	00413	SO 	1995	8	11	95ZZZX3804 	1	19950528	G	2842	550697	TRANSMITTER 			PIPER 	PA31 	PA31350 	7103110	SO 										RT OTBD AUX	DEFECTIVE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	500EE	8664 				318052131				FLOAT PORTION OF THE FUEL QUANTITY TRANSMITTER IS DETERIORATED WHERE THE ATTACH ARM GOES THROUGH CENTER.						1	L	7	2 	3O				A20SO 					 
1995081100414	19950811	00414	SO 	1995	8	11	95ZZZX3805 	1	19950528	G	2840	487804	SWITCH 			PIPER 	PA31 	PA31350 	7103110	SO 										FUEL SEL CENTER	WIRES LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	500EE	8664 				318052131				THE SCREWS ATTACHING THE ELECTRICAL WIRES TO THE MICROSWITCHES FOR THE RIGHT FUEL SELECTOR CONTROL WERE ALL FOUND LOOSE.	 THIS WAS CREATING A HIGHER RESISTANCE (MEASURED) WHICH MADE THE RIGHT FUEL GAUGE INDICATE MORE FUEL ON-BOARD THAN THER	E ACTUALLY WAS.				1	L	7	2 	3O				A20SO 					 
1995081100415	19950811	00415	CE 	1995	8	11	95ZZZX3806 	1	19950712	G	2130	1023800007	CONTROL CABLE 			BEECH 	58 	58P 	1152744	CE 										PRESSURE SOV	SEPARATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	58PV	1620 				TJ453				DURING ANNUAL INSPECTION, NOTED LEFT ENGINE FIREWALL PRESSURIZATION SHUT-OFF VALVE WOULD NOT FULLY SEAT SUCH THAT PRESSU	RIZATION OF THE CABIN COULD NOT BE ACCOMPLISHED FROM THE LEFT ENGINE. THE CABLE SWAGE AT THE ENGINE END WAS FOUND TO HA	VE FAILED PERMITTING THE CABLE HOUSING TO BACK OUT OF THE CLAMP FERRULE (A PART OF THE CABLE END) I.E., THE FLEXIBLE POR	TION OF THE HOUSING COULD MOVE OUT OF THE RIGID END.			1	L	7	2 	3O				A23CE 					 
1995081100416	19950811	00416	CE 	1995	8	11	95ZZZX3807 	1	19950712	G	7120	1029100263	MOUNT 			BEECH 	58 	58P 	1152744	CE 										LT ENGINE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	58PV	1620 				TJ453				DURING AN ANNUAL INSPECTION, THE SIDE PLATE OF THE LEFT ENGINE MOUNT WAS FOUND CRACKED IN TWO PLACES. THE REARMOST CRAC	K WAS LOCATED 2.25 INCHES AHEAD OF THE FIREWALL, AND THE FORWARD CRACK AT 17.75 INCHES AHEAD OF THE FIREWALL. THE REAR 	CRACK WAS HIDDEN BEHIND THE PROPELLER ACCUMULATOR MOUNT. BOTH CRACKS RUN VERTICALLY ACROSS THE LEFT TRUSS WEB. ALSO NO	TED WAS A CUT INTO THE PN 102-910026-77 SUPPORT. THIS WAS CAUSED BY IMPROPER BENDING OF THE EXHAUST HEAT SHIELD WHEN RE	MOVING THE ENGINE OIL FILTER.		1	L	7	2 	3O				A23CE 					 
1995081100417	19950811	00417	CE 	1995	8	11	95ZZZX3808 	1	19950627	G	7820	C1560200101	MUFFLER 			CESSNA	172 	172RG 	2072438	CE 										END FLANGE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	5252V	45 				172RG0485				END FLANGE CRACKED TWO-THIRDS OF THE WAY AROUND, 45 HOURS TOTAL TIME. AD 83-14-04 HAD BEEN DONE REGULARLY EACH 50 HOURS	. MUFFLER WHICH THIS REPLACED 45 HOURS AGO HAD THE FLANGE OBLITERATED. TOTAL TIME ON THAT MUFFLER COULD NOT BE DETERMI	NED, BUT IT WAS NOT TOO OLD.				1	H	7	1 	3O				3A17 					 
1995081100418	19950811	00418	CE 	1995	8	11	95ZZZX3809 	1	19950612	G	3230	08411111	ROD END 			CESSNA	414 	414 	2075908	CE 										LT MLG	FAILED 	G	S	A		K				NONE 				O			OTHER 			LD	LANDING 	1			GL	03	414JG	3026 				4140611				FORWARD DOWNLOCK EAR FAILED ON LANDING, AS WELL AS NAS-464P4-26 BOLT SHEARED AT HEAD AND ROD END FITTING FAILED IN THREA	DED AREA, PN 0841111-1, LEFT MAIN GEAR FOLDED ON LANDING CAUSING DAMAGE TO LEFT FLAP, LEFT OUTER WING TIP, LEFT PROPELLE	R AND ENGINE.				1	L	7	2 	3O			RT	A7CE 					 
1995081100419	19950811	00419	CE 	1995	8	11	95ZZZX3810 	1	19950707	G	2822	2B7290H	PUMP 	AIRBORNE 		CESSNA	402 	402C 	207590R	CE 										AUXILIARY FUEL	DEFECTIVE 	C	S			O				OTHER 				O			OTHER 			CR	CRUISE 	1			NE	01	660CA		2091 		8AD314	402C0406				DURING CRUISE FLIGHT, PLACED RIGHT FUEL SELECTOR TO LEFT MAIN FUEL TANK, BOTH RIGHT AND LEFT ENGINES SHOWED SIGNS OF FUE	L STARVATION (ENGINES SURGING). PUT LEFT FUEL BOOST PUMP ON LOW AND WAS OK. FOUND LEFT AUXILIARY BOOST PUMP INLET CHECK	 BALL STUCK ON SEAT RESTRICING FUEL FLOW WHEN BOTH ENGINES RUNNING OFF LEFT TANK AT HIGH POWER SETTINGS.				1	L	7	2 	3O				A7CE 					 
1995081100420	19950811	00420	CE 	1995	8	11	95ZZZX3811 	1	19950718	G	5753	0523920	ROLLER 			CESSNA	206 	TU206G 	2073357	CE 										LT FLAP CENTER	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	6303U	3515 				U20605409				DURING ROUTINE INSPECTION NOTED THAT CENTER REAR FLAP ROLLER ON LEFT FLAP WAS NOT ROLLING AS FLAP MOVED. REMOVED AND FO	UND SEVERAL NEEDLE BEARINGS MISSING AND ONE SIDE OF ROLLER WAS FLAT. NO REASON FOR DEFECT COULD BE FOUND. NO DAMAGE TO	 FLAP TRACK.				1	H	7	1 	3O				A4CE 					 
1995081100421	19950811	00421	SO 	1995	8	11	95ZZZX3812 	1	19950711	G	2434	902241	FAN 	PRESTOLITE 	ALU8421R 	PIPER 	PA31 	PA31350 	7103110	SO 										ALT COOLING	CRACKED 	B			IGXR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	711EB		1050 		3031089	317305049				ALTERNATOR COOLING FAN CRACKED AT CENTER MOUNT AREA. THIS CANNOT BE INSPECTED UNLESS THE PULLEY AND COOLING FAN ARE REM	OVED. FAN FAILURE WAS IMMINENT.					1	L	7	2 	3O				A20SO 					 
1995081100422	19950811	00422	CE 	1995	8	11	95ZZZX3813 	1	19950628	G	2910	128050996	LINE 			CESSNA	210 	T210M 	2073451	CE 										HYD PUMP	CRACKED 	D				K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			NM	01	732MZ	3796 				T2161632				HYDRAULIC FLUID WAS PUMPED OVERBOARD WHEN THE GEAR DOOR CLOSE LINE CRACKED JUST BELOW THE TUBING FLARE WHERE IT COMES OU	T OF THE HYDRAULIC PUMP.					1	H	7	1 	3O				3A21 					 
1995081100423	19950811	00423		1995	8	11	95ZZZX3814 	4	19950629	G	6122	F44A	GOVERNOR 			MRCHTI	F260 	F260B 		EU 										PROPELLER	SHAFT CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	800RH	1532 	677 			1102				GOVERNOR WAS SENT IN FOR AN OIL LEAK TO BE REPAIRED AND AD 83-06-10 TO BE COMPLIED WITH. FOUND DRIVESHAFT CRACKED.						1	L	7	1 	3O				A10EU 					 
1995081100425	19950811	00425	GL 	1995	8	11	95ZZZX3816 	3	19950629	G	6114	C4716C58	HUB 			PROPJT	200 	200D 	0140312	NM 						MCAULY	2A34C	D2A34C58 	GL 	NR 1 SOCKET	CRACKED 	B			EK2D	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	09	899RS	2153 			780308	313		780308		PROPELLER INSTALLED NEW 9-11-81, FACTORY INK STAMP ON BLADE SHANK INDICATED PROPELLER HAD NEVER BEEN OVERHAULED. PROPEL	LER REMOVED TO REPLACE MOUNT SEAL AND OLD NUTS, USED FOR 2-HOUR FLIGHT. FOUND SOME NUTS LOOSE, INSTALLED NEW NUTS. AIR	CRAFT FLOWN ADDITIONAL 60 HOURS AND REMOVED DUE TO INCREASING VIBRATION. BOTH DRIVE DOWELS FOUND BROKEN WITH SIDE WEAR 	ON MOUNTING STUDS. HUB FOUND CRACKED IN THREADS OF NR 1 BLADE SOCKET.			1	L	7	1 	3O				3A18 		5	C	P3EA	 
1995082500255	19950825	00255	CE 	1995	8	25	95ZZZX3818 	1	19950719	G	3610	030A63233	BLEED AIR TUBE 			MTSBSI	MU2 	MU2B60 	5780460	CE 										FS 6500	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	25	888PH	5200 				731SA				BLEED AIR TUBE ASSY FOUND CRACKED. THERE IS NO INSPECTION REQUIREMENT TO REMOVE THE DORSAL FIN PANEL AT FS 6500 AND INS	PECT THIS AREA.					1	H	7	2 	3T			RT	A10SW 					 
1995081100427	19950811	00427	CE 	1995	8	11	95ZZZX3819 	1	19950718	G	2741	40CB02B25K	RELAY 			BEECH 	MU300 	400BEECH 		CE 										PITCH TRIM FAIL	STICKS 	B			KI2R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CE	01	85CR					RK22				TRIM MOVEMENT ANNUNCIATION HORN FAILED TO SILENCE AFTER MANUAL PITCH TRIM INPUT. TROUBLESHOOTING DETERMINED THE K134 PI	TCH TRIM FAIL DETECTION (NORMAL) RELAY REMAINED ENGAGED DUE TO EITHER A WEAK INTERNAL SPRING OR EXCESS FRICTION. REPLAC	EMENT OF RELAY CURED PROBLEM. BEECH IS WORKING ON A RE-DESIGN OF THIS SYSTEM....(BADLY NEEDED!)				2	H	7	2 	4F			RT	A16SW 					 
1995012000502	19950120	00502		1995	1	20	95ZZZX382 	4	19950105	G	3452	AT50	TRANSPONDER 	NARCO 		PIPER 	PA28 	PA28140 	7102802	SO 										CENTER CONSOLE	COAX SHORTED 	B			BOJR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03										TRANSPONDER INTERMITTENT. COULD NOT DUPLICATE DISCREPANCY. REMOVED TRANSPONDER FROM A/C AND BENCH CHECKED UNIT. NO DI	SCREPANCY NOTED. CHECKED A/C WIRING, FOUND INTERMITTENT SHORT IN COAX. REMOVED AND REPLACED TRANSPONDER COAX. THREE W	EEKS LATER, A/C RETURNED WITH SAME DISCREPANCY. AGAIN, BENCH CHECKED TRANSPONDER, COULD NOT DUPLICATE DISCREPANCY. FOU	ND COAX SHORTED ONCE AGAIN. UPON CLOSER VISUAL INSPECTION, DISCOVERED COAX CABLE MELTED AND INTERNALLY SHORTING. THE T	RANSPONDER COAX WAS ROUTED ON RT SIDE OF CENTER CONSOLE BECAUSE OF NO FLOOR CAVITY SPACE. FOUND COAX WAS MELTING FROM A	IRCRAFT'S CABIN HEATING DUCT.	1	L	7	1 	3O				2A13 					 
1995081100428	19950811	00428	EU 	1995	8	11	95ZZZX3820 	1	19950710	G	2844	Z00N7809178704	TRANSDUCER 		9308704 	SOCATA	TBM 	TBM700 	8682000	EU 										FUEL PRESSURE	FAILED 	B			MZER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	300AE	120 			03940033	97				PILOT REPORTED NO FUEL PRESSURE INDICATION, TURNED BOOST PUMP ON, SAME RESULT. REPLACED FUEL PRESSURE TRANSDUCER WITH N	EW UNIT, FUEL PRESSURE INDICATING SYSTEM FUNCTIONED NORMALLY. A/C TT 275. OCCURRENCE 7-20-95.					1	L	7	1 	3T			RT	A60EU 					 
1995081100429	19950811	00429	CE 	1995	8	11	95ZZZX3821 	1	19950701	G	2742	99140563	ACTUATOR 		497D1009 	CESSNA	650 	650 	2076802	CE 										STAB PITCH TRIM	FAILED 	B	L		IW1R	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			EA	25	118CD				222	6500118				REPAIRED UNIT FROM CRS-BS4R087M REINSTALLED, 6-8-95. TEST FLIGHT AT ALTITUDE FAILED. UNIT STILL GOING INOP AFTER COLD 	SOAKING. REINSTALLED RENTAL UNIT AND RETURNED S/N 222 TO VENDOR 6-14-95. CONDITION CAUSE UNKNOWN AT THIS TIME.					2	L	7	2 	4F				A9NM 					 
1995081100476	19950811	00476		1995	8	11	95ZZZX3837 	4	19950622	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					66358					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100477	19950811	00477		1995	8	11	95ZZZX3838 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					31197					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100478	19950811	00478		1995	8	11	95ZZZX3839 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A21217					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100479	19950811	00479		1995	8	11	95ZZZX3840 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					79720					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100480	19950811	00480		1995	8	11	95ZZZX3841 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A28050					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100481	19950811	00481		1995	8	11	95ZZZX3842 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					25450					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100482	19950811	00482		1995	8	11	95ZZZX3843 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					37715					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100483	19950811	00483		1995	8	11	95ZZZX3844 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					69957					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100484	19950811	00484		1995	8	11	95ZZZX3845 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					40549					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100485	19950811	00485		1995	8	11	95ZZZX3846 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18690					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100486	19950811	00486		1995	8	11	95ZZZX3847 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					36797					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100487	19950811	00487		1995	8	11	95ZZZX3848 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					51258					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100488	19950811	00488		1995	8	11	95ZZZX3849 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					39242					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100489	19950811	00489		1995	8	11	95ZZZX3850 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					78617					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100490	19950811	00490		1995	8	11	95ZZZX3851 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					50506					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100491	19950811	00491		1995	8	11	95ZZZX3852 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					45154					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100492	19950811	00492		1995	8	11	95ZZZX3853 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					36078					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100493	19950811	00493		1995	8	11	95ZZZX3854 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					26940					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100494	19950811	00494		1995	8	11	95ZZZX3855 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					17350					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100495	19950811	00495		1995	8	11	95ZZZX3856 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					97719					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100496	19950811	00496	EA 	1995	8	11	95ZZZX3857 	2	19950614	G	8520	LW17676	CRANKSHAFT 								LYC 	O540 	AEIO540D4A5 	41532	EA 					FLANGE	CRACKED 	B	P		XBTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15		568 			62V7748		L2209248A			CRANK MAGNETIC PARTICLE INSPECTION SHOWS FATIGUE CRACK IN RADIUS OF FLANGE/JOURNAL TRANSITION. CRACK ALSO INDICATED JUS	T FORWARD OF OIL SLINGER. AIRCRAFT HAS NO DAMAGE HISTORY. CRACKS ARE ORIENTED TO PROPELLER BLADE POSITION. PROPELLER 	(HARTZELL HCCWYK4) APPLIES HIGH GYRO FORCES TO FLANGE. AIRCRAFT IS AN AEROBATIC TYPE.									3	O			1E4				 
1995081100497	19950811	00497		1995	8	11	95ZZZX3858 	2	19950701	G	7421	RHB32S	PLUG 	CHAMPION 																ENGINE	DEFECTIVE 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17										A PART 145 REPAIR STATION HAS REPORTED NUMEROUS OCCURRENCES OF CHAMPION RHB32S AND RHB36S SPARK PLUGS WITH SPLIT SIDE EL	ECTRODES. THE SIDE ELECTRODE IS MANUFACTURED WITH IRIDIUM MATERIAL. TIME IN SERVICE OF THE SPARK PLUGS IS USUALLY 200 	TO 300 HOURS ALTHOUGH SOME HAVE BEEN DISCOVERED BETWEEN 300 AND 800 HOURS. THE REPAIR STATION HAS CONTACTED CHAMPION RE	GARDING THIS PROBLEM AND HAVE BEEN INFORMED THAT IT IS A PROBLEM WITH CHAMPION'S VENDOR. ACCORDING TO THE REPAIR STATIO	N, CHAMPION HAS NOT CORRECTED THE PROBLEM.															 
1995081100498	19950811	00498	CE 	1995	8	11	95ZZZX3859 	1	19950725	G	2434	ALY8420R	ALTERNATOR 	PRESTOLITE 		BBAVIA	8 	8KCAB 	2110612	CE 										DC OUTPUT	WIRE BURNED 	B		A	CS3R	A				UNSCHED LANDING 				B	H		SMOKE/FUMES/ODORS/SPARKS 	ELECT. POWER LOSS-50 PC 		CR	CRUISE 	1			WP	17	76KF	2419 			3070944	15374				ALTERNATOR SHORTED INTERNALLY IN-FLIGHT CAUSING SMOKE IN COCKPIT. PILOT MADE EMERGENCY LANDING. INSPECTED AIRCRAFT, FO	UND ALTERNATOR OUTPUT TERMINAL SHORTED TO GROUND. THERE IS NO CIRCUIT PROTECTION ON ALTERNATOR OUTPUT CIRCUIT. THIS CA	USED WIRING TO BURN UNTIL PILOT SHUT OFF BATTERY MASTER. REPLACED WIRING. INSTALLED CIRCUIT BREAKER IN ALTERNATOR OUTP	UT CIRCUIT.			1	H	7	1 	3O				A21CE 					 
1995081100499	19950811	00499	EA 	1995	8	11	95ZZZX3860 	2	19950717	G	8530	60401	ROCKER SHAFT 			CESSNA	177 	177 	2073704	CE 	LYC 	O320 	O320E2D 	41508	EA 					NR 3 CYL EXH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	2942X	1417 				17700542	L2027927A			DURING THE CHANGING OF THE PUSHROD HOUSING TUBE SEALS WHICH INVOLVES REMOVING THE ROCKER BOXES, FOUND THE VALVE ROCKER S	HAFT ON THE EXHAUST SIDE OF CYLINDER NR 3 CRACKED ABOUT ONE-HALF THE WAY AROUND AND .25 INCH FROM THE END.					1	H	7	1 	3O	3	O	NT	A13CE 	E274				 
1995081100500	19950811	00500	SO 	1995	8	11	95ZZZX3861 	1	19950622	G	3220	50791	SPRING 			AYRES 	S2 	S2RT15NORMAL	0970105	SO 										TAIL WHEEL	BROKE 	D		A		O				OTHER 				O			OTHER 			TX	TAXI/GRND HDL 	1			SO	07	3106H	1307 				T27031				TAIL WHEEL SPRING BROKE WHILE TAXIING FROM LOADING PIT TO RUNWAY. SUSPECT CAUSE, BAD SPRING BECAUSE THIS IS THIRD ONE T	HAT HAS BEEN REPORTED TO AYRES. RECOMMENDATION - NEED HEAVIER OR BETTER GRADE SPRING. THE SPRING BREAKING DESTROYED TH	E RUDDER AND SEVERAL OTHER PARTS.				1	L	7	1 	3T				A3SW 					 
1995081100501	19950811	00501	SO 	1995	8	11	95ZZZX3862 	1	19950710	G	5751	452855	BEARING 			PIPER 	PA23 	PA23235 	7102306	SO 										AILERON	FRICTION 	D		A		K				NONE 				F	W		FLT CONT AFFECTED 	INADEQUATE Q C 		IN	INSP/MAINT 	1			NM	03	4930P					27523				NEW STYLE BEARING, PN 452-855, IS NOT ACCEPTABLE AS A REPLACEMENT FOR P/N 452-345 IN THE AILERONS. THERE IS TOO MUCH FR	ICTION BETWEEN THE 'BALL' AND 'SOCKET' MAKING AILERONS VERY STIFF.					1	L	7	2 	3O				1A10 					 
1995082500256	19950825	00256	SO 	1995	8	25	95ZZZX3863 	1	19950718	G	5341	624482	FITTING 			PIPER 	PA28 	PA28140 	7102802	SO 										WING ATTACH	PITTED 	B			UFAR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	25	4520X					287625048				DURING ANNUAL INSPECTION INCLUDING PIPER SB 977, THE CABIN AFT WING ATTACH FITTINGS WERE FOUND DEEPLY PITTED ON ALL EXPO	SED SURFACES. THEY HAD BEEN PREVIOUSLY CLEANED AND PAINTED (ZINC CHROMATE) WHICH STOPPED THE DECAY. MAINTENANCE RECORDS	 SHOW THE FITTINGS WERE SERVICED IN DECEMBER OF 1988 WITH AN A/C TT OF 4,198.6. MUCH OF THE PTTING IS .0312 INCH DEEP W	ITH A FEW PLACES UP TO .1875 INCH DEEP. THERE IS NO FLAKING OR DETERIORATION OF THE ZINC CHROMATE THAT WOULD INDICATE T	HE PITTING WAS ANY LESS WHEN THE WORK WAS PERFORMED. THE PARTS SHOULD HAVE BEEN REPLACED DUE TO THE EXTREME LOSS OF MAT	ERIAL DUE TO RUST. SB 977 C/W AT THIS TIME.	1	L	7	1 	3O				2A13 					 
1995082500257	19950825	00257	SO 	1995	8	25	95ZZZX3864 	1	19950718	G	5341	624483	FITTING 			PIPER 	PA28 	PA28140 	7102802	SO 										WING ATTACH	PITTED 	B			UFAR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	25	4520X					287625048				DURING ANNUAL INSPECTION INCLUDING PIPER SB 977, THE CABIN AFT WING ATTACH FITTINGS WERE FOUND DEEPLY PITTED ON ALL EXPO	SED SURFACES. THEY HAD BEEN PREVIOUSLY CLEANED AND PAINTED (ZINC CHROMATE) WHICH STOPPED THE DECAY. MAINTENANCE RECORDS	 SHOW THE FITTINGS WERE SERVICED IN DECEMBER OF 1988 WITH AN A/C TT OF 4,198.6. MUCH OF THE PTTING IS .0312 INCH DEEP W	ITH A FEW PLACES UP TO .1875 INCH DEEP. THERE IS NO FLAKING OR DETERIORATION OF THE ZINC CHROMATE THAT WOULD INDICATE T	HE PITTING WAS ANY LESS WHEN THE WORK WAS PERFORMED. THE PARTS SHOULD HAVE BEEN REPLACED DUE TO THE EXTREME LOSS OF MAT	ERIAL DUE TO RUST. SB 977 C/W AT THIS TIME.	1	L	7	1 	3O				2A13 					 
1995081100504	19950811	00504	WP 	1995	8	11	95ZZZX3867 	1	19950621	G	6320	269A4611	SWITCH 		269A517519 	HUGHES	269 	269C 	4470504	WP 										XMSN TEMP	FAILED 	H				O				OTHER 				N			FALSE WARNING 			CR	CRUISE 	1			GL	23	103WP	1743 			S385	S1573				MAIN ROTOR TRANSMISSION OIL TEMP/PRESSURE LIGHT ILLUMINATED IN-FLIGHT. INVESTIGATION FOUND THE SWITCH WOULD OPEN AT A L	OWER TEMPERATURE THAN NORMAL. INSTALLED NEW SWITCH, OPERATIONAL CHECK NORMAL.					1	G	7	1 	3O				4H12 					 
1995081100505	19950811	00505	WP 	1995	8	11	95ZZZX3868 	1	19950628	G	6710	369H120321	LINK 			HUGHES	369 	369D 	4470706	WP 										M/R LEAD LAG	DEFECTIVE 	B	S		EOOR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03	4571V					490487D				REMOVED LINK DUE TO STICKY OPERATION. DISCOVERED THE PIVOT BUSHING HAD NOT BEEN PROPERLY SEATED. IT IS IN SOLID, BUT A	 GAP EXISTS BETWEEN THE LINK AND BUSHING.					1	G	7	1 	3U				H3WE 					 
1995081100506	19950811	00506	SW 	1995	8	11	95ZZZX3869 	1	19950519	G	6230	51635200592	SHAFT 		S16352000017	SKRSKY	S58T 	S58T 	8141800	SW 										M/R	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	1078T	415 			3497	581016				TRANSMISSION DISASSEMBLED TO INSPECT MAST (ASB 58B35-33) (234.9 HRS SINCE LAST COMPLIANCE), .25 INCH CRACK INDICATION FO	UND BEGINNING AT TRAILING DOWEL PIN HOLE TOWARDS UNDERCUT IN MAST BASE.					2	G	7	1 	4U			NC	1H11 					 
1995081100507	19950811	00507	WP 	1995	8	11	95ZZZX3870 	1	19950708	G	6240	369H45267	GAUGE 			HUGHES	369 	369D 	4470706	WP 										TORQUE	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y	7584 				500716D				TORQUE GAUGE FLUCTUATED DURING OPERATION 4-5 PSI. BLEEDING THE SYSTEM FAILED TO CORRECT THE PROBLEM. REPLACING THE UN	IT DID CORRECT IT.					1	G	7	1 	3U				H3WE 					 
1995081100508	19950811	00508	SW 	1995	8	11	95ZZZX3871 	1	19950403	G	7160	206062815120	SEAL 			BELL 	206 	206B3 	1181506	SW 										PARTICLE SEP	TORN 	B			TU3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	303PD	230 				4319				SEAL WAS TORN/RIPPED (FOUND DURING INSPECTION).						1	G	7	1 	3U				H2SW 					 
1995081100554	19950811	00554		1995	8	11	95ZZZX3878 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					97778					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100555	19950811	00555		1995	8	11	95ZZZX3879 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					19822					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100556	19950811	00556		1995	8	11	95ZZZX3880 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					22395					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100557	19950811	00557		1995	8	11	95ZZZX3881 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					11470					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100558	19950811	00558		1995	8	11	95ZZZX3882 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					74230					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100559	19950811	00559		1995	8	11	95ZZZX3883 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					10704					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100560	19950811	00560		1995	8	11	95ZZZX3884 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					17444					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100561	19950811	00561		1995	8	11	95ZZZX3885 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					72840					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100562	19950811	00562		1995	8	11	95ZZZX3886 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A18450					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100563	19950811	00563		1995	8	11	95ZZZX3887 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A30045					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100564	19950811	00564		1995	8	11	95ZZZX3888 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					70067					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100565	19950811	00565		1995	8	11	95ZZZX3889 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C12105					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100566	19950811	00566		1995	8	11	95ZZZX3890 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					58635					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100567	19950811	00567		1995	8	11	95ZZZX3891 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					51589					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100568	19950811	00568		1995	8	11	95ZZZX3892 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					77268					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100569	19950811	00569		1995	8	11	95ZZZX3893 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					77622					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100570	19950811	00570		1995	8	11	95ZZZX3894 	4	19950629	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					29200					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100571	19950811	00571		1995	8	11	95ZZZX3895 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					78427					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100572	19950811	00572		1995	8	11	95ZZZX3896 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					16026					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100573	19950811	00573		1995	8	11	95ZZZX3897 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					69539					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100574	19950811	00574		1995	8	11	95ZZZX3898 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					45083					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100575	19950811	00575		1995	8	11	95ZZZX3899 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					73617					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100576	19950811	00576		1995	8	11	95ZZZX3900 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18698					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100577	19950811	00577		1995	8	11	95ZZZX3901 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A19604					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100578	19950811	00578		1995	8	11	95ZZZX3902 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					13575					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100579	19950811	00579		1995	8	11	95ZZZX3903 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					60041					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100580	19950811	00580		1995	8	11	95ZZZX3904 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A28424					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100581	19950811	00581		1995	8	11	95ZZZX3905 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14823					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100582	19950811	00582		1995	8	11	95ZZZX3906 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					64939					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100583	19950811	00583		1995	8	11	95ZZZX3907 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					95746					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100584	19950811	00584		1995	8	11	95ZZZX3908 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					62032					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100585	19950811	00585		1995	8	11	95ZZZX3909 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					69116					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100586	19950811	00586		1995	8	11	95ZZZX3910 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C14831					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100587	19950811	00587		1995	8	11	95ZZZX3911 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					11737					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100588	19950811	00588		1995	8	11	95ZZZX3912 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					57759					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100597	19950811	00597	GL 	1995	8	11	95ZZZX3921 	2	19950727	G	7323	23007506	GOVERNOR 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	MISRIGGED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y		295 			500716D	CAE830348			DURING RIGGING CHECK, THE GOVERNOR CONTACTED THE UPPER LIMIT STOP BEFORE THE COLLECTIVE REACHED ITS STOP.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995081100598	19950811	00598	GL 	1995	8	11	95ZZZX3922 	2	19950727	G	7230	6887121	VENT TUBE 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					COMP ASSY	DETACHED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y					500716D	CAE830348			ENGINE DIFFUSER VENT ORIFICE TUBE WOULD NOT STAY IN PLACE. INSPECTION FOUND END OF THE TUBE THAT SLIPS INTO THE VENT BO	SS WAS DEFORMED. INSTALLED NEW TUBE.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995081100599	19950811	00599	EU 	1995	8	11	95ZZZX3923 	1	19950630	G	5610	369350543	WINDOW 			HUGHES	369 	369FF 		EU 										PILOT SLIDER	DEPARTED 	D		A		O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			WP	01	911VC	170 				0049FF				THE SLIDE IN THE PILOT'S WINDOW DEPARTED THE HELICOPTER WHEN THE PILOT TRIED TO CLOSE THE WINDOW IN FORWARD FLIGHT. THE	 PILOT STATED HE BARELY TOUCHED THE SLIDER WHEN IT DEPARTED.					1	G	7	1 	3U				H3WE 					 
1995081100600	19950811	00600	SW 	1995	8	11	95ZZZX3924 	1	19950711	G	6330	222031605109	NODAL BEAM 			BELL 	222 	222U 	1182140	SW 										FLEXTURE ASSY	DEBONDED 	B			QMLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	274SM				BR1113	47537				FOUND RIGHT LOWER AFT ELASTOMER PAD BROKEN LOOSE FROM THE NODAL BEAM. SUBMITTER STATES THIS IS A COMMON OCCURRENCE ON E	NTIRE FLEET. IT APPEARS THE OIL AND GREASE IN THIS AREA CONTRIBUTES TO THE BREAKING LOOSE OF THE BOND SURFACE. THIS WO	ULD STOP IF A BETTER DESIGNED NODAL BEAM FLEXURE ASSY WAS USED OR A BETTER BOND MATERIAL WAS USED.				1	G	7	2 	3U				H9SW 					 
1995081100626	19950811	00626		1995	8	11	95ZZZX3926 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18688					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100627	19950811	00627		1995	8	11	95ZZZX3927 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					56144					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100628	19950811	00628		1995	8	11	95ZZZX3928 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					54256					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100629	19950811	00629		1995	8	11	95ZZZX3929 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					13612					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100630	19950811	00630		1995	8	11	95ZZZX3930 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14726					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100631	19950811	00631		1995	8	11	95ZZZX3931 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					19513					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100632	19950811	00632		1995	8	11	95ZZZX3932 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A198288					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100633	19950811	00633		1995	8	11	95ZZZX3933 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					41184					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100634	19950811	00634		1995	8	11	95ZZZX3934 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14726					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100635	19950811	00635		1995	8	11	95ZZZX3935 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18619					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100636	19950811	00636		1995	8	11	95ZZZX3936 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					44301					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100637	19950811	00637		1995	8	11	95ZZZX3937 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					11060					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100638	19950811	00638		1995	8	11	95ZZZX3938 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					35923					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100639	19950811	00639		1995	8	11	95ZZZX3939 	4	19950713	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					178473					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995081100640	19950811	00640	WP 	1995	8	11	95ZZZX3940 	2	19950717	G	7310	31016081	TUBE ASSY 			BEECH 	100 	B100 	1152919	CE 	GARRTT	TPE331	TPE3316252B 	01514	WP 					RT ENG FWD RT	CHAFED 	D				E				ENGINE SHUTDOWN 				B	J		SMOKE/FUMES/ODORS/SPARKS 	WARNING INDICATION 		CR	CRUISE 	1			GL	03	178NC					BE17	P27035			FAILURE OCCURRED IN-FLIGHT, PILOT NOTICED HIGH FUEL FLOW AND SMOKE. ENGINE SHUT DOWN IN-FLIGHT. FOUND ADEL CLAMP WORN 	THROUGH TUBE ASSY. ADDED EXTRA ADEL CLAMPS TO AFT END OF TUBE ASSY TO PREVENT MOVEMENT.					1	L	7	2 	4T	4	T		A14CE 	E2WE				 
1995081100642	19950811	00642	WP 	1995	8	11	95ZZZX3942 	2	19950727	G	7230	30755147	SEAL 			AMD 	FALC50	FALCON50MYST	2730106	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					NR 1 CARBON	FAILED 	G				O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			EA	03	4MB	4736 			2021762789	156	P76599			IN-FLIGHT SMOKE IN COCKPIT CAUSED BY FAILED NR 1 CARBON SEAL AND GEARBOX RELIEF VALVE, PN 3075323-2, OVER PRESSURE OF GE	ARBOX WITH FAILED NR 1 CARBON SEAL CAUSED OIL TO ENTER COMPRESSOR SECTION AND SMOKE IN BLEED AIR SYSTEM.					2	L	7	3 	4F	4	F		A46EU 	E6WE				 
1995081100643	19950811	00643	CE 	1995	8	11	95ZZZX3943 	1	19950715	G	5210		HINGE 			CESSNA	172 	172N 	2072434	CE 										CABIN	PIN BROKEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	737BP	3556 				17269293				DURING 100-HOUR INSPECTION, THE CABIN DOOR HINGE PINS WERE DETERMINED TO BE WORN. WHEN OLD PINS WERE REMOVED, FOUND 2 O	F 4 PINS BROKEN WITH ONLY ABOUT .25 INCH OF REMAINING PIN SECURING HINGE. THE BOTTOM PIECE WAS MISSING ON ONE PIN. THE	 TOP HINGES WERE FOUND BOWED CAUSING HINGES TO BIND WHEN DOORS WERE CLOSED. SUBMITTER SUGGESTED THIS IS ANOTHER ITEM TH	AT MUST BE LOOKED AT ON SCHEDULED INSPECTIONS ON AIRCRAFT WITH MORE THAN 2,000 HOURS.			1	H	7	1 	3O			NT	3A12 					 
1995081100644	19950811	00644	SO 	1995	8	11	95ZZZX3944 	1	19950623	G	2823	7741302	SELECTOR 			PIPER 	PA38 	PA38112 	7103812	SO 										FUEL VALVE	BROKEN 	B		A	AMYR	A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			CE	05	91318	4970 				3881A0162				IN-FLIGHT SELECTOR VALVE COULD NOT BE CHANGED FROM LEFT TANK. MULTIPLE ATTEMPTS MADE TO CHANGE FUEL SELECTOR POSITION. 	 AIRCRAFT ENGINE QUIT. AN OFF-AIRPORT EMERGENCY LANDING WAS MADE. FUEL WAS DELIVERED TO THE PLANE AND IT WAS FLOWN BAC	K TO THEIR AIRPORT. THE FUEL SELECTOR VALVE WAS REMOVED AND DISASSEMBLED. THE INTERNAL NYLON PART THAT ACTUALLY DETERM	INES THE SELECTOR POSITION WAS FOUND BROKEN. ONCE THE NYLON SHEARED, THE PIN WAS DISLODGED AND FORCED TO ONE SIDE MAKIN	G THE SELECTOR TOTALLY INOPERATIVE. THIS AIRCRAFT IS USED FOR FLIGHT TRAINING, SO SELECTOR VALVE GETS A GREAT DEAL OF U	SE.	1	L	7	1 	3O				A18SO 					 
1995081100645	19950811	00645	CE 	1995	8	11	95ZZZX3945 	1	19950720	G	3230		FITTING 			CESSNA	185 	A185F 	2072821	CE 										LT MLG GRBOX	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1555H					18503306				INSPECTION FOUND A CRACK IN THE LEFT LANDING GEARBOX ABOVE THE FORWARD WEDGE/SHIM LOCATION. THE FITTING REQUIRED REPLAC	EMENT.					1	H	7	1 	3O				3A24 					 
1995081100646	19950811	00646	CE 	1995	8	11	95ZZZX3946 	1	19950630	G	2150	660021128	VALVE 			LEAR 	35 	31A 	5170531	CE 										HOT AIR BYPASS	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	740E	1048 			1166	061				FLIGHT CREW REPORTED THEY COULD NOT ACHIEVE A COMFORTABLE TEMPERATURE IN THE CABIN (UNABLE TO COOL). TROUBLESHOOTING RE	VEALED THE HOT AIR BYPASS VALVE DOOR HAD ROTATED ON ITS SHAFT AND WOULD NOT FULLY CLOSE. THE DOOR IS HELD ON THE SHAFT 	WITH 4 SET SCREWS. INSPECTION DETERMINED 2 SET SCREWS WERE MISSING, THE 3RD SCREW WAS LOOSE, AND THE 4TH SCREW COULD NO	T HOLD THE DOOR TO THE SHAFT SECURELY.			2	L	7	2 	4F			RT	A10CE 					 
1995081100647	19950811	00647	CE 	1995	8	11	95ZZZX3947 	1	19950627	G	7830	311SM7T	SWITCH 			LEAR 	35 	31A 	5170531	CE 										STOW/DEPLOY	ARM FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	742E	967 				071				LEFT THRUST REVERSER WOULD DEPLOY ON GROUND ANY TIME SYSTEM WAS ARMED WITHOUT SELECTING DEPLOY. INSPECTED AND FOUND STO	W/DEPLOY SWITCH MECHANICAL ARM AND ROLLER BROKEN OFF FROM SWITCH DUE TO FAILURE OF MECHANICAL ARM TO PIVOT POINT THROUGH	 PIN WELD.				2	L	7	2 	4F			RT	A10CE 					 
1995081100648	19950811	00648	EA 	1995	8	11	95ZZZX3948 	2	19950623	G	8550	LW14114	OIL TUBE 			BEECH 	60 	B60 	1153605	CE 	LYC 	O541 	TIO541E1C4 	41536	EA 					NR 4 CYLINDER	BROKEN 	H				E				ENGINE SHUTDOWN 				K			FLUID LOSS 			NR	NOT REPORTED 	1			GL	03	6033C	2880 	269 			P491	L130559			RIGHT ENGINE OIL LEAK. IN-FLIGHT SHUT DOWN. FOUND OIL TUBE FOR NR 4 CYLINDER EXHAUST VALVE BROKEN. SUSPECT CAUSE - A)	 OVERTORQUED AT INSTALLATION. B) BUMPED WITH TOOL. C) FATIGUE.					1	L	7	2 	3O	3	O		A12CE 	E10EA				 
1995081100649	19950811	00649	GL 	1995	8	11	95ZZZX3949 	1	19950629	G	5320		TAIL POST 			AMTR 	PT2 	PT2 	056184H	GL 										FUSELAGE	BROKE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4215X	208 				PT1088				TAIL POST BROKE OFF FROM LOWER LONGERON. THIS WAS A FACTORY KIT FUSELAGE PART. TAIL POST IS .75 INCH BY .035 INCH, 413	0 TUBING. IT APPEARS TO BE CAUSED BY POOR ENGINEERING, TAIL WHEEL AND SPRING OVERLOADED THE STRUCTURE. DEFECT FOUND WH	EN DOING A PRE-FLIGHT INSPECTION. ADDITIONAL DEFECTIVE FLAP HANDLE BROKE WHEN LANDING, .035 INCH BY .8750 INCH ALUMINUM	 TOO LIGHT MATERIAL.			1	H	7	1 	3I			NC	EXPA1H71					 
1995081100650	19950811	00650	CE 	1995	8	11	95ZZZX3950 	1	19950714	G	2150	640778	BRACKET 			BEECH 	33 	F33A 	1151425	CE 										AIR COND TENSION	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	8246P					CE1624				INSPECTED A/C COMPRESSOR. A/C COMPRESSOR BELT FOUND SHREDDED. WHILE INSPECTING AREA, FOUND A CRACK FROM THE TENSIONER 	BOLT ALL THE WAY TO THE END OF THE BRACKET. IF THIS BROKE OFF, IT WOULD ALLOW THE COMPLETE TENSIONER TO COME LOOSE FROM	 ENGINE.				1	L	7	1 	3O				3A15 					 
1995081100651	19950811	00651	GL 	1995	8	11	95ZZZX3951 	3	19950725	G	6114	A1742	BEARING 			CESSNA	210 	210E 	2073416	CE 						MCAULY	2A34C	E2A34C73 	GL 	HUB	FAILED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	4974U		415 			21058674		730643		BEARING RACE BROKE, A PIECE ABOUT .3750 INCH CAME LOOSE AND WENT THROUGH HUB CAUSING DAMAGE. PROPELLER WAS OVERHAULED 5 	YEARS PRIOR AND 415 HOURS TSO. THIS CONDITION WAS FOUND DURING OVERHAUL. ENTIRE HUB WAS CONDEMNED.					1	H	7	1 	3O				3A21 		5	C	P3EA9	 
1995081100652	19950811	00652	SO 	1995	8	11	95ZZZX3952 	1	19950511	G	5320	6244802	FITTING 			PIPER 	PA28 	PA28161 	7102803	SO 										LT COCKPIT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	302FG	2613 				288016274				FOUND DURING COMPLIANCE WITH SB 977. LEAKING WINDOWS GETTING INSULATION WET AND KEEPING FITTINGS WET CAUSING CORROSION.	 SEAL WINDOWS PER SB 977.					1	L	7	1 	3O				2A13 					 
1995081100653	19950811	00653	GL 	1995	8	11	95ZZZX3953 	1	19950710	G	3252	AN37A	STOP-BOLT 			AMTR 	GAIR 	GLASAIRIII 	05691HK	GL 										SHIMMY DAMPER	SHEARED 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			SW	99	9DY					3184				A DIRT PILE ON 45 DEGREE ANGLE ON RUNWAY CAUSED NOSE WHEEL TO DEFLECT AND START SHIMMY. SEVERE SHIMMY CAUSED SHEARING O	F AN-3 STOP-BOLT RESULTING IN WHEEL TURNING SIDEWAYS AND STRUT COLLAPSING. THE NEW NOSE STRUT HAS A HEAVIER, AN-4 STOP-	BOLT.				1	L	7	1 	3O			RT	EXPA1L71					 
1995013000119	19950130	00119	SO 	1995	1	30	95ZZZX397 	2	19950110	G	8550		OIL PUMP 			CESSNA	207 	207A 	2073604	CE 	CONT 	O520 	IO520F 	17032	SO 					ENGINE	WORN 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	01	9935M					20700751	195900R			AFTER ONLY 2.4 HOURS TIME IN SERVICE AFTER MAJOR OVERAHAUL, OIL PUMP WAS REPORTED TO BE PRODUCING ONLY 12 POUNDS PRESSUR	E AT FULL POWER. OIL PUMP GEARS WERE FOUND SEVERELY WORN AND ENGINE WAS REMOVED AND SHIPPED BACK TO CRS NR 1AXR223L WHE	RE IT HAD BEEN OVERHAULED.				1	H	7	1 	3O	3	O		A16CE 	E5CE				 
1995081100840	19950811	00840	EU 	1995	8	11	95ZZZX3975 	1	19950710	G	3233	184811	CYLINDER 			BAG 	JETSTM	JETSTM3201 	1500217	EU 										MLG	CRACKED 	B			AY55	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	920AE	6913 				920				MLG RADIUS ROD CYLINDER WAS FOUND CRACKED. THIS CRACK RUNS PARALLEL TO THE LENGTH OF THE CYLINDER ALONG THE I.D. FOR 3.	50 INCHES BETWEEN THE MICROSWITCH TOGGLE ARM MOUNTING PAD, TERMINATING IN THE DOWNLOCK THREADS. THIS IS THE SECOND CYLI	NDER FOUND IN THIS MANNER.				2	L	7	2 	4T			RT	A56EU 					 
1995081100842	19950811	00842	EU 	1995	8	11	95ZZZX3977 	1	19950529	G	6410	10531727	LAMINATED PACK 		10531727 	BOLKMS	105 	BO105CBS 	5626008	EU 										INNER SLEEVE	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5416F	6787 	388 		121	794				UPON INSPECTION OF PARTS FOR REPAIR OF TAIL ROTOR ASSEMBLY, FOUND CORROSION BEYOND LIMITS ON CENTER SECTION OF LAMINATED	 PACK DUE TO SALT ATMOSPHERE IN WHICH THE AIRCRAFT FLIES. PART WAS SCRAPPED DUE TO CORROSION BEYOND LIMITS.					1	G	7	2 	3U			NC	H3EU 					 
1995081100843	19950811	00843	NE 	1995	8	11	95ZZZX3978 	1	19950619	G	2612		FIRE LIGHT 			SKRSKY	S76 	S76 	8143010	NE 										NR 1 ENGINE	MALFUNCTION 	B			ALGR	A				UNSCHED LANDING 				N			FALSE WARNING 			NR	NOT REPORTED 	1			SW	03	5446E					760175				NR 1 ENGINE FIRE LIGHT AND HORN CAME ON IN-FLGIHT. COULD NOT CONFIRM FIRE. AIRCRAFT LANDED WTHOUT FURTHER INCIDENT. N	R 1 ENGINE FIRE DETECTION SYSTEM WAS TROUBLESHOT AND PROBLEM COULD NOT BE DUPLICATED.					1	G	7	2 	3U				H1NE 					 
1995013000120	19950130	00120	CE 	1995	1	30	95ZZZX398 	1	19950109	G	7603	C2995150102	CONTROL CABLE 			CESSNA	208 	208B 	2073701	CE 										ENGINE	BROKEN 	B			MJ7R	O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			GL	05	9347B	2164 				208B0059				POWER CABLE BROKE. PILOT HAD NO CONTROL OVER ENGINE. USED EMERGENCY THROTTLE. REPLACED POWER CABLE WITH CESSSNA SERVI	CE KIT SK208-94.					1	H	7	1 	3T			 	A37CE 					 
1995081100909	19950811	00909	GL 	1995	8	11	95ZZZX3980 	1	19950528	G	6100		BOLT 			AMTR 	CH601 	CH601HDS 	05625J7	GL 										PROPELLER	FAILED 	G				O				OTHER 				D			INFLIGHT SEPARATION 			AP	APPROACH 	1			SO	16	18FL	11 				63073				DURING POWER CHANGE IN PATTERN, PROPELLER DEPARTED AIRCRAFT. EXAMINATION OF ALL SIX .25 INCH BOLTS REVEALED THEY HAD FA	ILED AT A POINT FLUSH WITH CRANKSHAFT FLANGE. ALL APPEARED TO HAVE BEEN OVERTORQUED AT INSTALLATION ONLY 11 HOURS PRIOR	. SUGGEST OPERATOR OF ROTAX ENGINES USING .25 INCH PROPELLER BOLTS CHECK FOR CONDITION AND PROPER TORQUE.				1	L	7	1 	3O			NC	1L71 					 
1995081100910	19950811	00910	GL 	1995	8	11	95ZZZX3981 	1	19950403	G	6100		PROPELLER 			AMTR 	KR2 	KR2 		GL 										ENGINE	DEPARTED 	G				O				OTHER 				D			INFLIGHT SEPARATION 			CL	CLIMB 	1			WP	17	22955	6 				2206				UNCERTIFICATED AMATEUR BUILT AIRCRAFT DEPARTED AIRPORT ON FIRST FLIGHT SINCE COMPLETION. PROP HUB ATTACH BOLT UNSCREWED	 AND PROP DEPARTED AIRCRAFT. THE VW CONVERSION WAS PERFORMED BY HAPI. THE PROP HUB BOLT RETAINING COTTER PIN WAS FOUND	 SHEARED. THE OWNER/BUILDER HAD NOT CHECKED PROP TORQUE AND DID NOT KNOW WHO INSTALLED HUB TO ENGINE.				1	L	7	1 	3O				EXPA1L71					 
1995081100911	19950811	00911	SO 	1995	8	11	95ZZZX3982 	1	19950719	G	7602	2329600	BRACKET 			PIPER 	PA24 	PA24260 	7102406	SO 										MIX CONTROL	BROKEN 	B		A	CIER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	8936P					244392				FOUND MIXTURE CONTROL SUPPORT BRACKET CRACKED IN HALF. SAGGING ENGINE SHOCK MOUNTS ALLOWED ENGINE TO DROOP THEREBY ALLO	WING LEFT NOSE GEAR STEERING BUSHING TO STRIKE THE BRACKET WHEN THE LANDING GEAR WAS RETRACTED. THIS RESULTED IN THE LA	NDING GEAR BUSHING WEARING A GROOVE IN THE BRACKET UNTIL IT EVENTUALLY BROKE. IT IS RECOMMENDED THE BRACKET BE INSPECTE	D CLOSELY AT EACH 100 HOUR OR ANNUAL INSPECTION. RECOMMEND REPLACEMENT OF SHOCK MOUNTS AT ANY TIME SAGGING IS NOTED.			1	L	7	1 	3O				1A15 					 
1995081100912	19950811	00912	CE 	1995	8	11	95ZZZX3983 	1	19950710	G	5312	002440024I	BULKHEAD 			BEECH 	58 	58TC 	1152746	CE 										FS 271.92	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	60234	2229 				TK92				DURING ROUTINE MAINTENANCE CRACKS WERE FOUND IN AFT BULKHEAD (FS 271.92) AT LOWER LT AND RT CORNERS OF CUT-OUT AREA FOR 	STUB SPAR. BEECH SI0090 R2 DEALS WITH THIS SUBJECT, BUT ONLY APPLIES TO EARLIER AIRCRAFT S/N. BOTH CRACKS WERE LESS TH	AN .25 INCH, SO ALL 4 CORNERS OF BULKHEAD CUT-OUT WERE REWORKED PER BEECH SI0990 R2.				1	L	7	2 	3O				A23CE 					 
1995081100913	19950811	00913	CE 	1995	8	11	95ZZZX3984 	1	19950710	G	5511	00244002415	STUB SPAR 			BEECH 	58 	58TC 	1152746	CE 										HORIZ STAB	DAMAGED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01	60234	2229 				TK92				DURING ROUTINE MAINTENANCE, DAMAGE TO HORIZ STABILIZER REAR STUB SPAR WAS FOUND. CAUSE OF DAMAGE WAS CONTACT TO UPPER S	URFACE WITH DRILL BIT WHILE DRILLING HOLES THROUGH BULKHEAD FLANGE. SUSPECT DAMAGE MAY HAVE OCCURRED AT FACTORY. BEECH	 SI0990 R2 CALLS ANY DAMAGE TO REAR SPAR CAUSE FOR REPLACEMENT OF SPAR. REPLACED REAR STUB SPAR WITH NEW PART. SUBMITT	ER SUGGESTS USING EXTREME CARE WHEN REMOVING HUCK LOCK BOLTS. NO OVERSIZE BOLTS ARE AVAILABLE AND NO SUBSTITUTIONS ARE 	ALLOWED. HOLES MUST MAINTAIN AN INTERFERENCE FIT OR BULKHEAD MUST BE REPLACED.		1	L	7	2 	3O				A23CE 					 
1995081100914	19950811	00914		1995	8	11	95ZZZX3985 	2	19950718	G	7322	16A108	GASKET 	FACET 	MA4SPA 															CARB INLET	LEAKING 	B			OL3R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	27			20 		BL2714598					CARBURETOR LEAKING AT INLET FITTING DUE TO LACK OF THREAD LUBE (SEALANT). GASKET PN 16-A108 IS INSTALLED IN FITTING.																			 
1995081100915	19950811	00915		1995	8	11	95ZZZX3986 	4	19950727	G	3452	088031140003	KNOB 	BENDIX 	KT76A 	BBAVIA	8 	8GCBC 	1220803	SW 										XPONDER ON-OFF	BROKE 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CE	01	88287					10374				ON FIRST FLIGHT AFTER INSTALLATION, THE ON-OFF-MODE C SELECTOR BROKE OFF IN PILOT'S HAND. THIS IS THE THIRD TIME THERE 	HAVE BEEN BROKEN KNOBS ON THE 'NEW STYLE' FACEPLATE FOR THE KT76A. ALL THREE OCCURRENCES HAVE HAPPENED WITHIN ONE MONTH	.				1	H	7	1 	3O				A21CE 					 
1995081100916	19950811	00916	SO 	1995	8	11	95ZZZX3987 	2	19950723	G	8520	649134SP	CRANKSHAFT 			CESSNA	188 	T188C 	2073012	CE 	CONT 	O520 	TSIO520T 	17040	SO 					NR 2-3 CYLS	BROKE 	D				A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			SO	09	2158J	442 			B099417	T18803395T	511683			NEW V.A.R. CRANKSHAFT BROKE BETWEEN NR 2 AND NR 3 CYLINDERS. THIS CRANKSHAFT HAD A TOTAL TIME OF 442 HOURS SINCE NEW. 	 FAILURE WAS IN-FLIGHT AND PILOT MADE SAFE LANDING WITH NO DAMAGE TO AIRCRAFT OR PROPERTY. THIS APPEARS TO BE A DEFECTI	VE CRANKSHAFT.				1	L	7	1 	3O	3	O		A9CE 	E8CE				 
1995081100917	19950811	00917		1995	8	11	95ZZZX3988 	4	19950710	G	2562	0025004	BATTERY 	ARTEX 	EAGLE 	BEECH 	55 	95B55 	1152706	CE 										ELT	RUPTURED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	213RG				8795	TC655				ELT BATTERY, ARTEX PN 00-25-004, RUPTURED CAUSING SEVERE CORROSION TO RADIO AND CASE. RADIO WAS DAMAGED BEYOND REPAIR. 	 THIS IS THE THIRD OCCURRENCE OF THIS PROBLEM WITH ARTEX BRAND BATTERIES, (2 IN MARTECH ELT'S AND 1 IN NARCO ELT-10). I	N THE NARCO INSTALLATION, SUBSTANTIAL CORROSION DAMAGE TO A/C SKIN BELOW ELT OCCURRED. SUBMITTER RECOMMENDS EVALUATION 	OF ARTEX QC STANDARDS AND PROCEDURES BE MADE. TIS OF AFFECTED BATTERIES WAS LESS THAN THE REPLACEMENT DATE.			1	L	7	2 	3O				3A16 					 
1995081100918	19950811	00918	CE 	1995	8	11	95ZZZX3989 	1	19950712	G	3260	YZ2RN7T	SWITCH 			CESSNA	210 	T210N 	2073456	CE 										LT MLG UPLOCK	BROKEN 	D				A				UNSCHED LANDING 				P			NO WARNING INDICATION 			CL	CLIMB 	1			SW	01	7213N	1333 				21063207				LANDING GEAR RETRACTED, GEAR MOTOR SHUT OFF, BUT HAD NO UP AND LOCKED INDICATION. AIRCRAFT RETURNED AFTER AN UNEVENTFUL	 LANDING. INVESTIGATION REVEALED LT UPLOCK MICROSWITCH HOUSING BROKEN IN HALF. SUSPECT CAUSE, MICROSWITCH HOUSING MADE	 OF PLASTIC, CRACKED AND BROKEN IN HALF DUE TO TIME IN SERVICE OF SWITCH - 16 YEARS.				1	H	7	1 	3O				3A21 					 
1995081100919	19950811	00919	SO 	1995	8	11	95ZZZX3990 	1	19950629	G	3230	AN625	BOLT 			PIPER 	PA28 	PA28R201T 	7102813	SO 										NLG UP DRAG LINK	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	93CC	1458 				28R7803157				WHILE COMPLYING WITH AD 94-14-14, THE UPPER DRAG LINK BOLTS WERE FOUND CRACKED AND STRETCHED. SUBMITTER SUGGESTS THESE 	BOLTS BE REPLACED AS PART OF PIPER SL 988.					1	L	7	1 	3O				2A13 					 
1995081100920	19950811	00920	CE 	1995	8	11	95ZZZX3991 	1	19950703	G	2841	813192	INDICATOR 	STWARNER 		CESSNA	206 	P206 	2073304	CE 										RT FUEL QTY	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	17	4678F	2722 				P2060278				INVESTIGATION OF THE PROBLEM WITH THE RIGHT FUEL GAUGE SHOWING FULL ALL THE TIME, REVEALED THE GAUGE ITSELF IS INOP. RE	PLACEMENT OF THE GAUGE ONLY, CORRECTED THE PROBLEM. THE ONLY COMMENT IS THAT THE AGE OF THE GAUGE MORE THAN THE TOTAL T	IME CAUSED THE PROBLEM. THE GAUGE IS ORIGINAL EQUIPMENT AND THE AIRCRAFT IS A 1966 MODEL.				1	H	7	1 	3O				A4CE 					 
1995081100921	19950811	00921	CE 	1995	8	11	95ZZZX3992 	1	19950724	G	5751	122005212	BRACKET 			CESSNA	206 	TU206A 	2073318	CE 										AILERON HINGE	CRACKED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	4831F	6846 				U2060531				INSPECTION FOUND AILERON HINGE BRACKET CRACKED IN LOWER FORWARD BEND RADIUS.						1	H	7	1 	3O				A4CE 					 
1995081100922	19950811	00922	CE 	1995	8	11	95ZZZX3993 	1	19950724	G	5751	122005211	BRACKET 			CESSNA	206 	TU206A 	2073318	CE 										AILERON HINGE	CRACKED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	4831F	6846 				U2060531				INSPECTION FOUND AILERON LOWER FORWARD HINGE BRACKET CRACKED.						1	H	7	1 	3O				A4CE 					 
1995081100923	19950811	00923	CE 	1995	8	11	95ZZZX3994 	1	19950724	G	5751	122005311	BRACKET 			CESSNA	206 	TU206A 	2073318	CE 										AILERON HINGE	CRACKED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	4831F	6846 				U2060531				INSPECTION FOUND AILERON HINGE BRACKET CRACKED IN LOWER FORWARD BEND RADIUS.						1	H	7	1 	3O				A4CE 					 
1995081100924	19950811	00924	CE 	1995	8	11	95ZZZX3995 	1	19950724	G	5751	122005312	BRACKET 			CESSNA	206 	TU206A 	2073318	CE 										AILERON HINGE	CRACKED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	4831F	6846 				U2060531				INSPECTION FOUND AILERON HINGE BRACKET CRACKED IN LOWER FORWARD BEND RADIUS.						1	H	7	1 	3O				A4CE 					 
1995081800054	19950818	00054	CE 	1995	8	18	95ZZZX3996 	1	19950720	G	3242	B301072	TORQUE PLATE 			CESSNA	185 	A185F 	2072821	CE 										RT MLG BRAKE	CRACKED 	G		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	23FG	7289 				18504035				RIGHT MLG WHEEL REMOVED FOR ROUTINE TIRE CHANGE. BRAKE CALIPER DIFFICULT TO REMOVE FROM TORQUE PLATE. FURTHER INVESTIG	ATION FOUND TORQUE PLATE CRACKED AND TWISTED AT PIN BUSHING TO PLATE AREA. BUSHINGS APPEAR TO BE PRESSED ONTO PLATE. S	IMILAR CLEVELAND TORQUE PLATE BUSHINGS ARE WELDED TO PLATE RESULTING IN A STRONGER PLATE ASSY.				1	H	7	1 	3O				3A24 					 
1995081800055	19950818	00055	SO 	1995	8	18	95ZZZX3997 	1	19950629	G	2720	63451000	SUPPORT 			PIPER 	PA28 	PA28180 	7102808	SO 										RUD PED CENTER	CRACKED 	H	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	21112	2169 				28730515				INSPECTION FOUND RUDDER PEDAL CENTER SUPPORT CRACKED AT BOLT HOLE AND CORNER. SUSPECT BOLTS ARE LOOSENING AND ALLOWING 	SUPPORT TO WORK OR MOVE.					1	L	7	1 	3O				2A13 					 
1995081800056	19950818	00056	SO 	1995	8	18	95ZZZX3998 	2	19950701	G	8550	CH48109	FILTER 	CHAMPION 		CESSNA	207 	T207A 	2073614	CE 	CONT 	O520 	TSIO520M 	17040	SO 					ENG OIL SYSTEM	GASKET DISPLACED	D	P	A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	01	803AN	50 				20700570	283222R			OIL FILTER INTERNAL GASKET WAS OUT OF PLACE AND COVERING INLET PASSAGE OF FILLER BODY. APPEARS TO BE MANUFACTURE DEFECT	. SUBMITTER ADVISES A CLOSER INSPECTION OF OIL FILTER PRIOR TO INSTALLATION TO INSURE GASKET IS NOT BLOCKING INLET HOLE	.				1	H	7	1 	3O	3	O		A16CE 	E8CE				 
1995081800061	19950818	00061	SO 	1995	8	18	95ZZZX4003 	1	19950721	G	5751	86392002	HINGE HALF 			PIPER 	PA44 	PA44180 	7104402	SO 										LT AIL OTBD	HOLE ELONGATED 	D	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	81141	1552 				448095008				LEFT AILERON OUTBOARD HINGE BOLT HOLE ELONGATED. ALL OTHER AILERON HINGES ON THIS AIRCRAFT SHOW NO SIGNS OF WEAR. SUSP	ECT CAUSE AS LOOSE BOLT. MATING HNGE HALF HAS A SEALED BEARING. SUGGEST A STEEL BUSHING FOR THIS HALF.					1	L	7	2 	3O				A19S0 					 
1995081800062	19950818	00062	CE 	1995	8	18	95ZZZX4004 	1	19950714	G	2730	053200135	TORQUE TUBE 		053200173 	CESSNA	172 	R172K 	2072431	CE 										LT ELEV	ADAPTER LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	736LC	1528 				R1722603				DURING ANNUAL INSPECTION, TORQUE TUBE ADAPTER ON THE LEFT ELEVATOR DISCOVERED LOOSE AND WORKING. A BALANCE CHECK OF THE	 ELEVATORS REVEALED THEM TO BE CLOSE TO THEIR LIMITS, BUT STILL SERVICEABLE. LEFT ELEVATOR WAS UNDER BALANCED AT 17.5 I	NCHES/POUNDS. ITS LIMITS ARE 0.0 TO 18.5 INCH/POUNDS. THE RIGHT ELEVATOR WAS UNDER BALANCED AT 24 INCHES/POUNDS. ITS 	LIMITS ARE 0.0 TO 24.5 INCH/POUNDS. RECOMMEND TIGHTER LIMITS ON CONTROL SURFACE AND MORE FREQUENT CHECKS OF CONTROL SUR	FACE BALANCE.		1	H	7	1 	3O				3A17 					 
1995081800063	19950818	00063	CE 	1995	8	18	95ZZZX4005 	1	19950724	G	3230	51413121	UPLOCK HOOK 			CESSNA	414 	414A 	2075907	CE 										RT MLG	WORN 	B			MGOR	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			CE	09	575JB	3243 				414A0426				AFTER GEAR SELECTION, RIGHT MAIN GEAR FAILED TO FULLY ENGAGE IN UPLOCK HOOK RESULTING IN CONTINUOUS BANGING. EMBODIMENT	 OF ME82-51 FAILED TO PRODUCE SATISFACTORY RESULT. UPLOCK HOOK, PN 5141312-1, REPLACED. NEW HOOK COMPARED WITH OLD HOO	K REVEALED WEAR LIKELY TO CAUSE HOOK TO BE FORCED AWAY FROM LEG ROLLER. MORE SPECIFIC INSPECTION CRITERION WITH DIMENSI	ONAL CHECKS WOULD PREVENT FUTURE OCCURRENCE.			1	L	7	2 	3O				A7CE 					 
1995081800064	19950818	00064	SW 	1995	8	18	95ZZZX4006 	1	19950622	G	2750		RELAY 			MOONEY	M20 	M20J 	5870219	SW 										FLAP MOTOR	TRIP BREAKER 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	205PP	495 				243061				A.C. INTERMITTENT TRIP 5 AMP CIRCUIT BREAKER WHEN FLAP HANDLE MOVED TO TAKEOFF POSITION OR FULL FLAPS. THEN, WHEN POWER	 WAS TURNED ON, CIRCUIT BREAKER WOULD POP. MOONEY HAS A NEW FLAP RELAY REPLACEMENT, PN 800376-503. VERY HARD TO TROUBL	ESHOOT BECAUSE THIS SERIES IS ONLY A/C THAT HAS PRE-SELECTED FLAP POSITIONS PUT TO TAKEOFF, AND FLAPS WILL MOVE TO POSIT	ION AND STOP WITHOUT PILOT HELP.			1	L	7	1 	3O				2A3 					 
1995081800065	19950818	00065	SO 	1995	8	18	95ZZZX4007 	1	19950803	G	3340	67436004	SWITCH 			PIPER 	PA28 	PA28161 	7102803	SO 										NAV/LIGHT	OVERHEAT 	G				K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			NE	01	8453Y	2100 				288216042				NAV/LIGHT SWITCH/REHOSTAT SHOWED SIGNS OF OVERHEATING ESPECIALLY WHERE THE WIRES WERE SOLDERED ON THE LUGS. SWITCH MAY 	BE TOO SMALL FOR THE EXISTING LOAD. SUBMITTED BY A & P IA, NR 021-52-9192.					1	L	7	1 	3O				2A13 					 
1995081800066	19950818	00066		1995	8	18	95ZZZX4008 	4	19950803	G	3421	36101P	HORIZONTAL GYRO 			PIPER 	PA28 	PA28161 	7102803	SO 										COCKPIT	CASE LEAK 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	8453Y	2100 			39096	288216042				THE CASE OF THE ARTIFICAL HORIZON HAS BLACK ELECTRICAL TAPE AROUND THE OUTSIDE OF THE CASE, SEALING THE UNIT. THE BLACK	 TAPE MELTS OR BECOMES SOFT DURING HIGH TEMPERATURES CAUSED BY THE SUN AND HIGH TEMPERATURES IN THE CABIN. DUE TO THE D	ETERIORATED TAPE THE UNIT IS NOT ACCURATE, AND, THERE IS A HISSING SOUND AT LOW VACUUM LEVELS. THE TAPE SEALS ITSELF AT	 HIGH VACUUM LEVELS, AND THE HISSING GOES AWAY. THE ARTIFICIAL HORIZON WAS MFG IN 1979, AND INSTALLED IN THE A/C IN 198	1. TWO FAILURES REPORTED BY THE SAME MECHANIC, A & P IA.		1	L	7	1 	3O				2A13 					 
1995081800067	19950818	00067	NE 	1995	8	18	95ZZZX4009 	3	19950608	G	6110	C792	BEARING 			BEECH 	1900 	1900D 	1154162	CE 						HARTZL	HCE4A	HCE4A3A 	NE 	PROPELLER	DAMAGED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										BEARING RECEIVED FROM HARTZELL IMPROPERLY PACKAGED. THE PACKAGING ALLOWED THE BEARING ASSY TO SEPARATE AND ALLOWED THE 	ROLLER PARTS TO IMPACT, THE BEARING RACE CAUSING THE ROLLERS TO BECOME DAMAGED. FIVE EACH BEARING BOXES RETURNED TO HAR	TZELL FOR CREDIT.				2	L	7	2 	4T			RT	A24CE 		5	C	P10NE	 
1995081800068	19950818	00068		1995	8	18	95ZZZX4010 	2	19950718	G	7322	16A108	GASKET 	FACET 																CARB INLET	LEAKING 	B			OL3R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	27					75032405					CARBURETOR LEAKING AT INLET FITTING DUE TO LACK OF THREAD SEALANT. GASKET NR 16-A108 IS INSTALLED IN CARBURETOR FITTING	.																		 
1995081800069	19950818	00069		1995	8	18	95ZZZX4011 	2	19950719	G	7322	16A108	GASKET 	PRECISION 	HA685 															CARB INLET	LEAKING 	B			OL3R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	27		80 			DL41204					CARBURETOR LEAKING AT INLET FITTING DUE TO LACK OF THREAD SEALANT. GASKET NR 16-A108 IS INSTALLED IN SAID FITTING.																			 
1995081800070	19950818	00070	EA 	1995	8	18	95ZZZX4012 	2	19950801	G	8520	LW18837	CAMSHAFT 			CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					ENGINE	WEAR 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	01	13599		1200 			17262390				CAMSHAFT WAS PURCHASED FROM AIR SUPPORT INTERNATIONAL, INC. CAMSHAFT WAS OVERHAULED AT AIRCRAFT SPECIALTIES SERVICES FA	A REPAIR STATION DD2R764K. CAMSHAFT SHOWED SIGNS OF PREMATURE WEAR. SUBMITTED BY EXECUTIVE FLYERS 141 SCHOOL LP8S302Q.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995081800071	19950818	00071	EA 	1995	8	18	95ZZZX4013 	2	19950801	G	8520	LW18837	CAMSHAFT 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					ENGINE	WEAR 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	01	2180E		532 			287916165				CAMSHAFT PURCHASED FORM AIR SUPPORT INTERNATIONAL, INC. CAMSHAFT WAS OVERHAULED AT AIRCRAFT SPECIALTIES SERVICES, FAA R	EPAIR STATION DD2R764K. CAMSHAFT SHOWED SIGNS OF PREMATURE WEAR. SUBMITTED BY EXECUTIVE FLYERS 141 SCHOOL LP8S302Q.					1	L	7	1 	3O	3	O		2A13 	E274				 
1995081800072	19950818	00072	SO 	1995	8	18	95ZZZX4014 	1	19950724	G	8120	93F0100004Y0300	HOSE ASSY 		LW10098 	PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					DIFF CONTROLLER	BRITTLE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	35269				DK0157	317952136	L632061A			THERE IS A NR 4 'AN' LOW PRESSURE HOSE ASSEMBLY WITH FIRE SLEEVE INSTALLED THAT RUNS FROM THE NR 4 90-DEGREE FITTING ON 	THE DIFFERENTIAL PRESSURE CONTROLLER TO THE OIL SUMP/INDUCTION HOUSING ASSEMBLY. THE END THAT ATTACHES TO THE CONTROLLE	R IS IN CLOSE PROXIMITY TO THE TURBOCHARGER WASTEGATE VALVE CAUSING HOSE TO BECOME VERY HARD AND BRITTLE. SUBMITTER SUG	GESTS THIS HOSE BE CHECKED CLOSELY EVERY ANNUAL AND ROUTINELY REPLACED EVERY 3 YEARS.			1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995081800073	19950818	00073	SO 	1995	8	18	95ZZZX4015 	1	19950724	G	8120	93F0100004Y0300	HOSE ASSY 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	LTIO540J2BD 	41533	EA 					DIFF CONTROLLER	BRITTLE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	3547B					318052017	L18368A			THERE IS A NR 4 'AN' LOW PRESSURE HOSE ASSEMBLY WITH FIRE SLEEVE INSTALLED THAT RUNS FROM THE NR 4 90-DEGREE FITTING ON 	 THE DIFFERENTIAL PRESSURE CONROLLER TO THE OIL SUMP/INDUCTION HOUSING ASSEMBLY. THE END THAT ATTACHES TO THE CONTROLLE	R IS IN CLOSE PROXIMITY TO THE TURBOCHARGER WASTEGATE VALVE CAUSING HOSE TO BECOME VERY HARD AND BRITTLE. SUBMITTER SUG	GESTS HOSE BE CHECKED CLOSELY EVERY ANNUAL AND ROUTINELY REPLACED EVERY 3 YEARS.			1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995081800075	19950818	00075	EA 	1995	8	18	95ZZZX4017 	2	19950801	G	8520	LW18837	CAMSHAFT 			CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					ENGINE	WEAR 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	01	61992		666 			17264943				CAMSHAFT WAS PURCHASED FROM AIR SUPPORT INTERNATIONAL, INC. CAMSHAFT WAS OVERHAULED AT AIRCRAFT SPECIALTIES SERVICES, F	AA REPAIR STATION DD2R764K. CAMSHAFT SHOWED SIGNS OF PREMATURE WEAR. SUBMITTED BY EXECUTIVE FLYERS 141 SCHOOL LP8S302Q	.				1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995081800076	19950818	00076	CE 	1995	8	18	95ZZZX4018 	1	19950528	G	2436	363800961	REGULATOR 	LAMAR 		BEECH 	36 	A36 	1151604	CE 										DC SYSTEM	MALFUNCTION 	D		A		A				UNSCHED LANDING 				H			ELECT. POWER LOSS-50 PC 			NR	NOT REPORTED 	1			SO	05	6ZM				1164	E2574				AIRCRAFT MADE FORCED LANDING (NO ELECTRICAL POWER). PILOT HAD TO PERFORM MANUAL LANDING GEAR EXTENSION. ON LANDING, NO	SE GEAR COLLAPSED (GEAR WAS NOT FULLY EXTENDED). NEW PROPELLER INSTALLED AND ENGINE RUN-UP, TROUBLESHOOTING DETERMINED 	A FAULTY VOLTAGE REGULATOR. DURING INSPECTION, A HEAVY COAT OF PAINT WAS FOUND ON BATTERY NEGATIVE TERMINAL. THIS MAY 	HAVE CONTRIBUTED TO VOLTAGE REGULATOR FAILURE. AFTER BATTERY TERMINAL WAS CLEANED, ENGINE RUN-UP AND ELECTRICAL SYSTEM 	CHECKED SERVICEABLE WITH NEW VOLTAGE REGULATOR INSTALLED.		1	L	7	1 	3O				3A15 					 
1995081800077	19950818	00077	SO 	1995	8	18	95ZZZX4019 	2	19950714	G	8530	629404	VALVE 			CESSNA	150 	150L 	2071826	CE 	CONT 	O200 	O200A 	17020	SO 					NR 3 CYL EXH	BINDING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	6836G	229 				15072336	681947A			INSPECTION REVEALED VALVE STEM TIGHT IN GUIDE DUE TO EXCESSIVE CARBON BUILD-UP. AFTER CLEAN-UP OF GUIDE, THE CLEARANCE 	WAS MEASURED AND DETERMINED TO BE IN LIMITS. CAUSE OF CARBON BUILD-UP, POSSIBLE RICH CARBURETOR. INSPECTION OF 3 REMAI	NING CYLINDERS ON ENGINE REVEALED NO PROBLEMS. ENGINE TT 4,082.0. TSM O/H, 979 HOURS.				1	H	7	1 	3O	3	O		3A19 	E252				 
1995013000124	19950130	00124	EA 	1995	1	30	95ZZZX402 	2	19950110	G	7414	10682560B	MAGNETO 	BENDIX 		PIPER 	PA32 	PA32R300 	7103213	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					ENGINE MAG	COIL FAILED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SW	17	47961	1820 			J179018G	32R7880029				PILOT NOTICED ENGINE WAS RUNNING ROUGH. AN EMERGENCY LANDING WAS MADE WITHOUT INCIDENT. MAGNETO REMOVED, BENCH CHECKED	, AND REPLACED.					1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995081800078	19950818	00078	CE 	1995	8	18	95ZZZX4020 	1	19950621	G	5312	0712206	BULKHEAD 			CESSNA	210 	210A 	2073408	CE 										FS 209	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	9443X	1900 				21057743				THE ATTACHING FLANGE OF THE HORIZONTAL BULKHEAD WAS FOUND CRACKED DURING THE ANNUAL INSPECTION WHERE IT ATTACHES TO THE 	STA 209.0 VERTICAL BULKHEAD. NOTED AREA WAS CRACKED 4 INCHES IN LENGTH. CRACK WAS ON THE CENTER ATTACHING FLANGE AND W	AS FOUND BY THE OWNER UPON REMOVAL OF THE TAIL CONE. SUSPECT CAUSE, EXCESSIVE PRELOAD .20 INCH DOWNWARD FORCE AT FORWAR	D END OF BULKHEAD. SUBMITTER RECOMMENDATION, INSPECT NOTED AREA AND IF CRACKED, ATTACH AN ANGLE/DOUBLER PICKING UP NOTE	D FASTENER HOLES ON BULKHEAD/FORWARD WITHOUT PRE-LOAD. NOTED FIX REQUIRES 337 FORM.		1	H	7	1 	3O				3A21 					 
1995081800079	19950818	00079	EA 	1995	8	18	95ZZZX4021 	2	19950312	G	7314	02532330003	FUEL PUMP 	PESCO 		STBROS	SD3 	SD330 	8100602	EU 	PWA 	PT6 	PT6A45R 	52043	EA 					LEFT ENGINE	STRIPPED 	D		A		A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			GL	13	336MV		392 		8519	SH3018	84070			DURING CRUISE AND LEVEL FLIGHT ON 3-12-94, ENGINE SHUT DOWN. CREW TRIED SEVERAL ATTEMPTS AT RESTART WITH NO SUCCESS. F	EATHERED ENGINE AND LANDED AT NEAREST AIRPORT. MAINTENANCE FOUND FUEL PUMP DRIVE SPLINES STRIPPED. REPLACED FUEL PUMP 	WITH OVERHAULED UNIT IAW MM 73-11-02. UNIT SENT BACK TO OVERHAUL SHOP FOR TEAR-DOWN REPORT.				2	H	7	2 	4T	4	T		A41EU 	E4EA				 
1995081800080	19950818	00080	EA 	1995	8	18	95ZZZX4022 	1	19950606	G	2421	721428	IDG 	SUNDSTRANDEM		CNDAIR	CL600 	CL6001A11 	1900302	EA 										NR 2	DEFECTIVE 	B			JO1R	O				OTHER 				H			ELECT. POWER LOSS-50 PC 			CR	CRUISE 	1			EA	25	91UC	4839 			313454	1051				THE PILOTS REPORTED THE NR 2 GENERATOR FAILED IN-FLIGHT AND WOULD NOT RESET. TROUBLESHOOTING REVEALED A VERY LOW RESIST	ANCE ACROSS GENERATOR FIELD WINDINGS. THE AIRCRAFT WIRING WAS CHECKED, THE NR 2 INTERGRATED DRIVE GENERATOR WAS REPLACE	D AND OPS CHECKED GOOD.				2	L	7	2 	4F			RT	A21EA 					 
1995081800081	19950818	00081	EA 	1995	8	18	95ZZZX4023 	1	19950609	G	2430	D31A	CONTACTOR 			CNDAIR	CL600 	CL6001A11 	1900302	EA 										NR 2 GENERATOR	DEFECTIVE 	B			JO1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	91UC	4849 			28387	1051				PILOTS REPORTED THE NR 1B HYDRAULIC PUMP CIRCUIT BREAKER TRIPPED AND COULD NOT BE RESET UNTIL NR 2 GENERATOR WAS TURNED 	OFF. TROUBLESHOOTING REVEALED A LARGE VOLTAGE DROP ACROSS ONE PHASE OF THE GENERATOR LINE CONTACTOR. THE NR 2 GENERATO	R LINE CONTACTOR WAS REPLACED AND PROBLEM WAS CURED. CLOSE INSPECTION OF THE CONTACTOR REVEALED THE A1 TERMINAL STUD NO	T FULLY SEATED IN INSULATOR. SLIGHT PRESSURE LOOSENED IT FULLY FROM INSULATOR. UNIT WAS REPLACED.			2	L	7	2 	4F			RT	A21EA 					 
1995081800082	19950818	00082	EA 	1995	8	18	95ZZZX4024 	2	19950726	G	8530	69602	TUBE 			ENSTRM	F28 	F28C 	3300407	GL 	LYC 	O360 	HIO360E1AD 	41514	EA 					ENG INDUCTION	DETACHED 	H				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			WP	27	5689T	2085 	85 			4742				HELICOPTER DEPARTED SCK AIRPORT AND MADE A FORCED LANDING IN A FIELD. INVESTIGATION FOUND AN INDUCTION TUBE HAD COME LO	OSE. RECOMMEND DURING OVERHAUL, ALL TUBES BE RE-SWAGED.					1	G	7	1 	3O	3	O		H1CE 	1E10				 
1995081800083	19950818	00083		1995	8	18	95ZZZX4025 	4	19950613	G	3422	258719343	GYRO 	HONEYWELL 	DG14A 	BEECH 	200 	B200 	1152922	CE 										COCKPIT DG	DEFECTIVE 	B			AC1R	A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			SO	01	356WC				82016459	BB1066				WHILE ON A PART 91 TRIP TO ROD FROM OWB, THE COPILOT'S HEADING FLAG ON THE HSI WOULD NOT RETRACT. AFTER SEVERAL ATTEMPT	S TO AUTOSLAVE AND FREE-SLAVE THE DIRECTIONAL GYRO, TRIP WAS ABORTED AND RETURNED TO HOME BASE. WERE ABLE TO DUPLICATE 	PROBLEM IN THE HANGAR TO A DEGREE, BUT THE FLAG WOULD RETRACT. INSPECTION OF THE AIRCRAFT RECORDS REVEALED THE DG14A HA	D APPROXIMATELY 1,507 HRS SINCE OVERHAUL. THIS IS THE USUAL TIME FOR AN OVERHAUL ON THIS TYPE OF UNIT. A LOANER UNIT W	AS ORDERED AND INSTALLED AND THE SYSTEM WORKED NORMALLY.		1	L	7	2 	4T				A24CE 					 
1995081800084	19950818	00084	CE 	1995	8	18	95ZZZX4026 	1	19950613	G	2430	51S39006F	GEN CONTROL 	LUCAS 		CESSNA	500 	560CESSNA 	2076750	CE 										LT GENERATOR	DEFECTIVE 	B			AC1R	O				OTHER 				H			ELECT. POWER LOSS-50 PC 			CR	CRUISE 	1			SO	01	2430	2079 			7943AB	560069				PILOTS REPORTED WHILE IN CRUISE FLIGHT, THE RT GEN OFF-LIGHT ILLUMINATED. ALSO, NOTED THE LT GEN VOLTAGE WAS FLUCTUATIN	G UP TO 30 VOLTS. ATTEMPTS MADE TO BRING RT GEN BACK ON LINE, HOWEVER, IT WOULD NOT STAY ON. PILOTS ELECTED TO TURN RT	 GEN OFF AND CONTINUE FLIGHT TO HOME BASE. WEATHER AT THE TIME WAS VFR. DISCUSSION REVEALED THE RT GEN VOLTAGE WAS OKA	Y, BUT LT GEN WAS FLUCTUATING TO AS HIGH AS 30 VOLTS. INSPECTED BOTH SETS OF GEN BRUSHES FOR CONDITION. BOTH SETS OF B	RUSHES REPLACED AS PRECAUTIONARY MEASURE. LT GEN CONTROL UNIT REPLACED AS BEING SUSPECT ITEM THAT WOULD CAUSE OVERVOLTA	GE CONDITION. TEAR-DOWN REPORT CONFIRMED THE PROBLEM.	2	L	7	2 	4F			RT	A22CE 					 
1995081800085	19950818	00085	CE 	1995	8	18	95ZZZX4027 	1	19950627	G	3020	555225090	INLET 			CESSNA	500 	560CESSNA 	2076750	CE 										RT ANTI-ICE	DEFORMED 	B	L	A	AC1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	70TG					560069				THE RIGHT INLET ANTI-ICE PICCOLOTUBE WAS FOUND SEVERELY DEFORMED AT THE ATTACH POINT. HOWEVER, THERE WERE NO CRACKS IN 	THE TUBE WHICH IS A COMMON OCCURRENCE. A REPLACEMENT INLET WAS ORDERED AND INSTALLED. THIS WAS INLET NR 3 THAT WAS REM	OVED FROM THE RIGHT SIDE. THIS INLET HAD THE LONGEST TIME IN SERVICE OF THE 3 THAT HAD BEEN ON THE RIGHT SIDE. THE FIR	ST 2 INLETS HAD 540.6 HOURS AND 384.2 HOURS RESPECTIVELY. THIS INLET HAD ACCRUED 1,245.2 HOURS SINCE INSTALLATION.			2	L	7	2 	4F			RT	A22CE 					 
1995081800086	19950818	00086	CE 	1995	8	18	95ZZZX4028 	1	19950613	G	2131	1520T10010	PNEUMOSTAT 			BEECH 	200 	B200 	1152922	CE 										LT BLEED FLOW	FAULTY 	B			AC1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	356WC		118 		2365	BB1066				PILOTS REPORTED THE LT BLEED AIR FLOW CONTROL UNIT WAS NOT FLOWING AT ALTITUDE. WITH THE RT FLOW CONTROL UNIT SELECTED 	OFF, THE CABIN ALTITUDE CLIMBED AT ABOUT 2,500 FPM. PERFORMED THE FLOW CONTROL UNIT TEST IN THE BEECHCRAFT 200 MM 21-10	-00, PAGES 207 THROUGH 212. UNIT IN QUESTION FAILED THE CONTROL HEAD AND PNEUMOSTAT CHECK-OUT, HOWEVER, THE UNIT PASSED	 THE OTHER TESTS. AN EXCHANGE FLOW CONTROL UNIT AND PNEUMOSTAT WAS ORDERED AND INSTALLED. THE NEXT FLIGHT UNIT WAS CHE	CKED AND FUNCTIONED NORMALLY.		1	L	7	2 	4T				A24CE 					 
1995081800087	19950818	00087	CE 	1995	8	18	95ZZZX4029 	1	19950613	G	2131	1520T100109	FLOW CONTROL 	TALLEY 		BEECH 	200 	B200 	1152922	CE 										LT BLEED	MALFUNCTION 	B	L		AC1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	356WC		118 		1972	BB1066				PILOTS REPORTED THE LT BLEED AIR FLOW CONTROL UNIT WAS NOT FLOWING AT ALTITUDE. WITH THE RT FLOW CONTROL UNIT SELECTED 	OFF, THE CABIN ALTITUDE CLIMBED AT ABOUT 2,500 FPM. PERFORMED THE FLOW CONTROL UNIT TEST IN THE BEECHCRAFT 200 MM 21-10	-00, PAGES 207 THROUGH 212. UNIT IN QUESTION FAILED THE CONTROL HEAD AND PNEUMOSTAT CHECK-OUT, HOWEVER, THE UNIT PASSED	 THE OTHER TESTS. AN EXCHANGE FLOW CONTROL UNIT AND PNEUMOSTAT WAS ORDERED AND INSTALLED. THE NEXT FLIGHT UNIT WAS CHE	CKED AND FUNCTIONED NORMALLY.		1	L	7	2 	4T				A24CE 					 
1995081800088	19950818	00088	EA 	1995	8	18	95ZZZX4030 	2	19950605	G	7250	310209404	GAS GENERATOR 								PWA 	PT6 	PT6A65B 	52043	EA 					GAS GEN CASE	DAMAGED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01										PART RECEIVED FROM EDM IN OVERHAULED CONDITION. WHEN GAS GENERATOR CASE WAS ASSEMBLED AND RUN ON THE TEST CELL FOR EVAL	UATION, ENGINE RAN HOT AND TOO FAST. ALL CORRECTIVE ACTIONS FAILED TO CORRECT THE PROBLEM. THE GAS GENERATOR CASE WAS 	REPLACED AND THE ASSEMBLED ENGINE RAN WELL WITHIN LIMITS. SUSPECT HIDDEN CRACKS OR DAMAGE TO THE CASE AND SAID CASE HAS	 BEEN SENT TO PWC FOR EVALUATION.								4	T			E4EA				 
1995081800089	19950818	00089	EA 	1995	8	18	95ZZZX4031 	2	19950621	G	7260	3040026	HOUSING 								PWA 	PT6 	PT6A65B 	52043	EA 					GAS GEN AGB	BORE OVERSIZE 	B			MAXR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	13					PWC95M376					THE HOUSING WAS RECEIVED FROM PWC AFTER THEY REPAIRED THE HOUSING AND REINSPECTED ALL BEARING BORES. THE BEARING BORES 	WERE MEASURED BY DTS INSPECTION DEPARTMENT AND FOUND OUT OF TOLERANCE. (OVERSIZED). PART RETURNED TO PWC FOR REWORK AND	/OR REPAIR.									4	T			E4EA				 
1995081800090	19950818	00090	EA 	1995	8	18	95ZZZX4032 	2	19950725	G	7320	311454801	LEVER 			BEECH 	200 	200BEECH 	1152920	CE 	PWA 	PT6 	PT6A41 	52043	EA 					FCU ACTUATOR	JAMS 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	13	2883					BB144	PCE80042			LEFT POWER LEVER WOULD INTERMITTENTLY STOP BEFORE FULL TRAVEL IN QUADRANT, LIMITING ENGINE SPEED TO APPROXIMATELY 80 PER	CENT N1. ENGINE WAS NEWLY OVERHAULED, AND FCU LEVER, PN 311458-01, WAS INSTALLED DURING C/W SB 3304. FCU LEVER FOUND J	AMMING ON PROPELLER REVERSE CONTROL FOLLOWING LEVER. REINSTALLED ORIGINAL FCU LEVER, PN 3010454, NO FURTHER PROBLEMS NO	TED. THIS PROBLEM IS ADDRESSED BY SB 3310, WHICH INSTALLS LEVER, PN 3119355-01.			1	L	7	2 	4T	4	T		A24CE 	E4EA				 
1995081800091	19950818	00091	SW 	1995	8	18	95ZZZX4033 	1	19950710	G	2432	G6381E	BATTERY 	GILLBATT 		GULSTM	690TP 	690B 	7630516	SW 										ELON CONNECTOR	DAMAGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	02	771BA	500 			G01471981	11429				UPON ROUTINE INSPECTION. LEAD FOUND SPRAYED ALL OVER THE BATTERY INTERIOR. THE CONNECTOR BOX SEALANT WAS MELTED AND CRA	CKED. SEALANT AND LEAD ALSO CAME OUT CONNECTOR PIN AND ALSO RUINED THE ELON CONNECTOR BEYOND FURTHER USE.					1	H	7	2 	3T				2A4 					 
1995081800092	19950818	00092	SO 	1995	8	18	95ZZZX4034 	1	19950710	G	5753	JW1217R	FITTING 			LKHEED	1329 	132925 	5263125	SO 										RT WING INB FLAP	CRACKED 	B			FGQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	701JH	7264 				5230				WHILE PERFORMING SCHEDULED MAINTENANCE ON THE TRAILING EDGE FLAP ACTUATORS, A CRACK WAS NOTICED IN THE INBD FITTING OF T	HE RT WING INBD FLAP. THE FLAPS WERE PREVIOUSLY RIGGED APPROXIMATELY 1 INCH ABOVE THE FAIRED POSITION WHEN FULL UP. TH	E MM GIVE .06 INCH TOLERANCE TO THE FAIRED POSITION. IT IS POSSIBLE THE OUT-OF-RIG CONDITION CAUSED UNDUE STRESS ON THE	 FITTING.			2	L	7	4 	4F				2A1SO 					 
1995081800095	19950818	00095	GL 	1995	8	18	95ZZZX4037 	2	19950802	G	7250	6898735	TURBINE 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	LOCKED-UP 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4282X	6472 	2957 			180253D	CAE833827			N2 LOCKED UP. UNIT SENT IN FOR SAME PROBLEM 356.7 HOURS AGO. REMOVED SN CAT 33968 AND SENT TO BE REPAIRED ON ALLISON R	EPORT NR A160209.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995081800096	19950818	00096	WP 	1995	8	18	95ZZZX4038 	1	19950727	G	6220	369A10045	PIN 			HUGHES	369 	369D 	4470706	WP 										M/R HUB	BROKEN 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R	3818 			0098840634	1151D				ON POST-FLIGHT, FOUND M/R BLADE PIN BROKEN AT THE END WHERE THE THREADS STOP. THIS IS THE SAME SERIAL NUMBERED PREFIX O	F 2 OTHER BROKEN BLADE PINS IN THE LAST 12 MONTHS.					1	G	7	1 	3U				H3WE 					 
1995081800097	19950818	00097	GL 	1995	8	18	95ZZZX4039 	2	19950622	G	7260		GEARBOX 			AEROSP	AS355 	AS355F1 	8680810	EU 	ALLSN 	250C 	250C20F 	03013	GL 					NR 1 ENGINE	FAILED 	E				A				UNSCHED LANDING 				J	X		WARNING INDICATION 	ENGINE FLAMEOUT 		CR	CRUISE 	1			SW	03	5774M	11516				5009	CAE840464			INBOUND FOR OFFSHORE PLATFORM, PILOT REPORTED NR 1 ENGINE CHIP LIGHT ILLUMINATED, AIRCRAFT YAWED, ENGINE FLAMED OUT. LA	NDED AT ONSHORE WITHOUT INCIDENT. INVESTIGATION REVEALED BOTH ENGINE ACCESSORY GEARBOX CHIP PLUGS COVERED WITH METAL. N	1 DOES NOT TURN FREELY. ENGINE TSO, 3,199:55.				1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1995081800583	19950818	00583	SO 	1995	8	18	95ZZZX4060 	2	19950615	G	7320	RSA7AD1	SERVO 	BENDIX 		BEECH 	58 	58P 	1152744	CE 	CONT 	O520 	TSIO520WB 	17040	SO 					FUEL SERVO	DIAPHRAGM TORN 	D	L			O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			SO	01	3807T	2480 	494 		56467	TJ332	L518458			DURING CRUISE, RT MAG INTERMITTENT. AT 14,000 FEET ALTITUDE, FUEL VENTING OUT OF LT ENGINE INBOARD UPPER COWL VENT. FO	UND FUEL SERVO DIAPHRAGM TORN ALLOWING FUEL INTO AIR SIDE. FUEL VENTED OUT MAG FILTER AND INTO MAG CAUSING MISFIRE.					1	L	7	2 	3O	3	O		A23CE 	E8CE				 
1995081800585	19950818	00585	NE 	1995	8	18	95ZZZX4062 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061858 						GE 	CF6 	CF680C2A5 		NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E13NE				 
1995081800586	19950818	00586	NE 	1995	8	18	95ZZZX4063 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061865 						GE 	CF6 	CF680C2A5 		NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E13NE				 
1995081800587	19950818	00587	NE 	1995	8	18	95ZZZX4064 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061874 						GE 	CF6 	CF680C2A5 		NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E13NE				 
1995081800588	19950818	00588	NE 	1995	8	18	95ZZZX4065 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061886 						GE 	CF6 	CF680C2A5 		NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E13NE				 
1995081800589	19950818	00589	NE 	1995	8	18	95ZZZX4066 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061888 						GE 	CF6 	CF680C2A5 		NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E13NE				 
1995081800590	19950818	00590	NE 	1995	8	18	95ZZZX4067 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061889 						GE 	CF6 	CF680C2A5 		NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E13NE				 
1995081800591	19950818	00591	NE 	1995	8	18	95ZZZX4068 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061893 						GE 	CF6 	CF680C2A5 		NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E13NE				 
1995081800592	19950818	00592	NE 	1995	8	18	95ZZZX4069 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061896 						GE 	CF6 	CF680C2A5 		NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E13NE				 
1995081800593	19950818	00593	NE 	1995	8	18	95ZZZX4070 	2	19950719	G	7321	1037642	SCREW 	WOODWARD 	8061526 						GE 	CFM56 	CFM565A 	13802	NE 					FUEL CONTROL	BROKEN 	B	L		UU2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03										WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIO	NAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH I	S ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL F	ROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERL	Y, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS	 OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION.						4	F			E29NE				 
1995081800594	19950818	00594	EU 	1995	8	18	95ZZZX4071 	1	19950701	G	3213	6401412	STRUT 			PILATS	PC6T 	PC6CH2 	7090214	EU 										MLG STRUT LT	CORRODED 	D	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	394R					599				HOT TURBINE EXHAUST IS DIRECTED ON TO LANDING GEAR V-STRUT (LEFT SIDE), CAUSING CORROSION INSIDE STEEL V-STRUT AT ABOUT 	MID-POINT OF STRUT. THIS UNIT HAD ABOUT 18 INCHES OF CORROSION.					1	H	7	1 	3T				7A15 					 
1995081800595	19950818	00595	WP 	1995	8	18	95ZZZX4072 	1	19950717	G	6230	369A70033	BEARING ASSY 			HUGHES	369 	369D 	4470706	WP 										M/R SWASHPLATE	BINDING 	D		A		K				NONE 				F			FLT CONT AFFECTED 			LD	LANDING 	1			WP	05	8620F	84 			6474	770160D				SWASHPLATE UNIBALL BINDING. PILOT FELT STIFFENING OF CONTROL ON LANDING. AFTER ALL CONTROLS WERE CHECKED, SWASHPLATE W	AS REMOVED. UNIBALL COULD NOT BE MOVED BY HAND. SWASHPLATE BEARING ASSY WAS REPLACED. AIRCRAFT TEST FLOWN AND RELEASE	D.				1	G	7	1 	3U				H3WE 					 
1995081800598	19950818	00598	GL 	1995	8	18	95ZZZX4075 	3	19950626	G	6114	D3695C91	HUB 			CESSNA	337 	T337B 	2075707	CE 						MCAULY	2AF34C	D2AF34C91 	GL 	NR 1 SOCKET	CRACKED 	B			ME4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	2432S	3102 	93 			3376732		674450		PROPELLER RECEIVED FOR REPAIR DUE TO RED DYE OIL LEAK. AFTER DISASSEMBLY, HUB DISCOVERED CRACKED IN NR 1 BLADE SOCKET. 	 THREE THREADS IN, 4 TO 7 O'CLOCK POSITION. PROPELLER WAS OVERHAULED WITH A NEW HUB, NO OTHER DEFECTS NOTED. CRACK DIS	COVERED USING A 10X POWER MICROSCOPE.				1	H	7	2 	3O				A6CE 		5	C	P5EA	 
1995081800600	19950818	00600	WP 	1995	8	18	95ZZZX4077 	1	19950607	G	5320		SPAR WEB 			DOUG 	DC9 	DC932 	3022066	WP 										RT FS 965	CRACKED 	B			MWER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	800DM					47466				FOUND WEBBING CRACKED IN THREE PLACES AT STA 965, RT SIDE FORWARD ENGINE PYLON SPAR INTERIOR (FWD BULKHEAD OF LAV). FAT	IGUE IS SUSPECT CAUSE. PERFORMED NDT OF SPAR FASTENERS AND SURROUNDING AREA, NO OTHER DEFECTS NOTED. FABRICATED NEW WE	BBING FROM 7075-T6 MATERIAL. RETURNED AIRCRAFT TO SERVICE.				2	L	7	2 	4F				A6WE 					 
1995081800601	19950818	00601	SW 	1995	8	18	95ZZZX4078 	1	19950201	G	5751	2734042048	BRACKET 			SWRNGN	SA226 	SA226TC 	8780404	SW 										LT AILERON	CRACKED 	B			ATZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	329BA	22513				TC238				FOUND AILERON BRACKET ASSY CRACKED AND BEARING ASSY RIVETS ALL SHEARED. BEARING ASSY REINSTALLED FOR FERRY FLIGHT. SUS	PECT DAMAGE DUE TO LIFTING AIRCRAFT WITH AIRBAGS UNDER AILERON.					1	L	7	2 	4T				A8SW 					 
1995081800602	19950818	00602	CE 	1995	8	18	95ZZZX4079 	1	19950720	G	5312	551104013	BULKHEAD BOX 			CESSNA	501 	501 	2076603	CE 										FWD PRESS BLKHD	CRACKED 	B	S		R2JR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	888MJ	7156 				5010446				WHILE TROUBLESHOOTING PRESSURIZATION LEAKS WITH PRESSURIZATION CART, FOUND AIR LEAKAGE AT FORWARD PRESSURE BULKHEAD AT C	ENTER BOX , .80 INCH AND .30 INCH CRACK FOUND AT RIVET CONNECTING ANGLE TO BULKHEAD. MANUFACTURER HAD NO APPROVED REPAI	R. OBTAINED DER APPROVAL AND RIVETED PATCH WAS INSTALLED. SUBMITTER SUGGESTS VISUAL INSPECTION OF AREA OFTEN ON OLDER 	AIRCRAFT.			1	L	7	2 	4F				A27CE 					 
1995081800603	19950818	00603	EU 	1995	8	18	95ZZZX4080 	1	19950407	G	2913	65WE010305	PUMP 			HWKSLY	DH125 	HS125600A 	4230158	EU 										NR 1 HYD	BUSHING CRACKED 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	500R	410 			A224303A5	256068				HYDRAULIC PUMPS REMOVED TO COMPLY WITH 150-HR INSPECTION UNDER SUPPLEMENT 'F'. THESE PUMPS WERE POST-MODIFICATION 25320	2 WITH A PLASTIC BUSHING INSERT IN THE PUMP END. REMOVED THE DRIVE SHAFTS TO INSPECT THE BUSHING INSERTS. ON THE NR 1 	HYDRUAULIC PUMP, DISCOVERED THE INSERT WAS CRACKED IN SEVERAL PLACES AND BEING HELD IN PLACE ONLY BY THE INTERNAL SPLINE	 OF THE PUMP. NR 2 PUMP HAD THE INSERT BADLY WORN, BUT STILL IN ONE PIECE. AN INSPECTION OF THE INTERNAL SPLINES OF NR	 2 PUMP REVEALED THEY WERE WORN ALMOST TO THE POINT OF FAILURE. NR 1 PUMP'S INTERNAL SPLINES WERE OK. REPLACED NR 2 PU	MP WITH A PRE-MOD 253202 AND INSTALLED NEW INSERT IN NR 1 PUMP. HYD SYS SERVICED, GRD RAN, A/C RETURNED TO SERVICE.	2	L	7	2 	4J				A3EU 					 
1995081800689	19950818	00689	SW 	1995	8	18	95ZZZX4081 	1	19950627	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	171AL		512 			52064				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 512.4.				1	G	7	1 	3U			NC	H2SW 					 
1995081800690	19950818	00690	SW 	1995	8	18	95ZZZX4082 	1	19950627	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	171AL		512 			52064				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 512.4.				1	G	7	1 	3U			NC	H2SW 					 
1995081800691	19950818	00691	SW 	1995	8	18	95ZZZX4083 	1	19950627	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	175AL		411 			52117				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 410.6.				1	G	7	1 	3U			NC	H2SW 					 
1995081800692	19950818	00692	SW 	1995	8	18	95ZZZX4084 	1	19950627	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	175AL		411 			52117				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 410.6.				1	G	7	1 	3U			NC	H2SW 					 
1995081800693	19950818	00693	SW 	1995	8	18	95ZZZX4085 	1	19950627	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	202AL		738 			1324				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 737.8.				1	G	7	1 	3U				H2SW 					 
1995081800694	19950818	00694	SW 	1995	8	18	95ZZZX4086 	1	19950627	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	202AL		738 			1324				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 737.8.				1	G	7	1 	3U				H2SW 					 
1995081800695	19950818	00695	GL 	1995	8	18	95ZZZX4087 	2	19950609	G	7210	A6887772	BEARING 		6894171 	BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20B 	03013	GL 					GEARBOX	GALLED 	B			ALGR	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	209AL	132 			032	1044	8800956BA			DISASSEMBLED GEARBOX DUE TO 'ENGINE CHIP LIGHT'. DISCOVERED THE P.T.O. ROLLER BEARING TO BE 'GALLING ROLLERS'. CAUSE U	NKNOWN.					1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995081800696	19950818	00696	SW 	1995	8	18	95ZZZX4088 	1	19950627	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27545		468 			45234				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 467.7.				1	G	7	1 	3U				H2SW 					 
1995081800697	19950818	00697	SW 	1995	8	18	95ZZZX4089 	1	19950627	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27545		468 			45234				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 467.7.				1	G	7	1 	3U				H2SW 					 
1995013000131	19950130	00131	EA 	1995	1	30	95ZZZX409 	2	19950104	G	7421	SR88	SPARK PLUG 			CESSNA	172 	172P 	2072436	CE 	LYC 	O320 	O320D2J 	41508	EA 					CENTER ELECTRODE	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	5227K	100 				17274020				SUBMITTER STATES A VERY POOR SERVICE FROM AUBURN SPARK PLUGS. HAS NOTED CENTER ELECTRODE PORCELAIN FAILS. FAILED ELECT	RODE PIECES THEN CAN CAUSE DAMAGE TO VALVES, SEATS, RINGS, AND PISTONS. SUBMITTER RECOMMENDS TO NOT USE THESE SPARK PLU	GS IN AIRCRAFT ENGINES.				1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995081800698	19950818	00698	SW 	1995	8	18	95ZZZX4090 	1	19950627	G	6410	206016201127	BLADE 		206011810125	BELL 	206 	206L1 	1182107	SW 										FEATHER BEARING	BEARING WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27554	383 			CS7181	45246				TAIL ROTOR ASSEMBLY REMOVED BECAUSE IT WOULD NOT BALANCE. HIGH FREQUENCY VIBRATION DURING PHASE INSPECTION. FOUND 2 EA	CH 206-010-765-001 BEARINGS WORN BEYOND LIMITS.					1	G	7	1 	3U				H2SW 					 
1995081800699	19950818	00699	SW 	1995	8	18	95ZZZX4091 	1	19950627	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2755N		662 			45243				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 662.2.				1	G	7	1 	3U				H2SW 					 
1995081800700	19950818	00700	SW 	1995	8	18	95ZZZX4092 	1	19950627	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2755N		662 			45243				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 662.2.				1	G	7	1 	3U				H2SW 					 
1995081800701	19950818	00701	SW 	1995	8	18	95ZZZX4093 	1	19950627	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3190P		517 			45779				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.4.				1	G	7	1 	3U				H2SW 					 
1995081800702	19950818	00702	SW 	1995	8	18	95ZZZX4094 	1	19950627	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3190P		517 			45779				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001,	 SPACERS, 4 EACH, 206-010-337-001, BEARINGS, 2 EACH, 206-010-338-003, BUSHINGS, 2 EACH, NAS6605D64, BOLTS, 1 EACH, 206-0	10-470-101, BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.4.				1	G	7	1 	3U				H2SW 					 
1995081800703	19950818	00703	SW 	1995	8	18	95ZZZX4095 	1	19950706	G	5320	205030279131	WORK DECK 		250030279131	BELL 	412 	412 	1182202	SW 										RIGHT HAND	SEPARATION 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	397AL	2814 				36012				DAILY INSPECTION FOUND WORK DECK PANELS TOP SKIN SEPARATED OVER A LARGE AREA. ALSO, UNDERSIDE OF PANEL IS SWELLED. SUS	PECT CAUSED BY PROLONGED EXPOSURE TO HIGH TEMPERATURES.					1	G	7	2 	4U				H4SW 					 
1995081800704	19950818	00704	SW 	1995	8	18	95ZZZX4096 	1	19950706	G	5412	212060901203	FIREWALL 			BELL 	412 	412 	1182202	SW 										STRAPS	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	397AL					36012				DURING REPLACEMENT OF ENGINE SERVICE DECK, FOUND THE STRAPS ON UPPER FIREWALL WHERE THE AIR MANAGEMENT SYSTEM BOLTS ON, 	HAD SEVERE CORROSION. CAUSED BY ALUMINUM BEING SANDWICHED BETWEEN STAINLESS STEEL. SUSPECT CAUSED DISSIMILAR METAL COR	ROSION.				1	G	7	2 	4U				H4SW 					 
1995081800705	19950818	00705	SW 	1995	8	18	95ZZZX4097 	1	19950706	G	5412	212061207153	FIREWALL 			BELL 	412 	412 	1182202	SW 										SEAL RETAINER	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	397AL					36012				DURING REPLACEMENT OF WORK DECK/ENGINE DECK, FOUND SEAL RETAINERS CORRODED. ALUMINUM RETAINERS ON STAINLESS STEEL PARTS	.					1	G	7	2 	4U				H4SW 					 
1995081800706	19950818	00706	SW 	1995	8	18	95ZZZX4098 	1	19950706	G	5412	212061207154	FIREWALL 			BELL 	412 	412 	1182202	SW 										SEAL RETAINER	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	397AL					36012				DURING REPLACEMENT OF ENGINE DECK/WORK DECK, FOUND SEAL RETAINERS CORRODED. ALUMINUM RETAINERS RIVETED TO STAINLESS STE	EL PARTS.					1	G	7	2 	4U				H4SW 					 
1995013000132	19950130	00132	EA 	1995	1	30	95ZZZX410 	2	19950104	G	8520	10646	CONNECT ROD 			PIPER 	PA32 	PA32300 	7103212	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					ENGINE	WRONG BOLT 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	99	2866D					32790163	L1944948A			FOLLOWING CYLINDER REMOVAL, FOUND P/N 75061 CONNECTING ROD BOLTS HAD BEEN INSTALLED INSTEAD OF P/N 75060 BOLTS. SUGGEST	 ALL PARTS AND NUMBERS BE LISTED IN THE LOG BOOKS AT OVERHAUL.					1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995081800708	19950818	00708	NE 	1995	8	18	95ZZZX4100 	1	19950622	G	7120	7630907007053	STRUT 			SKRSKY	S76 	S76A 	8143006	NE 										ENGINE DECK	DAMAGED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	709AL		1500 			760278				DURING 1,500 HOUR INSPECTION, FOUND STRUT WITH MECHANICAL DAMAGE. PART UNSERVICEABLE.						1	G	7	2 	3U				H1NE 					 
1995013000133	19950130	00133	EA 	1995	1	30	95ZZZX411 	2	19950107	G	8530	ECI12967CP	RINGS 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	LTIO540J2BD 	41533	EA 					NR 1 CYLINDER	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	59764		151 			317652037	L148468A			OIL BLOWING OUT BREATHER. FOUND NR 1 CYLINDER AT 10/80. PULLED CYLINDER AND FOUND COMP. RINGS BROKEN IN MANY PIECES AB	OUT .25 INCH TO 2.5 INCH. THESE RINGS ARE OF WRONG COMPOSITION. (BRITTLE).					1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995013000136	19950130	00136	EA 	1995	1	30	95ZZZX414 	2	19950102	G	8530	71828	CYLINDER 			GULSTM	AA1 	AA1B 	0631206	SO 	LYC 	O235 	O235C2C 	41505	EA 					ENGINE	SEPARATION 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			NE	01	9654L	3800 	2550 			AA1B0154	L1185815			AIRCRAFT ENGINE, WHILE IN-FLIGHT, SUFFERED BARREL-TO-HEAD SEPARATION. SUSPECT CAUSE SEVERE METAL FATIGUE FROM WELDING M	ULTIPLE TIMES AND POSSIBLE IMPROPER WELDING PRACTICES AND MULTIPLE HEAT CYCLES. LYCOMING DOES NOT MANUFACTURE NEW CYLIN	DERS FOR THIS ENGINE. IF THEY DID, THIS WOULD NOT CONTINUE TO HAPPEN. SUBMITTER RECOMMENDS LYCOMING BE FORCED TO SUPPO	RT THE O-235C SERIES ENGINE. ALSO, MORE CAREFUL INSPECTION OF BARREL-TO-HEAD AREAS BY MAINTENANCE PERSONNEL AND OPERATO	RS.		1	L	7	1 	3O	3	O		A11EA 	E223				 
1995082500080	19950825	00080	SW 	1995	8	25	95ZZZX4178 	1	19950627	G	6410	206016201127	BLADE 		206016201127	BELL 	206 	206L3 	1182108	SW 										FEATHER BEARINGS	BEARING CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	364AL	478 			CS6598	51434				TAIL ROTOR REMOVED FROM AIRCRAFT BECAUSE OF HIGH FREQUENCY VIBRATION IN-FLIGHT. FOUND 4 EACH BEARINGS, PN 206-010-765-0	01, WITH INNER RACES CRACKED.					1	G	7	1 	3U				H2SW 					 
1995082500081	19950825	00081	SW 	1995	8	25	95ZZZX4179 	1	19950627	G	6410	206016201127	BLADE 		206016201127	BELL 	206 	206L3 	1182108	SW 										FEATHER BEARINGS	BEARING CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	364AL	478 			CS6620	51434				TAIL ROTOR REMOVED FROM AIRCRAFT BECAUSE OF HIGH FREQUENCY VIBRATION IN-FLIGHT. FOUND 4 EACH BEARINGS, PN 206-010-765-0	01, WITH INNER RACES CRACKED.					1	G	7	1 	3U				H2SW 					 
1995082500225	19950825	00225	EA 	1995	8	25	95ZZZX4181 	2	19950803	G	8530	7380685	PUSHROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					CYL NR 3	MUSHROOMED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	757UR					15280018	L2016515			CYLINDER NR 3 REMOVED FOR LOW COMPRESSION, FOUND EXCESSIVE CLEARANCE BETWEEN EXHAUST VALVE AND ROCKER ARM CAUSED BY PUSH	ROD THAT HAD MUSHROOMED UNDER BALL END.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995082500226	19950825	00226	SO 	1995	8	25	95ZZZX4182 	1	19950727	G	2720	6345T00	SUPPORT 			PIPER 	PA28 	PA28140 	7102802	SO 										RUDDER BAR	CRACKED 	H		A		O				OTHER 				F			FLT CONT AFFECTED 			CR	CRUISE 	1			EA	05	98130	7730 				2826057				RUDDER PEDALS SPRUNG TO THREE-QUARTER RIGHT RUDDER FORWARD DURING FLIGHT. COULD NOT BE CORRECTED WITH TRIM. INSPECTION	 REVEALED CENTER SUPPORT CRACKED BOTH SIDES IN BEND RADIUS FROM OUTSIDE TOWARD CENTER. UNABLE TO RERIG RUDDER. DIFFICU	LT TO LOCATE BECAUSE OF POSITION IN AIRCRAFT. REPLACEMENT AND RERIGGING CORRECTED ALL PROBLEMS. SUBMITTER STATES SHOUL	D HAVE A SPECIAL INSPECTION NOTE IN 100-HOUR CHECKLIST DUE TO LOCATION NEAR OTHER FLIGHT CONTROLS AND PROBABILITY IF SER	IOUS FLIGHT CONTROL MALFUNCTIONS.		1	L	7	1 	3O				2A13 					 
1995082500227	19950825	00227	SO 	1995	8	25	95ZZZX4183 	1	19950731	G	7430	103572001	SWITCH 	BENDIX 		PIPER 	PA28 	PA28161 	7102803	SO 										IGNITION	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	6461C					287816425				AD 76-07-12 ON BENDIX IGNITION SWITCHES SAYS THAT INSTALLATION OF NEW SWITCHES WITH THE DATE CODE STAMPED ON THEM WILL E	LIMINATE THE REPETITIVE FUNCTION CHECK, BUT HAVE FOUND NEW SWITCHES (TWO) THAT HAVE FAILED THE FUNCTION CHECK AFTER ONLY	 140 AND 160 HOURS OF SERVICE.				1	L	7	1 	3O				2A13 					 
1995082500228	19950825	00228	CE 	1995	8	25	95ZZZX4184 	1	19950627	G	3230	SM50D7	RELAY 	CUTLERHAM 		BEECH 	33 	F33A 	1151425	CE 										MLG	FAILED 	D				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			WP	07	5587K	5695 			SN006	CE1392				LANDING GEARBOX BOTTOMED OUT IN THE GEAR UP POSITION DUE TO FAILURE OF RELAY. EXTREME FORCE WAS REQUIRED WITH BOOT ON T	HE GEAR HANDLE TO BREAK LOOSE BEFORE GEAR COULD BE CRANKED DOWN. NOTE: A SOLO PILOT WOULD HAVE TO CLIMB INTO BACK SEAT	 TO HAVE ENOUGH FORCE TO BREAK THE JAMMED UP POSITION.				1	L	7	1 	3O				3A15 					 
1995082500229	19950825	00229	EU 	1995	8	25	95ZZZX4185 	1	19950728	G	2752	Z00N6075627220	MOTOR 		8375 	SOCATA	TB9 	TB9 	8680694	EU 										FLAP ACTUATOR	BURNED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	507PC	1298 			465	1466				INSPECTION OF MOTOR REVEALED INTERNAL WINDINGS FAILED DUE TO OVERHEATING OF MOTOR UNDER NORMAL FLYING CONDITIONS.						1	L	7	1 	3O			NT	AS1EU 					 
1995082500230	19950825	00230	EA 	1995	8	25	95ZZZX4186 	2	19950720	G	7414	10400006	IDENT PLATE 		D4LN3000 	MOONEY	M20 	M20J 	5870219	SW 	LYC 	O360 	IO360A3B6 	41514	EA 					MAGNETO	DAMAGED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	195ER		1348 		G259001G	243256				ALUMINUM FOIL INDENTIFICATION PLATE WAS TORN WHEN MAGNETO WAS RECEIVED FOR REPAIR. CORRECTIVE ACTION WAS TO INSTALL A N	EW IDENTIFICATION PLATE WITH CORRECT MAGNETO IDENTIFICATION DATA. IT IS EXPECTED THE NEW IDENTIFICATION PLATE WILL EXPE	RIENCE THE SAME CONDITIONS THAT LED TO THE DESTRUCTION OF THE PREVIOUSLY INSTALLED IDENTIFICATION PLATE. SUBMITTER RECO	MMENDED A METAL DATA PLATE BE PERMANENTLY ATTACHED TO THE MAGNETO.			1	L	7	1 	3O	3	O		2A3 	1E10				 
1995082500231	19950825	00231	EA 	1995	8	25	95ZZZX4187 	2	19950517	G	8530		GASKET 			CESSNA	172 	172 	2072402	CE 	LYC 	O320 	O320E2D 	41508	EA 					INTAKE	LEAK 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	20024	260 				17260940	RL4349327A			MANITA GASKET PMA PART FOR INTAKE GASKET FOR LYCOMING 0320. BLOWS OUT OF SIDE CAUSING INTAKE LEAK. FIRST ONE AT 150 HO	URS SMO, AND SAMPLE AT 260 HOURS.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995082500232	19950825	00232	SO 	1995	8	25	95ZZZX4188 	2	19950804	G	8520	632857	BEARING 			PIPER 	PA34 	PA34220T 	7103420	SO 	CONT 	O360 	LTSIO360KB 	17025	SO 					REAR MAIN	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	83747	1174 				348133074	268263R			INSPECTION OF OIL FILTER ELEMENT DURING ROUTINE OIL CHANGE AND LARGE AMOUNT OF ALUMINUM SHAVINGS AND MINOR AMOUNT OF STE	EL (MAGNETIC) PARTICLES WERE FOUND. ENGINE WAS REMOVED FROM AIRCRAFT AND DISASSEMBLED. FOUND REAR INTERMEDIATE MAIN BE	ARING HAD BROKEN INTO ABOUT 6-8 PIECES, BUT WAS BEING HELD IN PLACE BY CASE WEB AND BEARING JOURNAL. THE BEARING PIECES	 HAD SHIFTED ENOUGH TO SPIN IN WEB AND PRODUCE THE SHAVINGS OF ALUMINUM FOUND IN THE FILTER. IT WAS NOTED DURING DISASS	EMBLY THAT TORQUE ON THROUGH-BOLT NUTS AT THIS WEB SEEMED LOW. ENGINE WAS OVERHAULED WITH BOTH CASE AND CRANKSHAFT BEIN	G RETURNED TO SERVICE AFTER REPAIR.	1	L	7	2 	3O	3	O		A7SO 	E9CE				 
1995082500233	19950825	00233	GL 	1995	8	25	95ZZZX4189 	3	19950725	G	6114	C4716C98	HUB 													MCAULY	2A34C	D2A34C98 	GL 	NR 1 SOCKET	CRACKED 	B			ME4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19								751722		PROPELLER WAS RECEIVED FOR OVERHAUL. AFTER DISASSEMBLY, THE BEARINGS, BALLS, PISTON, AND FERRULES CONDEMNED DUE TO CORR	OSION. HUB WAS STRIPED AND CLEANED FOR INSPECTION. HUB WAS DISCOVERED CRACKED IN NR 1 BLADE SOCKET, 7 TO 5 O'CLOCK POS	ITION, ABOUT 2 INCHES LONG. CRACK DISCOVERED BY 10X POWER MISCROSCOPE. NO OTHER INFORMATION AVAILABLE DUE TO NO LOG BO	OK. PROPELLER PARTS WERE RETURNED TO CUSTOMER. AVIATION PROPELLER INC. WORK ORDER NR 27861.													5	C	P3EA	 
1995082500234	19950825	00234	GL 	1995	8	25	95ZZZX4190 	3	19950412	G	6114	D5892C87	HUB 			CESSNA	401 	401B 	207590E	CE 						MCAULY	3AF32C	3AF32C87 	GL 	NR 2 SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								733155		UPON INSPECTION, HUB FOUND CRACKED IN BLADE SOCKET NR 2. HUB HAS BEEN SCRAPPED.						1	L	7	2 	3O				A7CE 		5	C	P22EA	 
1995082500236	19950825	00236	GL 	1995	8	25	95ZZZX4192 	3	19950417	G	6114	C4716C98	HUB 													MCAULY	2A34C	D2A34C98 	GL 	NR 2 SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15					728572			728572		UPON INSPECTION, HUB FOUND CRACKED IN BLADE SOCKET NR 2. HUB HAS BEEN SCRAPPED.																5	C	P3EA	 
1995082500237	19950825	00237	GL 	1995	8	25	95ZZZX4193 	3	19950530	G	6114	C6447C23	HUB 													MCAULY	2A36C	2A36C23 	GL 	NR 2 SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								767506		UPON INSPECTION, HUB FOUND CRACKED IN BLADE SOCKET NR 2. HUB HAS BEEN SCRAPPED.																5	C	P880	 
1995082500238	19950825	00238	GL 	1995	8	25	95ZZZX4194 	3	19950210	G	6114	D6602C76	HUB 													MCAULY	3A32C	3A32C76 	GL 	NR 3 SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								778438		UPON INSPECTION, HUB FOUND CRACKED IN NR 3 BLADE SOCKET. HUB HAS BEEN SCRAPPED.																5	C	P21EA	 
1995082500239	19950825	00239	GL 	1995	8	25	95ZZZX4195 	3	19950210	G	6111	C84686R	BLADE 													HARTZL	HCJ3Y	PHCJ3YF2 	GL 	PROPELLER	TIP DEPARTED 	B			ME4D	O				OTHER 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			SO	15					B74077			ED7		NINE INCHES OF TIP OF BLADE CAME OFF IN-FLIGHT. BLADE HAD BEEN SENT TO HARTZELL PROPELLER, INC., FOR EVALUATION.																5	C	P36EA	 
1995082500240	19950825	00240	GL 	1995	8	25	95ZZZX4196 	3	19950405	G	6114	D6100C71	HUB 													MCAULY	2AF34C	D2AF34C71 	GL 	NR 2 SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								691189		DURING INSPECTION, HUB FOUND CRACKED IN BLADE SOCKET NR 2. HUB HAS BEEN SCRAPPED.																5	C	P5EA	 
1995082500242	19950825	00242		1995	8	25	95ZZZX4198 	4	19950322	G	6122	210314	FLYWEIGHT 	WOODWARD 	D210439 															GOVERNOR	FAILED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15					995792MPT					UPON INSPECTION, FOUND FLYWEIGHT HAD DISINTEGRATED INSIDE GOVERNOR, THEREBY CONDEMNING GOVERNOR. GOVERNOR HAS BEEN SCRA	PPED.																		 
1995082500243	19950825	00243	GL 	1995	8	25	95ZZZX4199 	3	19950201	G	6114	D7015C87	HUB 													MCAULY	2A34C	2A34C203 	GL 	NR 2 SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								798423		HUB FOUND CRACKED IN THREADS OF BLADE SOCKET NR 2. HUB HAS BEEN SCRAPPED.																5	C	P3EA	 
1995082500244	19950825	00244	CE 	1995	8	25	95ZZZX4200 	1	19950802	G	7922	75944	VALVE 			CESSNA	172 	172M 	2072418	CE 										THERMO BYPASS	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	91712				27716	17261508				INSPECTION OF THERMOSTATIC VALVE ON 5 ENGINES FOUND 3 NOT SERVICEABLE.						1	H	7	1 	3O			NT	3A12 					 
1995082500245	19950825	00245	NM 	1995	8	25	95ZZZX4201 	1	19950609	G	2720	2611008	HORN 			UNIVAR	108 	1082 	9230406	NM 										VERTICAL ASSY	NOTCHED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	9653K					1082653				INSPECTION OF CONTROL HORN FOUND IT 'NOTCHED'. HARD RT RUDDER APPLICATION REPEATEDLY HIT VERTICAL ASSEMBLY CAUSING IMPA	CT DAMAGE. SOME ONE FAILED TO 'FIX' DAMAGE. NOTCH CAUSED INTERFERENCE OF CONTROL MOVEMENT. OWNER ADVISED TO GROUND AI	RCRAFT UNTIL REPAIRED. NOTE: PART PAINTED, SO DAMAGE NOT SHOWN UNTIL CONTROL SCRAPED.				1	H	7	1 	3O				A767 					 
1995082500246	19950825	00246	CE 	1995	8	25	95ZZZX4202 	1	19950810	G	2750	0860207135	CONTROL CABLE 			CESSNA	310 	310R 	2074245	CE 										FLAP	BROKEN 	D				L				ABORTED APPROACH 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			EA	05	41159					310R0727				PILOT SELECTED APPROACH TO FULL FLAP SETTING ON FINAL TO LAND. AIRCRAFT ROLLED HARD TO RIGHT. BROUGHT FLAPS UP AND WEN	T AROUND. LANDED WITHOUT FLAPS. MAINTENANCE FOUND FLAP DOWN CABLE BROKEN AT PULLEY UNDER CABIN FLOOR. REPLACED CABLE 	AND RIGGED FLAPS. AIRCRAFT TT, 9,200 HOURS.				1	L	7	2 	3O			 	3A10 					 
1995082500247	19950825	00247	GL 	1995	8	25	95ZZZX4203 	3	19950628	G	6114	D5892C93	HUB 			CESSNA	402 	402C 	207590R	CE 						MCAULY	3AF32C	3AF32C93 	GL 	NR 2 SOCKET	CRACKED 	B			ME4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19								789050		PROPELLER RECEIVED FOR 5-YEAR OVERHAUL. AFTER HUB INSPECTION, HUB DISCOVERED CRACKED IN NR 2 BLADE SOCKET, BETWEEN 8 TO	 9 O'CLOCK POSITIONS, 3 THREADS IN, APPROXIMATELY 1 INCH LONG. THE CRACK WAS DISCOVERED USING A 10X POWERED MICROSCOPE.					1	L	7	2 	3O				A7CE 		5	C	P22EA	 
1995082500248	19950825	00248	CE 	1995	8	25	95ZZZX4204 	1	19950717	G	2435	23079004	GENERATOR 			CESSNA	441 	441 	2076020	CE 										STARTER/GEN	SEIZED 	B			FE6R	E	F	A		ENGINE SHUTDOWN 	ACTIVATE FIRE EXT. 	UNSCHED LANDING 		J			WARNING INDICATION 			CR	CRUISE 	1			NM	07	665TM		232 		1226	4410215				FLIGHT CREW FIRST NOTED NOISE IN HEADSETS FOLLOWED BY RIGHT ENGINE SURGE/RPM DROP/FIRE WARNING AND HIGH I.T.T. INDICATIO	N. RIGHT ENGINE WAS FEATHERED, FIRE BOTTLE DISCHARGED AND AN UNEVENTFUL LANDING ACCOMPLISHED. MAINTENANCE FOUND RIGHT 	ENGINE STARTER/GENERATOR COMPLETELY SHEARED FROM ENGINE BY FAILURE OF STARTER/GENERATOR ADAPTER, PN 23065-504. MAINTENA	NCE SUSPECTS STARTER/GENERATOR FAILED INTERNALLY AND SEIZED. STARTER/GENERATOR DRIVE SHAFT FAILED TO SHEAR CAUSING ADAP	TER CASTING TO FAIL. FIRE WARNING WAS FROM OVERHEATED GENERATOR PRIOR TO COMPLETE FAILURE.		1	L	7	2 	3T			RT	A28CE 					 
1995082500249	19950825	00249	GL 	1995	8	25	95ZZZX4205 	3	19950711	G	6114		PROPELLER 			CESSNA	210 	T210L 	2073449	CE 						MCAULY	3A32C	D3A32C88 	GL 	HUB	FAILED 	B			FG6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	1668X					21060703		750795		PILOT COMPLAINED PROPELLER WAS SLUGGISH FOR PAST YEAR. FINALLY, PROPELLER WOULD NOT RETURN TO LOW PTICH AND RUN-UP. DI	SASSEMBLY REVEALED WATER IN HUB, ACTUATING PINS SEVERELY CORRODED AND BINDING IN LINKS. BLADE RACES SEVERELY RUSTED. U	PON INSPECTION, HUB AND MOST INTERNAL PARTS REJECT. THIS PROPELLER HAD SEVERAL YEARS SINCE LAST OVERHAUL.				1	H	7	1 	3O				3A21 		5	C	P21EA	 
1995082500250	19950825	00250	SO 	1995	8	25	95ZZZX4206 	1	19950727	G	5311	6269504	FRAME 			PIPER 	PA28 	PA28161 	7102803	SO 										SPAR CARRY-THRU	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	30119	3768 				287916078				DURING A PRE-SALE INSPECTION WHILE INSPECTING THE FUSELAGE REAR SPAR ATTACH FITTINGS FOR CORROSION, DISCOVERED THE LT PO	RTION OF FRAME CHANNEL INBOARD AND BELOW WING REAR ATTACH FITTING, WAS BUCKLED AND CRACKED WHICH APPEARS TO HAVE BEEN TH	E RESULT OF A COMPRESSION LOAD. REVIEW OF AIRCRAFT RECORDS INDICATED A PREVIOUS REPAIR TO THE LT WING TIP AND OUTBOARD 	LEADING EDGE. PRESENT DAMAGE COULD HAVE BEEN EXISTING HIDDEN DAMAGE AT THAT TIME.			1	L	7	1 	3O				2A13 					 
1995082500251	19950825	00251	CE 	1995	8	25	95ZZZX4207 	1	19950622	G	3260	MS25125E3	SWITCH 			BEECH 	33 	F33A 	1151425	CE 										MLG UP	SEIZED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8240T	5212 			8807	CE1542				LANDING GEAR POSITION SWITCH FROZEN IN THE 'UP' POSITION DURING FLIGHT, MANUAL GEAR EXTENSION REQUIRED TO LOWER GEAR.						1	L	7	1 	3O				3A15 					 
1995082500252	19950825	00252		1995	8	25	95ZZZX4208 	4	19950808	G	3452	0900025030	TRANSPONDER 		TRT2500 	PIPER 	PA60 	PA60601P 	7106012	NM 										COCKPIT	FAILED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	3640D	1931 			1931	61P080986341				UNIT LOCK UP, WILL NOT TRANSFER MODE 'A' CODES FROM STANDBY TO ACTIVE WINDOW. THIRD UNIT IN AIRCRAFT SINCE ORIGINAL PUR	CHASE IN APRIL, 1995. FIRST UNIT FAILED COMPLETELY OUT OF BOX. SECOND UNIT WORKED FOR 6 HOURS, THEN WOULD NOT REPLY. T	HIS UNIT WORKED FOR FIRST THREE FLIGHTS, THEN FAILED INTERMITTENTLY.				1	M	7	2 	3O			RT	A17WE 					 
1995082500253	19950825	00253	CE 	1995	8	25	95ZZZX4209 	1	19950711	G	2730	053200135	ADAPTER 		052300173 	CESSNA	172 	172L 	2072432	CE 										ELEV TORQ TUBE	LOOSE RIVETS 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7112Q	5901 				17260412				LOOSE/WORKING RIVETS WERE FOUND AT AN ANNUAL INSPECTION ON THE LEFT ELEVATOR TORQUE TUBE ADAPTER (6 AN-4 RIVETS). THE 	REMOVED RIVETS WERE CLINCHED AND INCOMPLETELY BUCKED (UPSET HEADS NOT OF PROPER DIMENSION). THE RIVETS WERE REPLACED AN	D AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3O			NT	3A12 					 
1995082500254	19950825	00254	CE 	1995	8	25	95ZZZX4210 	1	19950725	G	3246	40172	WHEEL ASSY 	PARKERHANFIN		BEECH 	90 	F90 	1152909	CE 										MLG	WRONG TIE BOLT 	B			OS52	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	88TW					LA0029				WHILE PERFORMING TIRE REPLACEMENT, NOTICED THE WHEEL TIE BOLTS AND NUTS WERE INCORRECT STANDARD 'AN' STEEL BOLTS - AN6-3	1 BOLTS, AN960-6 WASHERS, AND MS21042-6 NUTS AND AN363-624 NUTS. INSTALLED CORRECT HARDWARE IAW CLEVELAND WHEEL AND BRA	KE INSTALLATION MANUAL. BOLT, PN 103-32300 OR MS 21250-0642. WASHER, PN 085-13100 OR MS20002C6. ONE NUT, PN 094-91500	 OR MS21045.65. NOTE: THIS WAS FOUND ON ALL 4 MAIN WHEEL ASSEMBLIES.			1	L	7	2 	4T				A31CE 					 
1995082500338	19950825	00338	EU 	1995	8	25	95ZZZX4211 	1	19950523	G	6410	11731742	BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	PAINT PEEL 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117VU	18 			998	7211				BLADE PAINT PEELING (ONLY 17.6 HOURS SINCE LAST PAINT).						1	G	7	2 	3U				H13EU 					 
1995082500339	19950825	00339	EU 	1995	8	25	95ZZZX4212 	1	19950523	G	6410	11731742	BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	PAINT PEEL 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117VU	18 			1024	7211				BLADE PAINT PEELING (ONLY 17.6 HOURS SINCE LAST PAINT).						1	G	7	2 	3U				H13EU 					 
1995082500340	19950825	00340		1995	8	25	95ZZZX4213 	4	19950619	G	3120	JB15307	CLOCK 			BOLKMS	117 	BK117A1 	5626010	EU 										COCKPIT	INOPERATIVE 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	117LF				623585	7013				CLOCK INOPERATIVE. UNIT WAS UNSERVICEABLE WHEN RECEIVED. ZERO HOURS SINCE OVERHAULED.						1	G	7	2 	3U				H13EU 					 
1995082500341	19950825	00341		1995	8	25	95ZZZX4214 	4	19950421	G	2562	ELT1104	ELT 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	213AE	645 			52822	7219				ELT PANEL LIGHT FLICKERS DURING FLIGHT AND WILL NOT TURN OFF WITH SWITCH.						1	G	7	2 	3U				H13EU 					 
1995082500342	19950825	00342		1995	8	25	95ZZZX4215 	4	19950618	G	3453	4530103	LORAN 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	224LF				29255	45199				LORAN INSTALLED AND WOULD NOT COME ON LINE. PREVIOUS REPAIR UNIT WOULD NOT POWER UP.						1	G	7	1 	3U				H2SW 					 
1995082500343	19950825	00343	NE 	1995	8	25	95ZZZX4216 	2	19950602	G	7321	0164348670	FUEL CONTROL 			BOLKMS	117 	BK117C1 		EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENGINE	MALFUNCTION 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	556 			C558	7505				ENGINE STAGNATED START ON FIRST START OF THE DAY. REMOVED AND REPLACED FUEL CONTROL.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995082500344	19950825	00344	EU 	1995	8	25	95ZZZX4217 	1	19950620	G	5530	11730650	FIN 			BOLKMS	117 	BK117A4 	5626017	EU 										VERTICAL STAB	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	313LF	34 			5013	7138				FIN CRACKED SAME PLACE WHERE FIN WAS REPAIRED BY A.E.C. ON OUTSIDE FACE OF END PLATE.						1	G	7	2 	3U				H13EU 					 
1995082500345	19950825	00345	EU 	1995	8	25	95ZZZX4218 	1	19950602	G	2140	Z00016	VALVE 			BOLKMS	117 	BK117C1 		EU 										HEAT SYSTEM	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	556 			5926B140	7505				VALVE WILL NOT OPEN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995082500346	19950825	00346	EU 	1995	8	25	95ZZZX4219 	1	19950602	G	6730	7012409901	ACTUATOR 			BOLKMS	117 	BK117C1 		EU 										DUPLEX PITCH	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC				89050116	7505				DUPLEX PITCH ACTUATOR CAUSING API FAILURE.						1	G	7	2 	3U				H13EU 					 
1995082500347	19950825	00347	EU 	1995	8	25	95ZZZX4220 	1	19950612	G	6240	117902131	INDICATOR 			BOLKMS	117 	BK117C1 		EU 										TRIPLE TACH	READS LOW 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	578 				7505				TRIPLE TACHOMETER DEFECTIVE. ROTOR RPM READS LOW. REMOVED AND REPLACED INDICATOR.						1	G	7	2 	3U				H13EU 					 
1995082500348	19950825	00348	EU 	1995	8	25	95ZZZX4221 	1	19950608	G	7714	1179405303	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	460H	23 			282	7142				ENGINE NEEDLES WOULD NOT MATCH UP. PREVIOUS REPAIR WAS N2 NEEDLE ERRATIC. TWENTY DAYS LATER AND ONLY 22.9 HOURS SINCE 	REPAIR.					1	G	7	2 	3U				H13EU 					 
1995082500349	19950825	00349		1995	8	25	95ZZZX4222 	4	19950528	G	2350	AA95453	AUDIO PANEL 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	400SL	26 			3985	45235				AUDIO PANEL WILL NOT TRANSMIT AND HAS NO TONE.						1	G	7	1 	3U				H2SW 					 
1995082500350	19950825	00350		1995	8	25	95ZZZX4223 	4	19950526	G	3444	066106103	RADIO ALTIMETER 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	519EH	10 			13882	45429				RADIO ALTIMETER READS 1,000 FEET REGARDLESS OF ALTITUDE. ALSO, WILL NOT LOCK ON TO ANY ALTITUDE. ONLY LASTED 30 DAYS A	ND 9.6 HOURS. STILL DEFECTIVE.					1	G	7	1 	3U				H2SW 					 
1995082500351	19950825	00351		1995	8	25	95ZZZX4224 	4	19950608	G	3444	066106103	RADIO ALTIMETER 		DRAA10A 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	519EH	27 			14602	45429				RADIO ALTIMETER READS 75 TO 125 FEET HIGH. ALSO, WHEN DESCENDING FROM HIGH ALTITUDE.						1	G	7	1 	3U				H2SW 					 
1995082500352	19950825	00352	SW 	1995	8	25	95ZZZX4225 	1	19950606	G	7110	A23373	STRUT ASSY 			BELL 	222 	222U 	1182140	SW 										COWL	MISINSTALLED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	6992					47521				END OF STRUT NOT INSTALLED CORRECTLY. CAUSES STRUT TO BIND IN COWLING. END NEEDS TO BE ROTATED IN THE DIRECTION OF THE	 ARROW PRINTED ON THE TAPES. REMOVED AND REPLACED.					1	G	7	2 	3U				H9SW 					 
1995082500353	19950825	00353	SW 	1995	8	25	95ZZZX4226 	1	19950615	G	6320	206040156001	SEAL 			BELL 	206 	206L4 	1182110	SW 										M/R XMSN	LEAKING 	B			TI1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	05	706SD	550 				52056				REPLACED MAGNETIC INPUT SEAL ON MAIN ROTOR TRANSMISSION WITH NEW SEAL DUE TO EXCESSIVE OIL LEAKAGE FROM SEAL. REMOVED A	ND REPLACED MAGNETIC SEAL.					1	G	7	1 	3U			NC	H2SW 					 
1995082500354	19950825	00354		1995	8	25	95ZZZX4227 	4	19950526	G	2312	40001278500	TRANSCEIVER 			BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	725RE	22 			340	51007				TRANSCEIVER SQUEECH ON CONTINUOUSLY.						1	G	7	1 	3U				H2SW 					 
1995082500355	19950825	00355	SW 	1995	8	25	95ZZZX4228 	1	19950615	G	7810	206064300005	STACK 			BELL 	206 	206L4 	1182110	SW 										EXHAUST	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	706SD	994 				52056				EXHAUST STACK FOUND CRACKED. REMOVED AND REPLACED.						1	G	7	1 	3U			NC	H2SW 					 
1995082500356	19950825	00356	EU 	1995	8	25	95ZZZX4229 	1	19950515	G	6720	11731822	PITCH LINK 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	BEARING WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	950MB	141 			0044	7061				BEARING WORN BEYOND LIMITS ON PITCH LINK. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995082500357	19950825	00357	EU 	1995	8	25	95ZZZX4230 	1	19950515	G	6720	11731822	PITCH LINK 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	BEARING WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	950MB	141 			0054	7061				BEARING WORN BEYOND LIMITS ON PITCH LINK. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995082500358	19950825	00358	SW 	1995	8	25	95ZZZX4231 	1	19950519	G	7931	IPT20RT11000250G	TRANSDUCER 			BELL 	222 	222 	1182122	SW 										OIL PRESSURE	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911MK	28 			46486255	47515				AS TRANSDUCERS WARM UP, PRESSURE DROPS OFF. WILL STAY AROUND 50 PSI.						1	G	7	2 	3U				H9SW 					 
1995082500359	19950825	00359	SW 	1995	8	25	95ZZZX4232 	1	19950611	G	3340	7028501	LIGHT 			BELL 	222 	222 	1182122	SW 										STROBE	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911MK	17 			R28MS00002	47515				INOPERATIVE STOBE LIGHT.						1	G	7	2 	3U				H9SW 					 
1995082500571	19950825	00571	GL 	1995	8	25	95ZZZX4261 	3	19950118	G	6114	D4326C211	HUB 													MCAULY	2D34C	B2D34C211 	GL 	PROPELLER	CORRODED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								767744		UPON INSPECTION, EXTERIOR OF HUB WAS FOUND CORRODED. HUB HAS BEEN SCRAPPED.																5	C	P7EA	 
1995082500572	19950825	00572	SO 	1995	8	25	95ZZZX4262 	2	19950518	G	8520		CAMSHAFT 			CESSNA	207 	207 	2073602	CE 	CONT 	O520 	IO520F 	17032	SO 					CYL 3-4 LOBE	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	1704U	486 			472013	20700304	286372R			FAILURE OF CAMSHAFT AT NR 3 AND NR 4 INTAKE LOBE. DESTROYED LIFTER BODIES, METAL IN ENGINE, ETC. TIME SINCE OVERHAUL 4	86.1 HOURS.					1	H	7	1 	3O	3	O		A16CE 	E5CE				 
1995082500573	19950825	00573	SO 	1995	8	25	95ZZZX4263 	2	19950517	G	8530		RING 			CESSNA	207 	207 	2073602	CE 	CONT 	O520 	IO520F 	17032	SO 					NR 2 CYLINDER	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	707FY	598 				20700063	286190R			OIL ANALYSIS SHOWING ALUMINUM HIGH. THEN IRON, NICKEL, CHROME. COMPRESSION GOOD, UNTIL TIME ON ENGINE OVER 600 HOURS A	ND COMPRESSION DROPPED TO 60/80 ON NR 2 CYLINDER. PULLED CYLINDER, FOUND BROKEN RING TOP COMPRESSION.					1	H	7	1 	3O	3	O		A16CE 	E5CE				 
1995082500574	19950825	00574	EA 	1995	8	25	95ZZZX4264 	2	19950627	G	8530	19353REVC	ROCKER ARM 		LW12416 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					OIL PASSAGE	OBSTRUCTED 	B			NX42	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	15	137ER	2259 				1527	L1760539A			WHILE CLEANING THE ROCKER ARM, SOLVENT FLOW THROUGH THE OIL PASSAGE WAS FOUND TO BE RESTRICTED. INSPECTION REVEALED A B	ROKEN DRILL BIT TIP TO BE THE OBSTRUCTION IN THE OIL PASSAGEWAY. WHEN THE DRILL BIT TIP WAS REMOVED, NORMAL FLUID FLOW 	WAS OBSERVED.				1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995082500575	19950825	00575	EA 	1995	8	25	95ZZZX4265 	2	19950606	G	7322	30766	FLOAT 		105217 	PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					CARBURETOR	LEAKING 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	171ER		13 		784	2841209				CARBURETOR WAS REMOVED FROM ENGINE BECAUSE OF REPORTED ROUGH RUNNING AND ENGINE SHUT DOWN WHEN THROTTLE MOVED TO IDLE. W	HEN CARBURETOR WAS DISASSEMBLED, FLOAT WAS FOUND FULL OF FUEL WHICH RESULTED IN EXCESSIVELY RICH CONDITION.					1	L	7	1 	3O	3	O		2A13 	E274				 
1995082500576	19950825	00576	EA 	1995	8	25	95ZZZX4266 	2	19950627	G	8530	SL74230	GUIDE 			SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					EXHAUST VALVE	CRACKED 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	138ER		971 			1528				DURING CYLINDER REPAIR, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED AT BOTH THE TOP AND BOTTOM PORTIONS OF THE GUIDE. THE	 CRACKS WERE NOT CONNECTED.					1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995082500577	19950825	00577	EA 	1995	8	25	95ZZZX4267 	2	19950627	G	8530	74230	GUIDE 			SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					CYLINDER EXHAUST	BROKEN 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	177ER		1376 			1353				DURING CYLINDER REPAIR, A RECTANGULAR SECTION OF THE EXHAUST VALVE GUIDE THAT MEASURED APPROXIMATELY .3125 INCH X .25 IN	CH WAS FOUND MISSING FROM THE LOWER PORTION OF THE GUIDE.					1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995082500578	19950825	00578	EA 	1995	8	25	95ZZZX4268 	2	19950627	G	8530	SL74230	GUIDE 		LW12416 	SOCATA	TB9 	TB9 	8680694	EU 	LYC 	O320 	O320D2A 	41508	EA 					CYLINDER EXHAUST	BROKEN 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	245ER		722 			1350				DURING CYLINDER REPAIR, A HALF-MOON SHAPED SECTION OF THE EXHAUST VALVE GUIDE THAT MEASURED APPROXIMATELY .3125 INCH X .	25 INCH WAS FOUND MISSING FROM THE LOWER PORTION OF THE GUIDE.					1	L	7	1 	3O	3	O	NT	AS1EU 	E274				 
1995082500579	19950825	00579	EA 	1995	8	25	95ZZZX4269 	2	19950606	G	7414	ES10382585	CONTACT ASSY 		D4LN3000 	MOONEY	M20 	M20J 	5870219	SW 	LYC 	O360 	IO360A3B6 	41514	EA 					MAGNETO	WORN 	B			NX42	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	193ER	997 	497 		B208905G	243243				WHEN MAGNETO WAS UNDERGOING PRELIMINARY INSPECTION, THE CONTACT ASSEMBLY WAS FOUND PITTED AND THE CAM FOLLOWER WAS EXCES	SIVELY WORN. SOME CAM FOLLOWER MATERIAL HAD TRANSFERRED TO THE OUTER FELT OF THE CONTACT ASSEMBLY. A THIN DARK COATING	 WAS FOUND ON THE MAGNETO CAM. CAUSE IS SUSPECTED TO BE CAM FOLLOWER WEAR. CAM FOLLOWER WEAR RESULTS IN DECREASING CON	TACT CLEARANCE AND MAY LEAD TO MAGNETO FAILURE.			1	L	7	1 	3O	3	O		2A3 	1E10				 
1995082500580	19950825	00580	CE 	1995	8	25	95ZZZX4270 	1	19950725	G	3252	22430281	CLAMP 			CESSNA	182 	TR182 	2072735	CE 										SHIMMY DAMPENER	LOOSE 	D	S			O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			WP	17	5379S	2606 				R18201561				PILOT REPORTED LANDING GEAR WOULD NOT LOCK UP, INTRANSIT LIGHT ON WHILE THE GEAR WAS RETRACTED. INVESTIGATION REVEALED 	THE SHIMMY DAMPENER CLAMP ON THE STRUT WAS LOOSE AND THE SHIMMY DAMPENER SHAFT CAUGHT THE SKIN ON THE TUNNEL COVER AND T	ORE A HOLE IN IT. THE COVER HAS A HOLE IN IT TO ALLOW THE SHIMMY DAMPENER TO GO THROUGH IT, BUT IF THE STRUT HAS BEEN T	URNED AND THE CLAMP IS LOOSE, IT CATCHES ON THE EDGE AND TEARS THE TUNNEL SKIN. SUBMITTER SUGGESTS DURING PRE-FLIGHT AN	D INSPECTIONS, MAKE SURE CLAMP IS TIGHT AND IN CORRECT POSITION.		1	H	7	1 	3O				3A13 					 
1995082500581	19950825	00581	SO 	1995	8	25	95ZZZX4271 	2	19950727	G	7322		GASKET 	FACET 	MA5SPA 	CESSNA	175 	175 	2072502	CE 	CONT 	O300 	GO300A 	17022	SO 					CARBURETOR	WRONG PART 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	15	6618E					56118	61919A			FOLLOWING ENGINE OVERHAUL, CARBURETOR WAS RE-INSTALLED TO OIL SUMP USING O-RING SUPPLIED IN KIT NR 627372-A1, PAGE 25 OF	 GO-300 PARTS MANUAL, FORM X30020. CARBURETOR INSTALLED PER G0-300 PARTS MANUAL, FIGURE 5, WHICH CALLS FOR AN O-RING. N	O O-RING GROOVE EXISTED. G0-300 OVERHAUL MANUAL, SECTION 12-11 CALLS OUT GASKET OR O-RING DEPENDING ON PART NUMBER. OI	L PUMP INSTALLED. INDUCTION SYSTEM SHOWN IN FIGURE 8.			1	H	7	1 	3O	3	O	NT	3A17 	E298				 
1995082500582	19950825	00582	EU 	1995	8	25	95ZZZX4272 	1	19950710	G	6410	355A12003104	BLADE 			AEROSP	AS355 	AS355F1 	8680810	EU 										TAIL ROTOR	DELAMINATED 	B			SZTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	911BB	2716 			2003	5099				TAIL ROTOR BLADE ASSY REMOVED FOR HAIL DAMAGE AND LEADING EDGE DELAMINATON. RETIREMENT TIME IS 4,000 HOURS.						1	G	7	2 	3U				H11EU 					 
1995082500583	19950825	00583	WP 	1995	8	25	95ZZZX4273 	1	19950809	G	6210	369D21100516A	BLADE 			HUGHES	369 	369D 	4470706	WP 										MAIN ROTOR	PAINT PEEL 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V	2908 			002222E390	4904870				BLADE HAD RETURNED FROM REWORK RECENTLY AND SINCE INSTALLATION 90.9 HOURS AGO, 3 SECTIONS ON THE BOTTOM OF THE BLADE HAV	E BEEN STRIPPED OF PAINT IN SHEETS ABOUT 75 SQUARE INCHES OF AREA EXPOSED AFFECTING THE LATERAL BALANCE OF THE ROTOR SYS	TEM.				1	G	7	1 	3U				H3WE 					 
1995082500584	19950825	00584	SW 	1995	8	25	95ZZZX4274 	1	19950628	G	2432	G641	BATTERY 	GILLBATT 		BELL 	206 	206B 	1181511	SW 										DC SYSTEM	MISMARKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5740A				G01589290	2986				DURING ANNUAL INSPECTION, MECHANIC NOTICED BATTERY MODEL NUMBER WAS LABELED G-241. THIS LABEL WAS INCORRECT FOR THE TYP	E OF BATTERY AND POST LOCATION. NOTIFIED GILL BATTERY WITH BATTERY SERIAL NUMBER AND VERIFIED THAT INSTALLED BATTERY WA	S AG-641 AND IT DID CONFORM TO THE STC FOR THIS INSTALLATION. GILL PROVIDED A NEW LABEL AND A LETTER. AIRCRAFT WAS RET	URNED TO SERVICE.			1	G	7	1 	3U				H2SW 					 
1995082500585	19950825	00585	NE 	1995	8	25	95ZZZX4275 	1	19950724	G	2913	9665009808101	PUMP 			SKRSKY	S76 	S76C 	8143008	NE 										NR 2 HYD	LEAKING 	C				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	25	399KK	323 			190375	760421				NR 2 HYDRAULUIC PUMP CASE DRAIN LEAKING. C/A - INSTALLED SERVICEABLE PUMP ASSEMBLY IAW SIKORSKY MM. BLED SYSTEM. RUN-	UP AND LEAK CHECK NORMAL. SERVICED HYDRAULIC SYSTEM. (THIRD PUMP CHANGE THIS POSITION DUE LEAKAGE). AIRCRAFT TT 387.7	 HOURS. LANDINGS, 977.				1	G	7	2 	3U			NC	H1NE 					 
1995082500587	19950825	00587	WP 	1995	8	25	95ZZZX4277 	2	19950805	G	7210	23037419	COVER ASSY 		6894171 	HUGHES	369 	369D 	4470706	WP 										GR BOX CHIP PLUG	INSERT LOOSE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4282X	11874	3121 		CAG21007	180253D				DURING 100 HOUR INSPECTION, THE LOWER CHIP PLUG WAS LOOSENED FOR REMOVAL WHEN IT WAS DISCOVERED THE INSERT BOSS WAS LOOS	E IN THE COVER ASSEMBLY. PART REPLACED AND SENT FOR REPAIR.					1	G	7	1 	3U				H3WE 					 
1995082500588	19950825	00588	WP 	1995	8	25	95ZZZX4278 	1	19950807	G	6710	369A7304	CONTROL BRACKET 			HUGHES	369 	369D 	4470706	WP 										FLT CONTROL	CAP BROKEN 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y	7678 			5	500716D				DURING 100-HOUR INSPECTION, THE BEARING CAP WAS FOUND CRACKED AT THE FORWARD BOLT EAR.						1	G	7	1 	3U				H3WE 					 
1995082500589	19950825	00589	GL 	1995	8	25	95ZZZX4279 	2	19950805	G	7323	23007505	GOVERNOR 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	ERRATIC 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4282X		424 		28419	180253D	CAE833827			GOVERNOR IS ERRATIC WITH ANY POWER CHANGE. UNIT REMOVED AND SENT IN FOR REPAIR ON ALLISON 250 REPORT NR A151615.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995082500591	19950825	00591	EU 	1995	8	25	95ZZZX4281 	1	19950801	G	3010	0372176437	PIPE 			BAG 	JETSTM	JETSTM3201 	1500217	EU 										DE-ICE	PIN HOLE 	B			UN9R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	3108	8723 				824				DURING MAIN CABIN BELOW FLOOR INSPECTION AT STR 345, WATER WAS FOUND DRIPPING FROM DE-ICE PIPE THAT SERVICES THE TAIL BO	OTS. INVESTIGATION REVEALED PIN HOLE IN LOW POINT OF PIPE. REMOVED AND REPLACED PIPE. REMOVED PIPE WAS CUT OPEN, FOUN	D PIPE WAS SEVERELY CORRODED INTERNALLY. SUSPECT CAUSE WAS THE WATER THAT WAS RETAINED IN THE LOW POSITION OF THIS PIPE	. NEED TO REPOSITION LINE SO THAT IT WILL NOT RETAIN WATER WHILE ON GROUND.			2	L	7	2 	4T			RT	A56EU 					 
1995082500593	19950825	00593	NE 	1995	8	25	95ZZZX4283 	3	19950620	G	6111	7861471	BLADE SHANK 	HAMSTD 	SFA13M10A1B 	AEROSP	ATR42 	ATR42320 	8680930	EU 						HAMSTD	14SF	14SF5 	NE 	SHANK BUTT	CRACKED 	B			H2SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	99838	14708	2094 		854873	259				THE SUBJECT BLADE WAS RECEIVED FOR A TORN DE-ICE BOOT. DURING DYE CHECK OF THE BLADE SHANK, TWO CRACKS WERE FOUND; ONE 	IN THE FILLET, AND ONE ON THE BUTT OUTSIDE DIAMETER. BOTH CRACKS WERE LOCATED ADJACENT TO THE COLLAR PARTING LINE ON TH	E FACE SIDE, AND WERE PARALLEL TO EACH OTHER. THE CRACKS WERE HAIR LINE IN WIDTH AND DEPTH AND WERE APPROXIMATELY 1.25 	INCHES IN LENGTH. THE BLADE IS BEING SCRAPPED FOR THIS CONDITION.			2	H	7	2 	4T			RT	A53EU 		6	C	P7NE	 
1995082500594	19950825	00594	CE 	1995	8	25	95ZZZX4284 	1	19950808	G	2131	3203353	VALVE 			LEAR 	60 	60LEAR 	5170707	CE 										CABIN FLOW	STUCK 	B			NVIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	205FX	1240 			034	005				PILOT REPORTED THE AIRPLANE WOULD NOT PRESSURIZE AFTER TAKEOFF, IN NORMAL OR MANUAL MODE. GROUND OPERATION CONFIRMED NO	 INFLOW OF AIR TO THE CABIN EXCEPT IN EMERGENCY PRESSURIZATION. REPLACED THE CABIN AIR FLOW CONTROL VALVE, SYSTEM TESTE	D NORMAL. (REF: LEARJET MM CHAPTER 21-30-00, PAGE 202, CHAPTER 21-40-01, PAGE 201.				2	L	7	2 	4F			RT	A10CE 					 
1995082500595	19950825	00595	CE 	1995	8	25	95ZZZX4285 	1	19950701	G	5350		FAIRING 			LEAR 	35 	35A 	5170602	CE 										RT WING	SCREWS DETACHED 	B	S		NVIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	210WL					210				DURING PRE-FLIGHT INSPECTION, THE PILOT DISCOVERED EXTENSIVE F.O.D. TO THE RIGHT ENGINE FAN AND NOISE SUPPRESSION BAND. 	 INVESTIGATION REVEALED 2 SCREWS ON THE WING LEADING EDGE FAIRING HAD BACKED OUT. THE PREVIOUS CREW DID NOT REPORT ANY 	SHIFT IN ENGINE PARAMETERS OR ANY UNUSUAL NOISE. SUBMITTER STATED THE SAME THING HAS OCCURRED ON A FOREIGN REGISTERED L	EARJET 24D. ACFT TT, 6,404.9 HOURS, LANDINGS, 5,279.			2	L	7	2 	4F				A10CE 					 
1995082500596	19950825	00596	CE 	1995	8	25	95ZZZX4286 	1	19950801	G	2150	1179100609	PIVOT BRACKET 			BEECH 	B300 	B300 	1159232	CE 										AC COMPRESSOR	BROKEN 	B		A	KI2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	65CR	498 				FL60				PIVOT BRACKET HOLDS AIR CONDITIONER COMPRESSOR TO ENGINE ACC SECTION. PART IS MADE OUT OF ALUMINUM. EARS KEEP BREAKING	 OFF. RECOMMEND REDESIGN. SUBMITTER STATED THIS IS THE FOURTH BRACKET TO BREAK, ALL IN EXACT SAME LOCATION. BRACKET 1	,069 HRS TT, FIRST ONE. SECOND, 414 HRS TT. THIRD, 519 HRS TT. FOURTH, 1497.9 HRS TT.				2	L	7	2 	4T			RT	A24CE 					 
1995082500597	19950825	00597	CE 	1995	8	25	95ZZZX4287 	1	19950711	G	2742	9914056	ACTUATOR 		497D1009 	CESSNA	650 	650 	2076802	CE 										PITCH TRIM	FAILED 	B			IW1R	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			EA	25	118CD				187	6500118				INTERMITTENT PITCH TRIM FAIL INDICATION. TIME IN SERVICE OF THIS REPAIRED PART - 16.8 HOURS. THIS IS THE FOURTH FAILUR	E OF THIS PART ON THIS AIRCRAFT.					2	L	7	2 	4F				A9NM 					 
1995082500598	19950825	00598	NE 	1995	8	25	95ZZZX4288 	2	19950801	G	7530	451077	SENSE LINE 			BOEING	727 	72722 	1384002	NM 	PWA 	JT8 	JT8D7B 	52053	NE 					NR 3 ENGINE	BROKEN 	D				O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			SW	99	400RG					19149	P648871			DURING CRUISE, NR 3 ENGINE'S FUEL FLOW AND EGT BEGAN TO CLIMB WITH LOWER RPM'S AT SAME THROTTLE SETTING AS NR 1 AND NR 2	 ENGINES. OK, PRESSURE GOOD, NO VIBRATION NOTED. REDUCED POWER TO IDLE FOR ABOUT 1.50 HOURS, INBOUND TO EWR. FOUND 13	TH STAGE AIR PRESSURE SENSE LINE BROKEN AT 13TH STAGE SADDLE DUCT. LINE BROKE AT FERRULE TO TUBE WELD JUNCTION, SUSPECT	 CAUSE - VIBRATION.			2	L	7	3 	4F	4	F		A3WE 	E2EA				 
1995082500599	19950825	00599	EA 	1995	8	25	95ZZZX4289 	1	19950801	G	2913	601751005	PUMP 			CNDAIR	CL601 	CL6013A 	8070802	EA 										LT ENG NR 1 HYD	LINE FAILED 	C				O				OTHER 				K			FLUID LOSS 			CL	CLIMB 	1			EA	25	399SW	3488 			MX449383	5009				ON CLIMB, LOSS OF NR 1 HYDRAULIC FLUID QUANTITY. C/A - FOUND PRESSURE LINE FROM NR 1 ENGINE HYDRAULIC PUMP FAILED. REP	LACED NR 1 ENGINE PUMP AND HYDRAULIC LINE. SERVICED SYSTEM, BLED SYSTEM, OPERATIONAL CHECK NORMAL.					2	L	7	2 	4F			RT	A21EA 					 
1995082500600	19950825	00600	CE 	1995	8	25	95ZZZX4290 	1	19950727	G	3260		SWITCH 			CESSNA	500 	S550 	2076607	CE 										LT MLG DOWNLOCK	WIRE BROKEN 	B			HAXR	O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			SW	11	693M					S5500021				LEFT MAIN GEAR NOT INDICATED AS DOWN AND LOCKED. UNEVENTFUL LANDING. FOUND BROKEN WIRE AT LEFT MAIN GEAR DOWNLOCK SWIT	CH.					1	L	7	2 	4F			RT	A22CE 					 
1995082500601	19950825	00601	CE 	1995	8	25	95ZZZX4291 	1	19950711	G	2612		LOOP 			LEAR 	60 	60LEAR 	5170707	CE 										BAG COMPARTMENT	NOT GROUNDED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	07	699SC					041				INSPECTION FOUND SOME BAGGAGE COMPARTMENT FIRE LOOPS THAT ARE NOT GROUNDED. THE LOOP ONLY WORKS WITH A GROUND-TO STRUCT	URE. ADVISED ENGINEERING. LEARJET DRAWING 6059005 WAS TO BE CHANGED. THE LOOPS SIMILAR ON PRATT AND WHITNEY ENGINES H	AVE A BRAIDED BOND TO ASSURE GROUND.				2	L	7	2 	4F			RT	A10CE 					 
1995082500602	19950825	00602	SO 	1995	8	25	95ZZZX4292 	1	19950713	G	2433	38B932C	CONVERTER 			GULSTM	G1159 	G1159A 	3970109	SO 										DC SYSTEM	MALFUNCTION 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	19	721FF				97	421				UNIT RECEIVED FROM REPAIR FACILITY WITH COOLING FAN ASSEMBLY AND FAN COVER LOOSE. ATTACHING HARDWARE ONLY STARTED IN NUT	PLATES. FASTENERS WERE TIGHTENED AND THE UNIT INSTALLED. UNIT TRIPS OFF-LINE DURING ENGINE ACCELERATION ON AN INTERMIT	TENT BASIS. SUBMITTER RECOMMENDS TESTING OF THE VOLTAGE REGULATOR AND FINAL INSPECTION PRIOR TO MAINTENANCE RELEASE.				2	L	7	2 	4F				A12EA 					 
1995082500603	19950825	00603	WP 	1995	8	25	95ZZZX4293 	2	19950712	G	7260	358206	BEARING 			LEAR 	35 	35A 	5170602	CE 	GARRTT	TFE731	TFE73122B 	01518	WP 					START SPUR GEAR	FAILED 	B			IY2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	600AW	7932 	808 		P961	149	P74483C			DURING ROUTINE 150-HOUR ENGINE INSPECTION, FOUND CHIP DETECTOR COVERED WITH FINE SLIVERS OF METAL. INSPECTION OF OIL FI	LTER REVEALED 4 TO 20 MG OF CARBON STEEL AND COPPER. THIS COMBINATION OF METALS IS THE MAKE-UP OF A 'LOW' QUALITY ENGIN	E BEARING. ACCESSORY GEARBOX WAS OPENED WHICH REVEALED THE FORWARD STARTER SPUR GEAR SHAFT BEARING HAD FAILED. POWERPL	ANT WAS RETURNED TO SERVICE FOLLOWING REPLACEMENT OF BEARING AND FLUSHING OF OIL TANK AND LINES.			2	L	7	2 	4F	4	F		A10CE 	E6WE				 
1995082500604	19950825	00604	CE 	1995	8	25	95ZZZX4294 	1	19950727	G	5320	54124814	DOUBLER ANGLE 			LEAR 	55 	55LEAR 	5170702	CE 										RUD MECH STOP	DAMAGED 	B	S	A	VJ1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	82JA	5474 				029				DURING A VISUAL INSPECTION FOR RUDDER REMOVAL AND REINSTALLATION STRENGTHENING DOUBLER ANGLE LOCATED BELOW THE RUDDER, M	ECHANICAL STOP WAS NOTED TO BE SEVERELY CRACKED. FAILURE OF MECHANICAL STOP COULD RESULT IN STOP BECOMING LODGED IN RUD	DER BELLCRANK OR OVER TRAVEL OF THE RUDDER. SUBMITTER RECOMMENDS VISUAL INSPECTION WITH FLASHLIGHT AND MIRROR AT NEXT O	PPORTUNITY.			2	L	7	2 	4F				A10CE 					 
1995082500605	19950825	00605	NE 	1995	8	25	95ZZZX4295 	3	19950615	G	6111		SNAP RING 			CESSNA	177 	177RG 	2073709	CE 						MCAULY	C3D36C	C3D36C41582 	NE 	BLADE SHANK	CORRODED 	H	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	7903V	89 				0914		912246		UPON INSPECTION, THE STEEL SNAP RING AT THE BASE OF THE BLADES WAS FOUND SEVERELY CORRODED. THIS CONDITION INCLUDED THE	 BLADES NEXT TO THE SNAP RINGS AS THE PAINT ON BLADES WAS LOOSE AND WHITE POWDER WAS FOUND UNDER THE PEELED PAINT. THIS	 PROP WAS NEW AND HAD BEEN IN SERVICE 80.7 HOURS. AIRCRAFT WAS ALWAYS KEPT IN HANGAR SINCE PROP INSTALLATION.				1	H	7	1 	3O				A20CE 		5	N	SA645NE	 
1995082500606	19950825	00606	SO 	1995	8	25	95ZZZX4296 	1	19950724	G	3213	6703704	STRUT 			PIPER 	PA34 	PA34200T 	7103406	SO 										LT MLG	CRACKED 	B	S		VG4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	951GP	3315 				348070052				LEFT MAIN STRUT WAS FOUND CRACKED ADJACENT TO THE BOLTS THAT HOLD THE BRAKE ANCHOR PLATE TO THE STRUT.						1	L	7	2 	3O				A7SO 					 
1995082500607	19950825	00607	SO 	1995	8	25	95ZZZX4297 	1	19950724	G	3213	6703704	STRUT 			PIPER 	PA34 	PA34200T 	7103406	SO 										RT MLG	CRACKED 	B			VG4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	951GP	3315 				348070052				RIGHT MAIN STRUT WAS FOUND CRACKED ADJACENT TO THE BOLTS THAT HOLD THE BRAKE ANCHOR PLATE TO THE STRUT.						1	L	7	2 	3O				A7SO 					 
1995082500608	19950825	00608		1995	8	25	95ZZZX4298 	4	19950720	G	2562	BP1040	BATTERY PACK 	MARTECH 	EB2BCD 	MOONEY	M20 	M20D 	5870210	SW 										ELT CASE	LEAKING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	1919Y				15517	214				DURING ANNUAL, FOUND CORROSION IN ELT CAUSED BY BATTERY LEAKING, SWELLING, AND CRACKING THE BATTERY ENCLOSURE. THIS IS 	SECOND CONSECUTIVE ANNUAL WITH SAME PROBLEM. MARTECH ENGINEER SAID HIGH CABIN TEMPS CAUSING PROBLEM AND ADVISED ELT'S B	E REMOVED FROM ACFT WHEN NOT IN USE AND BE STORED IN COOL TEMPS. CLEANED UP ELT AND INSTALLED ANOTHER NEW BATTERY PACK.				1	L	7	1 	3O				2A3 					 
1995082500609	19950825	00609	CE 	1995	8	25	95ZZZX4299 	1	19950804	G	3230	24130023	FITTING 			CESSNA	172 	172RG 	2072438	CE 										MLG STA 19.6	BOLTS LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	6612V	2065 				172RG0781				DURING 100-HOUR INSPECTION OF NOSE GEAR ACTUATOR, FOUND BOLTS LOOSE IN NOSE GEAR ACTUATOR FITTING. NON-COMPLIANCE OF SB	 SEB93-8 LED TO DEFECT. SUBMITTER RECOMMENDS A RECURRING AD BE ATTACHED TO SB UNTIL SERVICE KIT SK A2-142 INSTALLED.					1	H	7	1 	3O				3A17 					 
1995082500610	19950825	00610	SO 	1995	8	25	95ZZZX4300 	1	19950807	G	2510	5453405	LAP BELT 			PIPER 	PA31 	PA31325 	7103105	SO 										HARNESS	PART MISSING 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	407TJ					317512069				THE PLASTIC SLEEVE/COLLAR IS MISSING FROM THE LAP BELT LUG/PIN WHERE SHOULDER HARNESS CONNECTS TO BELT. WITH THIS MISSI	NG, POSITIVE ENGAGEMENT OF HARNESS TO BELT IS COMPROMISED.					1	L	7	2 	3O				A20SO 					 
1995082500611	19950825	00611	SO 	1995	8	25	95ZZZX4301 	1	19950807	G	2510	551390	SEAT BELT 			PIPER 	PA28 	PA28236 	7102815	SO 										HARNESS	PART MISSING 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	2897A					287911230				THE PLASTIC SLEEVE/COLLAR IS MISSING FROM THE LAP BELT LUG/PIN WHERE SHOULDER HARNESS CONNECTS TO BELT. WITH THIS MISSI	NG, POSITIVE ENGAGEMENT OF HARNESS TO BELT IS COMPROMISED.					1	L	7	1 	3O				2A13 					 
1995082500612	19950825	00612	CE 	1995	8	25	95ZZZX4302 	1	19950807	G	2510	S21996	SEAT BELT 			CESSNA	172 	172N 	2072434	CE 										HARNESS	PART MISSING 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	75742					17267919				THE PLASTIC SLEEVE/COLLAR IS MISSING FROM THE LAP BELT LUG/PIN WHERE SHOULDER HARNESS CONNECTS TO BELT. WITH THIS MISSI	NG, POSITIVE ENGAGEMENT OF HARNESS TO BELT IS COMPROMISED.					1	H	7	1 	3O			NT	3A12 					 
1995082500613	19950825	00613	SO 	1995	8	25	95ZZZX4303 	1	19950807	G	2510	551390	SEAT BELT 			PIPER 	PA34 	PA34220T 	7103420	SO 										HARNESS	PART MISSING 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	84643					348233033				THE PLASTIC SLEEVE/COLLAR IS MISSING FROM THE LAP BELT LUG/PIN WHERE SHOULDER HARNESS CONNECTS TO BELT. WITH THIS MISSI	NG, POSITIVE ENGAGEMENT OF HARNESS TO BELT IS COMPROMISED.					1	L	7	2 	3O				A7SO 					 
1995082500614	19950825	00614	SO 	1995	8	25	95ZZZX4304 	1	19950807	G	2510	5453405	SEAT BELT 			PIPER 	PA31 	PA31325 	7103105	SO 										HARNESS	PART MISSING 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	4503L					318012031				THE PLASTIC SLEEVE/COLLAR IS MISSING FROM THE LAP BELT LUG/PIN WHERE SHOULDER HARNESS CONNECTS TO BELT. WITH THIS MISSI	NG, POSITIVE ENGAGEMENT OF HARNESS TO BELT IS COMPROMISED.					1	L	7	2 	3O				A20SO 					 
1995082500615	19950825	00615	CE 	1995	8	25	95ZZZX4305 	1	19950802	G	7602	5038901223	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										MIX CONTROL	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	830Q	40 				TH368				INSTALLED NEW MIXTURE CONTROL CABLE PURCHASED FROM BEECHCRAFT ON 7-14-95. PART FAILED INTERNALLY NEAR ROD END. AFTER 3	9.8 HOURS OF SERVICE, NO OBVIOUS DEFECTS WERE NOTED THAT COULD LEAD TO THE PREMATURE FAILURE.					1	L	7	2 	3O			 	3A16 					 
1995082500616	19950825	00616	SO 	1995	8	25	95ZZZX4306 	2	19950721	G	8550	9696001111	LINE 			BEECH 	58 	58 	1152740	CE 	CONT 	O520 	IO520C 	17032	SO 					PROP GOVERNOR	FAILED 	B			EKGR	K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			WP	07	365C	3299 				TH346				PILOT REPORTED OIL LOSS FROM RIGHT ENGINE COMPARTMENT. INSPECTION REVEALED THE METAL LINE CONNECTED TO THE PROPELLER GO	VERNOR HAD SEPARATED JUST BELOW THE FLARE. A NEW LINE WAS INSTALLED. REASON FOR FAILURE IS UNKNOWN.					1	L	7	2 	3O	3	O		3A16 	E5CE				 
1995082500617	19950825	00617	NM 	1995	8	25	95ZZZX4307 	1	19950622	G	3230		CONTROL CABLE 			PROPJT	200 	200A 	0140304	NM 										WHEEL BAIL	MISINSTALLED 	B			FTUR	O				OTHER 				J	W		WARNING INDICATION 	INADEQUATE Q C 		NR	NOT REPORTED 	1			NE	05	492C					256				RIGHT MAIN GEAR FAILED TO EXTEND. INVESTIGATION REVEALED THE WHEEL BAIL CABLE WAS PREVIOUSLY REPLACED. THE CABLE WAS 2	 INCHES TOO SHORT AND THE WRONG SWAGED TERMINAL WAS INSTALLED ALLOWING THE CABLE TO BIND AT THE ATTACHMENT. THIS BINDIN	G, AND SHORTNESS, CAUSED THE CABLE TO PREVENT THE INBOARD RIGHT GEAR DOOR TO MOVE CLEAR OF THE LANDING GEAR WHEEL ASSEMB	LY UPON GEAR EXTENSION. SERVICE CHANGE 2003 PERTAINS TO THIS MECHANISM. NO RECORD WAS FOUND OF COMPLIANCE OF THIS SERV	ICE CHANGE.		1	L	7	1 	3O			 	3A18 					 
1995082500618	19950825	00618	CE 	1995	8	25	95ZZZX4308 	1	19950714	G	2730	51152151	FORK ASSY 			CESSNA	421 	421B 	2076014	CE 										ELEV ATTACH	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	70MC	4856 				421B0622				FOUND CRACK IN FORK END AT ELEVATOR ATTACH POINT. CRACK RADIATED FROM THREADS AND ALONG THE BOTTOM. THE CRACK WAS NOT 	VISABLE UNTIL ROD REMOVED FOR OTHER MAINTENANCE.					1	L	7	2 	3O				A7CE 					 
1995082500619	19950825	00619	SO 	1995	8	25	95ZZZX4309 	1	19950808	G	2701	7927600	CONTROL WHEEL 			PIPER 	PA28 	PA28140 	7102802	SO 										COCKPIT	BROKE 	D	P			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	27	8879E					287625163				CONTROL WHEEL BROKEN THROUGH CENTER. BREAK OCCURRED THROUGH CENTER OF PIN HOLE (1944 HRS).						1	L	7	1 	3O				2A13 					 
1995082500620	19950825	00620	EU 	1995	8	25	95ZZZX4310 	2	19950727	G	8530	935730	GEAR 			AMTR 	CH701 	CH701 	0564900	GL 	ROTAX 	582 	ROTAX582 	55555	EU 					ROTARY VALVE	TEETH SHEARED 	G				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			CE	03	701ZA	414 				73001	4016584			ROTARY VALVE GEAR OIL SUMP FASTENER BROKE AND SUMP FELL TO A LOWER LEVEL THAN THE CRANKSHAFT. LACK OF LUBRICATION FROM 	SUMP CAUSED BRASS ROTARY VALVE GEAR TO SHEAR OFF ITS TEETH. RESULT WAS THE ROTARY VALVE SLIPPED AND BECAME OUT OF TIME 	WITH ENGINE; THUS, ROUGHNESS AND POWER LOSS OCCURRED.				1	H	7	1 	3O	3	I	NT	EXPA1H71	EXPE3I				 
1995082500621	19950825	00621		1995	8	25	95ZZZX4311 	4	19950802	G	2562	1104	ELT 			BEECH 	MU300 	400BEECH 		CE 										TAIL CONE	CASE SPLIT 	B	S	A	OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	3038V	601 			53777	RK93				UPON SCHEDULED REMOVAL FOR INSPECTION, ELT/BATTERY CASE, S/N 53777, WAS FOUND SPLIT OPEN AND LEAKING. CASE WAS SPLIT I	NTO SEVERAL PIECES. AREA BETWEEN BATTERY PACK AND HEAD OF ELT APPEARED TO HAVE OVERHEATED. BATTERY IS MOUNTED UNDERNEA	TH AIR CONDITIONER CONDENSOR AND ABOVE ANTI-SKID CONTROL BOX. ALL ABOVE COMPONENTS ARE LOCATED BEHIND TAILCONE BAGGAGE 	COMPARTMENT. IT IS NOT KNOWN IF ELT FAILED ON ITS OWN OR IF EXCESSIVE EXTERNAL HEAT WAS A FACTOR. INSTALLED NEW ELT'S.	 ELT INSPECTION FREQUENCY BEING INCREASED.		2	H	7	2 	4F			RT	A16SW 					 
1995082500622	19950825	00622		1995	8	25	95ZZZX4312 	4	19950802	G	2562	1104	ELT 			BEECH 	MU300 	400BEECH 		CE 										TAIL CONE	CASE SPLIT 	B		A	OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	3196N	601 			53854	RK96				UPON SCHEDULED REMOVAL FOR INSPECTION, ELT/BATTERY CASE, S/N 53854, WAS FOUND SPLIT OPEN AND LEAKING. CASE WAS SPLIT IN	TO SEVERAL PIECES. AREA BETWEEN BATTERY PACK AND HEAD OF ELT APPEARED TO HAVE OVERHEATED. BATTERY IS MOUNTED UNDERNEAT	H AIR CONDITIONER CONDENSOR AND ABOVE ANTI-SKID CONTROL BOX. ALL ABOVE COMPONENTS ARE LOCATED BEHIND TAILCONE BAGGAGE C	OMPARTMENT. IT IS NOT KNOWN IF ELT FAILED ON ITS OWN OR IF EXCESSIVE EXTERNAL HEAT WAS A FACTOR. INSTALLED NEW ELT'S. 	 ELT INSPECTION FREQUENCY BEING INCREASED.		2	H	7	2 	4F			RT	A16SW 					 
1995090100058	19950901	00058	SO 	1995	9	1	95ZZZX4313 	1	19950615	G	3230	41983000	DOWNLOCK HOOK 			PIPER 	PA31 	PA31P 	7103120	SO 										LT MLG	BINDING 	D				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			EA	01	57BT					31P7400175				DURING ROUTINE FLT, LT MLG FAILED TO EXTEND PROPERLY. GREEN 'DOWN & LOCKED' LIGHT FAILED TO ILLUM & RED 'TRANSITION' LI	GHT REMAINED LIT. AFTER DETERMINING GRN LIGHT NOT AT FAULT & UNSUCCESSFUL ATTEMPTS TO EXTEND GEAR (MANUAL EXTENSION, G-	LOADING, FISH-TAILING), PILOT ELECTED TO LAND WITH GEAR DOWN, BUT WITH LT GEAR NOT LOCKED. AT TOUCHDOWN, GRN LIGHT ILLU	M & RED LIGHT WENT OUT. INSP OF GEAR ASSY REVEALED DNLK HOOK STIFF & UNABLE TO SPRING INTO LOCKED POSITION. REMOVAL & 	INSP OF ASSY REVEALED BUSHINGS VERY DRY. SUBMITTER SUGGESTS CONDITION COULD RESULT FROM WASHING ACFT. ALSO, DNLK HOOK 	HAD NOT BEEN LUBED SINCE ANNUAL, 11 MOS PRIOR. REC PILOTS CHK HOOK EACH PRE-FLT FOR SPRING ACTION & FREE MOVEMENT.	1	L	7	2 	3O				A8EA 					 
1995090100059	19950901	00059	CE 	1995	9	1	95ZZZX4314 	1	19950721	G	2842	200HM5W	RESISTOR 			CESSNA	150 	152 	2071835	CE 										FUEL QTY XMITTER	NOT REQUIRED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	01	757UR					15280018				MALFUNCTION OR DEFECT REPORT, FAA FORM 8010-4, WAS SUBMITTED TO FSDO WITH FOLLOWING STATEMENT: 'AFTER INSTALLING REPLAC	EMENT FUEL QUANTITY GAUGES AND TRANSMITTERS PER SK152-21A, THE TRANSMITTERS COULD NOT BE CALIBRATED, THE GAUGES READ FUL	L WITH TANKS LESS THAN HALF FULL.' THERE IS A RESISTOR, PN 20-OHM 5W, INSTALLED BY THE FACTORY, AT THE TRANSMITTER ON T	HIS SN AIRCRAFT. THIS RESISTOR MUST BE REMOVED FOR THE NEW SYSTEM TO OPERATE PROPERLY, BUT IS NOT CALLED OUT IN THE INS	TRUCTIONS PROVIDED WITH THE KIT. A CALL TO CESSNA'S TECHNICAL DEPARTMENT CONFIRMED THIS.		1	H	7	1 	3O			NT	3A19 					 
1995090100060	19950901	00060	CE 	1995	9	1	95ZZZX4315 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	94508	4215 				15285698				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100061	19950901	00061	CE 	1995	9	1	95ZZZX4316 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	94534	5105 				15285709				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100062	19950901	00062	CE 	1995	9	1	95ZZZX4317 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95563	6209 				15285926				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100063	19950901	00063	CE 	1995	9	1	95ZZZX4318 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95564	5804 				15285927				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100064	19950901	00064	CE 	1995	9	1	95ZZZX4319 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95565	5765 				15285928				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100065	19950901	00065	CE 	1995	9	1	95ZZZX4320 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95566	6172 				15285929				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100066	19950901	00066	CE 	1995	9	1	95ZZZX4321 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95570	5970 				15285930				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100067	19950901	00067	CE 	1995	9	1	95ZZZX4322 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95571	5988 				15285931				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100068	19950901	00068	CE 	1995	9	1	95ZZZX4323 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95574	5981 				15285932				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100069	19950901	00069	CE 	1995	9	1	95ZZZX4324 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95591	5568 				15285933				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100070	19950901	00070	CE 	1995	9	1	95ZZZX4325 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95593	5827 				15285934				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100071	19950901	00071	CE 	1995	9	1	95ZZZX4326 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95604	5028 				15285935				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100072	19950901	00072	CE 	1995	9	1	95ZZZX4327 	1	19950705	G	5753	052390113	ARM 			CESSNA	150 	152 	2071835	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	95606	6332 				15285936				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O			NT	3A19 					 
1995090100073	19950901	00073	CE 	1995	9	1	95ZZZX4328 	1	19950705	G	5753	052390113	ARM 			CESSNA	172 	R172E 	2072413	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	88763	8976 				R1720216				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O				3A17 					 
1995090100074	19950901	00074	CE 	1995	9	1	95ZZZX4329 	1	19950705	G	5753	052390113	ARM 			CESSNA	172 	172RG 	2072438	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	9452D	6405 				172RG1168				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O				3A17 					 
1995090100075	19950901	00075	CE 	1995	9	1	95ZZZX4330 	1	19950705	G	5753	052390113	ARM 			CESSNA	172 	172RG 	2072438	CE 										FLAP SUPPORT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	6328V	6540 				172RG0627				DURING COMPLIANCE WITH SEB 95-3, THE RIB ASSY FLAP SUPPORT ARMS, PN 0523901-13 LT, OR PN 0523901-14 RT, FOUND WEAR GROOV	ES WHICH EXCEED THE MAXIMUM DEPTH OF 0.020 INCH. AT LEAST ONE OR BOTH ARMS WORN BEYOND LIMIT.					1	H	7	1 	3O				3A17 					 
1995090100077	19950901	00077	GL 	1995	9	1	95ZZZX4332 	3	19950726	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95604	5815 				15285935		DG092		A CRACK WAS FOUND IN THE HUB AREA. CRACK RADIATED FROM INSIDE THE HUB THROUGH THE FACE OF THE HUB TO THE MOUNTING SURFA	CE ENDING IN THE BOLT HOLE ADJACENT TO THE NR 1 BLADE. COMPLIANCE WITH MCCAULEY SB 169C AND AD 89-26-10 WAS ACCOMPLISHE	D AT 3229.7 TOTAL HOURS WHERE NO DEFECTS WERE FOUND. A FREQUENT DYE PENETRANT INSPECTION WOULD BE RECOMMENDED. PROPELL	ER TOTAL TIME: 5,815.0 HOURS.			1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100078	19950901	00078	GL 	1995	9	1	95ZZZX4333 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B	L		GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95564	5342 				15285927		RPDG078		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100079	19950901	00079	GL 	1995	9	1	95ZZZX4334 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95563	5872 				15285926		RPDG125		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100080	19950901	00080	GL 	1995	9	1	95ZZZX4335 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95565	5531 				15285928		RPCF071		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100081	19950901	00081	GL 	1995	9	1	95ZZZX4336 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95566	6172 				15285929		RPDG022		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100082	19950901	00082	GL 	1995	9	1	95ZZZX4337 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95570	5970 				15285930		RPDG126		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100083	19950901	00083	GL 	1995	9	1	95ZZZX4338 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95571	5988 				15285931		RPDG018		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100084	19950901	00084	GL 	1995	9	1	95ZZZX4339 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95574	5980 				15285932		RPDG065		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100085	19950901	00085	GL 	1995	9	1	95ZZZX4340 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95591	5839 				15285933		RPDG079		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100086	19950901	00086	GL 	1995	9	1	95ZZZX4341 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	95593	5827 				15285934		RPDG077		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100087	19950901	00087	GL 	1995	9	1	95ZZZX4342 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	94508	4215 				15285698		RPCF108		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100088	19950901	00088	GL 	1995	9	1	95ZZZX4343 	3	19950811	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19	69051	5290 				15282461		R773228		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.	1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995090100089	19950901	00089	GL 	1995	9	1	95ZZZX4344 	3	19950811	G	6114		HUB 													MCAULY	1A103	1A103TCM 	GL 	NR 1 BLADE	CRACKED 	B			GPWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19								RPDC058		FOLLOWING THE DISCOVERY OF A PROPELLER WITH A HUB CRACK AT THE LEADING EDGE BOLT HOLE OF NR 1 BLADE, INSPECTION OF SAME 	PROPELLER MODEL ON OTHER 'N' NUMBERED AIRCRAFT WAS MADE. THE OTHER PROPELLERS' TIMES RANGED FROM 3,950 HRS TO 6,171 HRS	, TT. ALL OF THE OLDER PROPS HAD AD89-26-10 COMPLIED WITH PER MCCAULEY SB 169C. THE 3,950 HOUR PROP WAS NOT CRACKED. A	LL OTHERS, WITH THE EXCEPTION OF THE NEW PROP, HAD CRACK INDICATIONS. EVERY CRACK WAS IN THE SAME GENERAL LOCATION. AL	L INSPECTIONS WERE DONE WITH MAGNAFLUX MODEL ED520 EDDY CURRENT TESTER. THE MACHINE WAS SENT TO CENTURION NDT AND RECER	TIFIED ON JUNE 23, 1995. ALL OF THE CRACKS THAT WERE FOUND SHOWED A FULL SCALE DEFLECTION.											5	N	P50GL	 
1995090100342	19950901	00342	SO 	1995	9	1	95ZZZX4349 	2	19950815	G	7414	M3525	COIL 	SLICK 	4201REVE 	TCRAFT	19 	F19 	9230703	GL 	CONT 	O200 	O200A 	17020	SO 					MAGNETO	OPEN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	3682T	145 			89060087	F089	255713			INSPECTION FOUND M3121 DISTRIBUTOR BLOCK AND ROTOR CONTACTS BURNED. M3525 COIL FAILED - OPEN AND HAD A CRACK IN SIDE.						1	H	7	1 	3O	3	O		1A9 	E252				 
1995090100343	19950901	00343	EA 	1995	9	1	95ZZZX4350 	2	19950731	G	8520	71105ASR218	LIFTER 			PIPER 	PA38 	PA38112 	7103812	SO 	LYC 	O235 	O235L2C 	41505	EA 					NR 2 CYL EXH	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	2412K	1071 				3879A0621	L1874815			DURING ANNUAL INSPECTION, NR 2 CYLINDER WAS REMOVED DUE TO LOW COMPRESSION. WHEN CYLINDER WAS REMOVED, THE CUP PORTION 	OF THE EXHAUST SOLID LIFTER FELL TO THE FLOOR. THE CUP SECTION OF THE LIFTER HAD BROKEN COMPLETELY OFF. ALL LIFTERS HA	D BEEN REPLACED DURING PREVIOUS ENGINE OVERHAUL.				1	L	7	1 	3O	3	O		A18SO 	E223				 
1995090100344	19950901	00344	CE 	1995	9	1	95ZZZX4351 	1	19950701	G	7160	628122	CONTROL ARM 			CESSNA	150 	150M 	2071830	CE 										CARBURETOR HEAT	FRACTURED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	3240V					15076436				INSPECTION FOUND CARBURETOR AIR INTAKE HOUSING ASSEMBLY WITH CARBURETOR HEAT CONTROL ARM FRACTURES.						1	H	7	1 	3O				3A19 					 
1995090100345	19950901	00345	CE 	1995	9	1	95ZZZX4352 	1	19950718	G	3240		PEDAL 			BBAVIA	8 	8KCAB 	2110612	CE 										PILOT LT BRAKE	BROKE 	D		A		K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	09	924TA	144 				73694				PEDAL BROKE IN TWO WITH NORMAL PRESSURE APPLIED. FACTORY PARTS DEPARTMENT REPORTS THIS IS SECOND ONE THAT HAS BROKEN. R	EPLACED WITH NEW FACTORY PART. TOTAL TIME OF AIRCRAFT 143.8 HOURS SINCE NEW.					1	H	7	1 	3O				A21CE 					 
1995090100347	19950901	00347	CE 	1995	9	1	95ZZZX4354 	1	19950815	G	2913	HYH5001	POWER PACK 	PRESTOLITE 		BEECH 	76 	76 	1153005	CE 										MLG	DEFECTIVE 	B			HBKR	O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			SW	11	3739Z		353 		AH2474	ME380				LANDING GEAR FAILED TO EXTEND THE FIRST TRY. RECYCLED LANDING GEAR AND IT EXTENDED OK. PUT AIRCRAFT IN SHOP, JACKED AI	RCRAFT, AND DETERMINED PROBLEM TO BE POWER PACK. INSTALLED ON OVERHAULED POWER PACK AND HAD NORMAL OPERATION.					1	L	7	2 	3O				A29CE 					 
1995090100348	19950901	00348	EA 	1995	9	1	95ZZZX4355 	2	19950728	G	8530	SL134441	PISTON PIN 			PIPER 	PA60 	PA60601P 	7106012	NM 	LYC 	O540 	LTIO540J2BD 	41533	EA 					NR 3 CYLINDER	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	36BW	243 				61P0232033	L227168A			DISASSEMBLING ENGINE FOR SEALING OIL LEAKS. WHEN NR 3 PISTON PIN WAS PUSHED OUT IT WAS FOUND BROKEN IN HALF RIGHT IN TH	E MIDDLE OF THE CONNECTING ROD BUSHING. FOUND LIGHT (0.002 INCH - 0.003 INCH DEEP) SCORING IN CONNECTING ROD BUSHING. A	PPARENTLY, THE PIN HAD NOT BEEN BROKEN FOR LONG. REMAINDER OF CYLINDER ASSY APPEARED NORMAL. NO SIGNIFICANT DIFFERENCE	 FROM OTHER 5. PLAN TO SUBMIT PIN TO U. OF T. METALLURGY LAB FOR ANALYSIS. APPEARS TO BE METAL DEFECT.			1	M	7	2 	3O	3	O	RT	A17WE 	E14EA				 
1995090100349	19950901	00349	NM 	1995	9	1	95ZZZX4356 	1	19950713	G	5220	250003503	EXIT 			PIPER 	PA60 	PA60601 	7106010	NM 										EMERGENCY DOOR	DEPARTED 	D		A		O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			SW	07	8054J	6572 				610537132				EMERGENCY EXIT DEPARTED AIRCRAFT AFTER LEVELLNG OFF AT 9,500 FEET. THE AIRCRAFT SUSTAINED NO DAMAGE TO EXIT FRAME OR TA	IL SURFACES. INVESTIGATION REVEALED THE FORWARD RETENTION HINGE, PN 210074-01, WAS BROKEN. AFT HINGE WAS ALSO STILL AT	TACHED, BUT RIPPED FROM DOOR. PREVENTION: STRONGER HINGE DESIGN SERVICE LIFE PLACED ON PART. REPETITIVE INSPECTIONS O	F ALL EXITS.			1	M	7	2 	3O			RT	A17WE 					 
1995090100350	19950901	00350	CE 	1995	9	1	95ZZZX4357 	1	19950712	G	5220	52111302	EXIT 			CESSNA	402 	402CESSNA 	207590K	CE 										EMERGENCY	DEPARTED 	D		A		O				OTHER 				D			INFLIGHT SEPARATION 			DE	DESCENT 	1			SW	07	4046Q	5500 				4020146				DURING DESCENT, THE EMERGENCY EXIT DEPARTED THE AIRCRAFT. THE AIRCRAFT SUSTAINED NO DAMAGE TO THE EXIT FRAME OR TAIL. I	NVESTIGATION BY MAINTENANCE PERSONNEL REVEALED BOTH MOUNTING CLIPS ON THE AFT SIDE OF DOOR SHOWED SIGNS OF SHEARED RIVET	S AND WERE STILL IN PLACE. THE FORWARD CLIPS WERE FOUND BROKEN AND CORRODED CLIP, PN 5211130-1S. SUSPECT CORROSION, PO	OR DESIGN. PREVENTION - DESIGN CLIPS IN STAINLESS STEEL.			1	L	7	2 	3O				A7CE 					 
1995090100351	19950901	00351	SO 	1995	9	1	95ZZZX4358 	1	19950803	G	7810	LW120935	CLAMP 			PIPER 	PA32 	PA32R301T 	7103220	SO 										NR 5 CYL EXH	LOOSE 	B		A	UG1R	A				UNSCHED LANDING 				A			FLAME/FIRE 			CL	CLIMB 	1			SW	03	8108V	969 				32R8029008				AFTER TAKEOFF, EXHAUST GASES MELTED FINS ON NR 5 CYLINDER AND CAUSED ENGINE FIRE. FIRE SPREAD THROUGH FORWARD BAGGAGE A	REA AND INTO COCKPIT. AIRCRAFT WAS LANDED SAFELY AND FIRE EXTINGUISHED. 'V' BAND COUPLING FOR EXHAUST CONNECTION AT NR	 5 CYLINDER WAS FOUND LOOSE. PART CAUSING FIRE WAS NOT SAFETIED PER RECOMMENDATIONS FROM MANUFACTURERS. REF: PIPER SB	 NR 884.			1	L	7	1 	3O				A3SO 					 
1995090100352	19950901	00352	CE 	1995	9	1	95ZZZX4359 	1	19950613	G	2436	EM2070363800561	REGULATOR 			BEECH 	36 	A36TC 	1151603	CE 										DC OVERVOLTS	FAILED 	C				O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			WP	21	364DZ	1610 				EA147				UPON GEAR RETRACTION DURING A 'GO-AROUND', THE CHARGING SYSTEM WENT INTO A HIGH-VOLTAGE RUNAWAY. THE OVERVOLTAGE RELAY 	DID NOT TRIP TO PROTECT THE SYSTEM. THE BATTERY MASTER RELAY BURNED OUT. WITHOUT THE BATTERY IN THE CIRCUIT, THE VOLTA	GE WENT VERY HIGH AND DAMAGED ALL ELECTRONIC EQUIPMENT IN THE AIRCRAFT. THE APPARENT FAILED COMPONENT WAS NOT VIBRATION	 PROTECTED ON THE CIRCUIT BOARD. SUGGEST VISUAL INSPECTION OF THE INTERIOR OF VOLTAGE REGULATOR FOR DAMAGED COMPONENTS 	AS THE OVERVOLTAGE CIRCUIT CAN BE FAILED WITH NO INDICATION DURING NORMAL USE. ALSO, LARGER DIODES SHOULD BE USED IN TH	E BATTERY MASTER RELAY CIRCUIT.	1	L	7	1 	3O				3A15 					 
1995090100353	19950901	00353	CE 	1995	9	1	95ZZZX4360 	1	19950725	G	5220	45A30257009	HOOK 			BEECH 	MU300 	400BEECH 		CE 										EMERG EXIT	WORN 	B		A	OG5R	O				OTHER 				O			OTHER 			CR	CRUISE 	1			GL	21	3196N	676 				RK96				EMERGENCY EXIT HANDLE (INTERIOR) POPPED OPEN DURING FLIGHT. FOUND HOOK WORN. INSTALLED NEW HOOK. HANDLE FAILED PULL T	EST. (10-15 POUNDS.) HOOK TRAVEL WAS INSUFFICIENT. REMOVED SMALL AMOUNT OF METAL FROM CONTACT AREA OF BRACKET. PERFO	RMED SECOND PULL TEST AND MET SPEC OF 50-70 POUNDS.				2	H	7	2 	4F			RT	A16SW 					 
1995090100354	19950901	00354	EA 	1995	9	1	95ZZZX4361 	2	19950712	G	7210	310074701	SHAFT 								PWA 	PT6 	PT6A65B 	52043	EA 					PROP	MISMATCH SET 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										PART WAS RECEIVED FROM THE VENDOR. THE PROP SHAFT AND SLEEVE HAVE TO BE A MATCHED SET, SAME S/N. THE SLEEVE HAS A S/N 	OF A1351. THE SHAFT IS S/N 5F780. THEREFORE, THIS IS NOT A MATCHED SET.										4	T			E4EA				 
1995090100355	19950901	00355	NM 	1995	9	1	95ZZZX4362 	1	19950802	G	5330		SKIN 			BOEING	727 	727225 	1384077	NM 										FS 235-243	CRACKED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	352PA	59103				20616				VISUAL INSPECTION OF RT SECTION 41 EXTERNAL SKIN PER AD 94-07-08 AND SB 727-53-0183 REVEALED 14 EACH CRACKED FASTENER HO	LES (9 EACH AT BS 235, 5 EACH AT BS 243), 18 INCHES TO 28 INCHES BELOW RT AFT SIDE COCKPIT WINDOW. CRACK LENGTH RANGED 	FROM .100 INCH TO .300 INCH. SUBSEQUENT EDDY CURRENT INSPECTION OF REMAINING HOLES IN SKIN PANEL FOUND NO ADDITIONAL CR	ACKS AT THIS TIME. TOTAL TIME ON ACFT, 59,103.16 HOURS. TOTAL CYCLES, 40,945.			2	L	7	3 	4F				A3WE 					 
1995090100356	19950901	00356	NM 	1995	9	1	95ZZZX4363 	1	19950802	G	5311		FRAME 			BOEING	727 	727225 	1384077	NM 										FS 783.95	CRACKED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	352PA	59103				20616				A VISUAL INSPECTION OF FRAME FLANGE AND WEB AT FS 783.95 JUST BELOW STR 17L, FOUND CRACK, 3 INCHES INTO WEB, FROM FLANGE	 TO LIGHTING HOLE. SUSPECT CAUSE BY METAL FATIGUE. REPAIR DONE IAW BOEING DRAWING NR 65C36280.					2	L	7	3 	4F				A3WE 					 
1995090100357	19950901	00357	NM 	1995	9	1	95ZZZX4364 	1	19950802	G	5510	652791727	PANEL ASSY 			BOEING	727 	727225 	1384077	NM 										LT HORIZ STAB	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	352PA	59103				20616				INSPECITON FOUND NR 1 HORIZONTAL STABILIZER BALANCE PANEL AND REAR PANEL HINGE MATING SURFACE HAD LIGHT CORROSION. HING	E, P/N 65-26659-1-2. THERE WAS NO CORROSION COMPOUND IN NR 1 BALANCE PANEL BAY.					2	L	7	3 	4F				A3WE 					 
1995090100358	19950901	00358	NM 	1995	9	1	95ZZZX4365 	1	19950802	G	5510	652791714	PANEL ASSY 			BOEING	727 	727225 	1384077	NM 										RT HORIZ STAB	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	352PA	59103				20616				INSPECTION FOUND NR 10 HORIZONTAL STABILIZER BALANCE PANEL AND REAR PANEL HINGE MATING SURFACE HAD LIGHT CORROSION. HIN	GE, PN 65-26659-1-2. THERE WAS NO CORROSION COMPOUND IN NR 10 BALANCE PANEL BAY.					2	L	7	3 	4F				A3WE 					 
1995090100359	19950901	00359	WP 	1995	9	1	95ZZZX4366 	2	19950811	G	7230	8933831	HOUSING 			SWRNGN	SA226 	SA226TC 	8780404	SW 	GARRTT	TPE331	TPE3313U 	01514	WP 					2ND IMPELLER	DAMAGED 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			SW	11	509SS	3288 	88 		4P13644	TC206	P03295			ENGINE WAS SENT IN FOR GBI AND HSI ON 10-14-94 WITH ENGINE TT OF 3,081.8 HOURS. ENGINE WAS RETURNED FOR ITT HARNESS REP	LACEMENT AND IT WAS FOUND THAT THE SECOND IMPELLER HOUSING SPRAY METAL HAD BECOME UNATTACHED. VENDOR WAS NOTIFIED AND R	EPAIRED UNIT. ENGINE WAS REPAIRED AND REASSEMBLED, 87.6 HOURS LATER, ENGINE RETURNED DUE TO LOW POWER. AGAIN, FOUND SE	COND IMPELLER HOUSING SPRAY METAL HAD COME UNATTACHED CAUSING MAJOR DAMAGE. VENDOR WAS NOTIFIED AGAIN OF PROBLEM. IMPE	LLER HOUSING WAS SENT OUT TO THIRD PARTY FOR EVALUATION.		2	L	7	2 	4T	4	T	RT	A8SW 	E4WE				 
1995090100360	19950901	00360	SO 	1995	9	1	95ZZZX4367 	1	19950729	G	7810	NH100229910	CLAMP 			LKHEED	1329 	132923E 	5263116	SO 										NR 2 TAIL PIPE	MISSING 	B	L	A	DELR	A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			CE	03	1DB	6625 				5155				WHILE TEST FLYING, JULY 29, 1995, THE PILOT GOT AN ENGINE FIRE WARNING LIGHT. HE LANDED AND FOUND THE NR 2 ENGINE TAIL 	PIPE MISALIGNED. TAIL PIPE CLAMP, PN NH1002299-10, WAS FOUND MISSING. CLAMP TO BE REPLACED WITH A NEW CLAMP. THE AIRC	RAFT TOTAL TIME WAS 6,625.5 HOURS, AND LANDINGS, 4,842. THE NR 2 ENGINE HOURS WERE 4,053.9 AND CYCLES 2,787. GARRETT E	NGINE, MODEL NR TFE731-3-1E, SN P75234C.			2	L	7	4 	4J				2A15 					 
1995090100368	19950901	00368	CE 	1995	9	1	95ZZZX4375 	1	19950811	G	5412	0851601201	BULKHEAD 			CESSNA	414 	414 	2075908	CE 										LT ENGINE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	854RM	2730 				4140959				AT THE ANNUAL INSPECTION, LEFT ENGINE COMPARTMENT REAR CANTED BULKHEAD THAT IS PART OF THE ENGINE MOUNT STRUCTURE WAS FO	UND TO HAVE A SMALL HOLE FROM INTERGRANULAR CORROSION. CONSIDERED TO BE UNAIRWORTHY.					1	L	7	2 	3O			RT	A7CE 					 
1995090100369	19950901	00369		1995	9	1	95ZZZX4376 	4	19950720	G	2562	BP1040	BATTERY 	MARTECH 	EB2BCD 	MOONEY	M20 	M20D 	5870210	SW 										ELT	CASE CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	1919Y				15517	214				BATTERY CASE CRACKED FROM LEAKING BATTERY CELLS. BATTERY CELLS ENCLOSED IN HARD PLASTIC CASE. MANUFACTURER REP REPORTE	D CRACK WAS FROM HIGH CABIN TEMPS DUE TO SITTING OUTSIDE IN SUN THAT WAS CAUSING PROBLEM. THIS IS SECOND CONSECUTIVE AN	NUAL ON THIS ACFT THAT FOUND ELT CASE DAMAGED DUE TO LEAKING BATTERY PACK.				1	L	7	1 	3O				2A3 					 
1995090100371	19950901	00371	NE 	1995	9	1	95ZZZX4378 	2	19950730	G	8530		PISTON 			GRUMAN	SA16 	HU16 	3950405	EA 	PWA 	R1830 	R1830* 	52020	NE 					RT ENG NR 9 CYL	DAMAGED 	D				E				ENGINE SHUTDOWN 				J	E		WARNING INDICATION 	VIBRATION/BUFFET 		CR	CRUISE 	1			WP	28	7025J		110 			131910				AT 6,500 MSL-10 MI E OF DSM, RT ENGINE CHIP DETECTOR LIGHT CAME ON WITH ENGINE VIBRATION. FEATHERED RT ENGINE, PRECAUTI	ONARY. LANDING NORMAL. FOUND VALVE AND PISTON DAMAGE NR 9 CYLINDER. REPLACED CYLINDER, RECHECKED BOTH ENGINES FOR VAL	VE CLEARANCE, CHANGED OIL.				2	H	7	2 	4R	4	R		EXPA2H72	5E4				 
1995090100372	19950901	00372	SW 	1995	9	1	95ZZZX4379 	1	19950822	G	5755	01577	SPEED BRAKE 			MOONEY	M20 	M20J 	5870219	SW 										WING	MALFUNCTIONED 	D		A		K				NONE 				F			FLT CONT AFFECTED 			TX	TAXI/GRND HDL 	1			NE	05	40BK	303 				243325				AIRCRAFT TAXIED TO RAMP, SHUT DOWN ALL SYSTEMS. SPEED BRAKE STAYED IN THE FULL UP. THIS WAS ONLY ONE SPEED BRAKE ON ON	E SIDE. AIRCRAFT WILL ROLL AT HIGH SPEED, BUT NOT TO0 BAD AT LOW SPEEDS WITH ONE SPEED BRAKE EXTENDED.					1	L	7	1 	3O				2A3 					 
1995090100373	19950901	00373	SW 	1995	9	1	95ZZZX4380 	1	19950817	G	5755	01577	SPEED BRAKE 			MOONEY	M20 	M20M 	5870222	SW 										WING	FAIL TO REETRACT	D				K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			NE	05	9151X	401 				270149				BOTH SPEED BRAKES HAVE BEEN OUT OF AIRCRAFT FOR FAILURE TO RETRACT. LEFT UNIT AT ABOUT 300 HOURS AND RIGHT UNIT AT 401.	0 HOURS. HAVE HAD 2 AIRCRAFT IN 30 DAYS WITH THE SAME RETRACT TROUBLE.					1	L	7	1 	30			RT	2A3 					 
1995090100374	19950901	00374	SW 	1995	9	1	95ZZZX4381 	1	19950817	G	2822	A10051D	PUMP 			MOONEY	M20 	M20M 	5870222	SW 										AUX FUEL	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	1086D					270041				AIRCRAFT HAS HAD 3 AUXILIARY FUEL PUMPS FAIL IN 1,000 HOURS. TWO HAVE FAILED, 1 HAD INTERMITTENT HIGH PRESSURE.						1	L	7	1 	30			RT	2A3 					 
1995090100375	19950901	00375	SW 	1995	9	1	95ZZZX4382 	1	19950807	G	2822	A10051D	PUMP 			MOONEY	M20 	M20M 	5870222	SW 										AUXILIARY FUEL	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	1085W					270043				AIRCRAFT HAD AUXILIARY PUMP FAIL WITH ONLY 426 HOURS ON IT.						1	L	7	1 	30			RT	2A3 					 
1995090100376	19950901	00376	CE 	1995	9	1	95ZZZX4383 	1	19950701	G	5511		RIB 			CESSNA	210 	210N 	2073453	CE 										LT/RT HORIZ STAB	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	4729C					21063604				DURING ANNUAL INSPECTION, FOUND BOTH LT AND RT HORIZONTAL STABILIZER'S LEADING EDGE (NOSE) RIBS CRACKED AND BROKEN LOOSE	 FROM STABILIZER SKIN. BROKEN RIBS ARE FOUND BY SQUEEZING LEADING EDGE AND LISTENING FOR SNAPPING NOISE PER CESSNA SNL-	87-18. SUBMITTER STATED THIS HAS BEEN A PROBLEM ON MANY 210 AND 206 SERIES AIRCRAFT. INSTALLED NEW STYLE RIBS.				1	H	7	1 	3O				3A21 					 
1995090100377	19950901	00377	SO 	1995	9	1	95ZZZX4384 	2	19950817	G	8500		ENGINE 			CESSNA	414 	414A 	2075907	CE 	CONT 	O520 	TSIO520NB 	17040	SO 					CYLINDER	DEFECTIVE 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			NE	03	300SQ	817 				414A0416	800543			ENGINE HAS HIGH OIL CONSUMPTION, HIGH COOLENT PRESSURE, ROUGH RUNNING, LOW MANIFOLD PRESSURES. SUSPECT POSSIBLE CRACKED	 CYLINDER(S).					1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995090100378	19950901	00378		1995	9	1	95ZZZX4385 	4	19950801	G	3416	A30	ENCODER 	ACK 																COCKPIT	ERRATIC 	B			QQMR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23										ALTITUDE ENCODER CALIBRATION APPEARS AFFECTED BY MECHANICAL STRESS OR VIBRATION BEING TRANSFERRED TO THE STATIC LINE CON	NECTION AT THE ENCODER. IT APPEARS THAT MOVEMENT OF THE FITTING APPLIES STRESS TO THE SENSING ELEMENT IN THE ENCODER. T	HIS STRESS IS INTERPRETED AS ALTITUDE CHANGE AND THE ENCODER OUTPUTS RESPOND ACCORDINGLY EVEN THOUGH NO ALTITUDE CHANGE 	HAS OCCURRED. THE CONDITION MAY MANIFEST ITSELF FOLLOWING INSTALLATION OR MONTHS LATER AND THE PILOT MAY NOT BE AWARE O	F THE CONDITION.															 
1995090100379	19950901	00379	GL 	1995	9	1	95ZZZX4386 	1	19950816	G	7921	626189	COOLER 	LORINORDAM 		BLANCA	17 	1730A 	1220433	GL 										ENG OIL	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CE	01	8223R	2865 			838	30407				REPAIR STATION FOUND CRACKS IN MOUNTING BASE OF OIL COOLER DURING OVERHAUL TO CORRECT LEAK IN TUBES. EXCHANGE UNIT WAS 	INSTALLED.					1	L	7	1 	3O				A18CE 					 
1995090100380	19950901	00380		1995	9	1	95ZZZX4387 	4	19950701	G	2562	0004006A	BATTERY 	ARTEX 																ELT BATTERY	STRAP FAILED 	B			AQHR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										THE BONDING STRAP BETWEEN TWO OF THE SIX BATTERIES BECAME DISCONNECTED WHEN INSTALLING THE BATTERY INTO THE ELT. THE ME	THOD OF ATTACHING THE STRAPS TO THE BATTERY APPEARS TO BE SPOT WELDS IN FOUR LOCATIONS ON EACH END OF THE STRAP. ON THE	 FAILED END, ONE WELD DID NOT PENETRATE THROUGH TO THE CELL, AND AT THE OTHER THREE LOCATIONS, EACH OF THE WELDS WERE LO	CATED AT THE STRAP EDGE ONLY. THE ELT FAILED TO OPERATE DURING TEST. THIS COULD VERY EASILY HAVE FAILED DURING NORMAL 	OPERATIONS (VIBRATION).															 
1995090100381	19950901	00381	CE 	1995	9	1	95ZZZX4388 	1	19950809	G	2913	9881128	POWER PACK 			CESSNA	210 	T210N 	2073456	CE 										MLG	MOTOR FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	1937U	1484 			3175	21064753				LANDING GEAR POWER PACK INOPERATIVE. REMOVED ELECTRIC MOTOR. FOUND ARMATURE HAD COME APART.						1	H	7	1 	3O				3A21 					 
1995090100382	19950901	00382	SO 	1995	9	1	95ZZZX4389 	1	19950809	G	3213	207504	TRUNNION 			PIPER 	PA30 	PA30 	7103002	SO 										LT MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	126PF	3388 				301122				FOUND LEFT MLG TRUNNION CRACKED AT UPPER WEB WHERE A HOLE HAS BEEN DRILLED FOR A CLAMP.						1	L	7	2 	3O				A1EA 					 
1995090100383	19950901	00383	EA 	1995	9	1	95ZZZX4390 	2	19950726	G	8520	LW12596	ROD BOLT 			BEECH 	80 	65B80 	1152812	CE 	LYC 	O540 	IGSO540A1A 	41532	EA 					NR 6 ROD	BROKEN 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			CE	05	265RW	122 				LD381	LL317830			ROD BOLT BROKE SUDDENLY WITH NO WARNING. ENGINE WAS RUNNING SMOOTH UNTIL ROD BROKE.						1	L	7	2 	3O	3	O		3A20 	1E7				 
1995090100384	19950901	00384		1995	9	1	95ZZZX4391 	2	19950807	G	7414	10357174	CONTACT ASSY 		S4LN20 															MAGNETO	MISMANUFACTURED 	D	P			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	01										INSPECTION FOUND POINT MIS-MATCH NOTED ON THREE SETS OF 10-357174 CONTACT ASSEMBLIES WHICH WERE PURCHASED AS NEW REPLACE	MENT PARTS FROM A TCM DISTRIBUTOR.																		 
1995090100385	19950901	00385	SO 	1995	9	1	95ZZZX4392 	2	19950801	G	8520	649895	CRANKCASE 			CESSNA	402 	402B 	207590P	CE 	CONT 	O520 	TSIO520E 	17040	SO 					NR 4 CYL PAD	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	07	53SA	7712 	469 			402B0597	20650271E			DURING A ROUTINE INSPECTION, THE LEFT ENGINE CRANKCASE WAS FOUND CRACKED AT THE NR 4 CYLINDER MOUNTING PAD. AD 77-13-22	 DOES NOT APPLY TO THIS CRANKCASE DUE TO MARKINGS. SUSPECT FATIGUE, WEAK DESIGN. SUBMITTER SUGGESTS INSPECTING AREA CL	OSELY AT 100-HOUR INTERVALS. INVESTIGATE ALL OIL LEAKS IMMEDIATELY ON CONTINENTAL CRANKCASES.				1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995090100386	19950901	00386	SO 	1995	9	1	95ZZZX4393 	2	19950811	G	8530	6291171	ROTOR 								CONT 	O520 	IO520* 	17032	SO 					EXH VALVE	DEFECTIVE 	B			YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11										FOUND EXHAUST VALVE ROTOR CAP WILL NOT ROTATE. THIS VALVE ROTOR WAS OUT OF A CYLINDER VALVE ASSY.											3	O			E5CE				 
1995090100387	19950901	00387		1995	9	1	95ZZZX4394 	2	19950725	G	7322	CF131533	THROTTLE SHAFT 	FACET 	10396512 															CARBURETOR	MISMANUFACTURED 	B			TY5R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	03					H171449					DURING OVERHAUL OF MARVEL SCHEBLER CARBURETOR, A NEW THROTTLE SHAFT NR CFB-1533, WAS SELECTED FOR INSTALLATION. WHEN IN	STALLED, FOUND THE SHAFT WOULD NOT TRAVEL TO FULL OPEN STOP. AFTER CHECKING SHAFT AGAINST ANOTHER, FOUND THE STOP ARM W	AS PINNED IN THE WRONG LOCATION ON THE SHAFT. THE REPLACEMENT WAS OKAY.																	 
1995090100388	19950901	00388	SO 	1995	9	1	95ZZZX4395 	2	19950701	G	8520	629340	ROD BOLT 								CONT 	O470 	O470U 	17026	SO 					NR 5 CYLINDER	BROKE 	G				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	17			1300 							1300 HOURS SINCE FACTORY OVERHAUL, ENGINE NR 5 CYLINDER CONNECTING ROD BOLT BROKE IN TWO PIECES.											3	O			E273				 
1995090100390	19950901	00390	CE 	1995	9	1	95ZZZX4397 	1	19950708	G	5753	0523231	RIB 			CESSNA	172 	172B 	2072406	CE 										RT INBD FLAP	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	6921X	4063 				17247821				FLAP TRACK PART DID NOT FAIL, HOWEVER, SEVERE CORROSION WAS FOUND DURING AN ANNUAL INSPECTION AT A POTENTIALLY WEAK AREA	 ON THE PART. CORROSION FOUND WAS INTERGRANULAR AND WAS ON BOTH SIDES OF THE PART IN AFFECTED AREA. SUBMITTER SUGGESTS	 A CLOSE INSPECTION OF THESE FLAP TRACKS, AS COROSION HAD STARTED ON ALL 3 OF THE OTHER FLAP TRACKS ON THIS AIRCRAFT.				1	H	7	1 	3O			NT	3A12 					 
1995090100391	19950901	00391	SO 	1995	9	1	95ZZZX4398 	1	19950802	G	2410	PU672A	DRIVE PULLEY 	PRESTOLITE 	ALU8421 	PIPER 	PA23 	PA23250 	7102308	SO 										ALTERNATOR	FAILED 	D	S			K				NONE 				H			ELECT. POWER LOSS-50 PC 			IN	INSP/MAINT 	1			GL	11	7436C				6M000189	277754017				DURING RUN-UP, LEFT ALTERNATOR FAILED AND COULD NOT BE RESET. INSPECTION REVEALED THE DRIVE PULLEY HOUSING HAD SHEARED. 	 SUSPECTED CAUSE IS MATERIAL FAILURE OF THE METAL ITSELF. SUBMITTER RECOMMENDS THAT OTHER OPERATORS INSPECT THE DRIVE P	ULLEYS OF SIMILAR ALTERNATORS. PART HAS BEEN RETAINED FOR INSPECTION.				1	L	7	2 	3O				1A10 					 
1995090800030	19950908	00030	SW 	1995	9	8	95ZZZX4399 	1	19950731	G	2510	206031102057	KICK PANEL 			BELL 	206 	206L1 	1182107	SW 										AIRFRAME	SEPARATION 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1067D					45435				DURING AIRFRAME INSPECTION BEFORE REFURB, FOUND KICK PANEL WITH SEPARATION AND CORROSION.						1	G	7	1 	3U				H2SW 					 
1995090800031	19950908	00031	SW 	1995	9	8	95ZZZX4400 	1	19950731	G	5320	206033100225A	TUB ASSY 			BELL 	206 	206L1 	1182107	SW 										FWD AIRFRAME	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1067D				A006133	45435				DURING AIRFRAME INSPECTION BEORE REFURB, FOUND TUB ASSEMBLY CORRODED AND SEPARATED.						1	G	7	1 	3U				H2SW 					 
1995090800034	19950908	00034	SW 	1995	9	8	95ZZZX4403 	1	19950731	G	3213	206030104023	FITTING 			BELL 	206 	206L4 	1182110	SW 										FWD CROSS-TUBE	CRACKED 	B	S		ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	171AL	2113 				52064				WHILE PERFORMING DAILY SERVICE CHECK, NOTED CROSS-TUBE FITTING WAS CRACKED. FITTING WAS FOUND CRACKED IN THE SAME MANNE	R AS REPORTED ON MDR'S SUBMITTED ON 5-8-95 AND ON 2-7-94 AND EARLIER REPORTED CRACKED FITTINGS.					1	G	7	1 	3U			NC	H2SW 					 
1995090800035	19950908	00035	SW 	1995	9	8	95ZZZX4404 	1	19950721	G	6230	206010335001	LEVER ASSEMBLY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2018R		550 			45681				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001 	SPACERS, 4 EACH, 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH, NAS 6605D64 BOLTS, 1 EACH, 206-010-	470-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 550.3.				1	G	7	1 	3U				H2SW 					 
1995090800036	19950908	00036	SW 	1995	9	8	95ZZZX4405 	1	19950721	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2018R		550 			45681				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001 	SPACERS, 4 EACH, 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH, NAS 6605D64 BOLTS, 1 EACH, 206-010-	470-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 550.3.				1	G	7	1 	3U				H2SW 					 
1995090800037	19950908	00037	SW 	1995	9	8	95ZZZX4406 	1	19950807	G	6230	206040536001	BEARING SET 		206040014105	BELL 	206 	206L1 	1182107	SW 										M/R MAST	PITTED 	B			ALGR	K				NONE 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	03	27554				0581	45246				TRANSMISSION CHIP LIGHT. INSPECTION FOUND MAST BEARING INNER RACE PITTED CAUSING CHIP LIGHT IN TRANSMISSION. BEARING S	ET SN 058-1 AND SN 058-2.					1	G	7	1 	3U				H2SW 					 
1995090800038	19950908	00038	SW 	1995	9	8	95ZZZX4407 	1	19950721	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D		497 			45280				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001 	SPACERS, 4 EACH, 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH, NAS 6605D64 BOLTS, 1 EACH, 206-010-	470-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 497.0.				1	G	7	1 	3U				H2SW 					 
1995090800039	19950908	00039	SW 	1995	9	8	95ZZZX4408 	1	19950721	G	6230	206010336005	LINK IDLER 		206010336005	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D		497 			45280				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001 	SPACERS, 4 EACH, 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH, NAS 6605D64 BOLTS, 1 EACH, 206-010-	470-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 497.0.				1	G	7	1 	3U				H2SW 					 
1995090800042	19950908	00042	SW 	1995	9	8	95ZZZX4411 	1	19950721	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL		337 			51460				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001 	SPACERS, 4 EACH, 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH, NAS 6605D64 BOLTS, 1 EACH, 206-010-	470-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 337.0.				1	G	7	1 	3U				H2SW 					 
1995090800043	19950908	00043	SW 	1995	9	8	95ZZZX4412 	1	19950721	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL		337 			51460				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001 	SPACERS, 4 EACH, 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH, NAS 6605D64 BOLTS, 1 EACH, 206-010-	470-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 337.0.				1	G	7	1 	3U				H2SW 					 
1995090800044	19950908	00044	SW 	1995	9	8	95ZZZX4413 	1	19950718	G	6320	2060400321	BEARING SET 		206040002025	BELL 	206 	206B 	1181511	SW 										M/R XMSN	MAKING METAL 	B			ALGR	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			SW	03	3896W		5814 		2658	3197				TRANSMISSION CHIP LIGHT ILLUMINATED IN-FLIGHT. FOUND BEARING SET BEGINNING TO BREAK DOWN FROM FATIGUE CAUSING METAL IN 	OIL AND CHIP LIGHT TO COME ON.					1	G	7	1 	3U				H2SW 					 
1995090800046	19950908	00046	SW 	1995	9	8	95ZZZX4415 	1	19950721	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5734M		476 			45449				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001 	SPACERS, 4 EACH, 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH, NAS 6605D64 BOLTS, 1 EACH, 206-010-	470-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 475.9.				1	G	7	1 	3U				H2SW 					 
1995090800047	19950908	00047	SW 	1995	9	8	95ZZZX4416 	1	19950721	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5734M		476 			45449				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH, 206-010-338-001 	SPACERS, 4 EACH, 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH, NAS 6605D64 BOLTS, 1 EACH, 206-010-	470-101 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 475.9.				1	G	7	1 	3U				H2SW 					 
1995090800048	19950908	00048	SW 	1995	9	8	95ZZZX4417 	1	19950807	G	6300	206040015015	DRIVESHAFT 			BELL 	206 	206L1 	1182107	SW 										M/R INPUT	DAMAGED 	B			ALGR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5829D				AMN00103	45270				INPUT DRIVESHAFT REMOVED DUE TO FIRE IN ROTOR BRAKE AREA. SUSPECT CAUSE ROTOR BRAKE MALFUNCTION. DRIVESHAFT WAS SCRAPP	ED DUE TO HEAT DAMAGE.					1	G	7	1 	3U				H2SW 					 
1995090800049	19950908	00049	NE 	1995	9	8	95ZZZX4418 	1	19950711	G	6210	7615009000046	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	709AL	11688	396 		A08600306	760278				DURING 500-HOUR INSPECTION, FOUND CRACK IN SPAR ORIGINATING FROM BUSHING HOLE. COMPONENT P/N 7600009300013.						1	G	7	2 	3U				H1NE 					 
1995090800050	19950908	00050	NE 	1995	9	8	95ZZZX4419 	1	19950711	G	6210	7615009000046	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	709AL	11639	396 		A08601132	760278				DURING 500-HOUR INSPECTION, FOUND CRACK IN SPAR ORIGINATING FROM ROOT END BUSHING HOLE. COMPONENT P/N 7600009300013.						1	G	7	2 	3U				H1NE 					 
1995090800051	19950908	00051	NE 	1995	9	8	95ZZZX4420 	1	19950711	G	7603	7630101910107	N1 CABLE 			SKRSKY	S76 	S76A 	8143006	NE 										THROTTLE LEVER	BROKEN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	712AL	11832				760280				AFTER COMPLETION OF THE ENGINE WASH, ATTEMPTED TO START NR 1 ENGINE FOR A DRYING RUN. THE ENGINE WOULD NOT LIGHT-OFF AN	D THE THROTTLE LEVER WAS STUCK IN THE FLIGHT POSITION. NR 1 THROTTLE CABLE WAS INSPECTED AND FOUND BROKEN APPROXIMATELY	 3.50 INCHES FROM THE POINT WHERE THE SHAFT ATTACHES TO THE FLEX PORTION OF THE INTERNAL CABLE. THIS BREAK WAS AT THE F	UEL CONTROL END OF THE CABLE.			1	G	7	2 	3U				H1NE 					 
1995090800052	19950908	00052	GL 	1995	9	8	95ZZZX4421 	2	19950710	G	7210	23059588	P.T.O. GEAR 		23035179 	SKRSKY	S76 	S76 	8143010	NE 	ALLSN 	250C 	250C30S 	03013	GL 					GEARBOX	MAKING METAL 	B			ALGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	769AL	337 			CG120136	760048	CAE890074S			DISASSEMBLED GEARBOX TO INSPECT GEARBOX FOR MAKING METAL. FOUND CAUSE TO BE THE P.T.O. GEAR, IMPROPER MACHINING ON THE 	GEAR TEETH. DISCOVERED THE TORQUE METER GEAR TO BE MAKING METAL DUE TO THE IMPROPER MACHINING ON THE P.T.O. GEAR TEETH.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995090800131	19950908	00131	SO 	1995	9	8	95ZZZX4427 	1	19950626	G	5102		VENT FLAP 			BALWKS	FIREFY	FIREFLY11 	1050125	SO 										ROTATION VENT	TORN 	D	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	2585Z					F11004				ROTATION VENT DESIGN AND INSTALLATION ON A 45 DEGREE ANGLE MAKE THEM VERY INEFFECTIVE WHEN TRYING TO ROTATE THE BALLOON 	IN FLIGHT TO ALIGN THE BASKET PROPERLY FOR LANDING. THIS CAUSES THE PILOT TO USE EXCESSIVE FORCE WHEN OPERATING THE VEN	TS. THE STRESS ON THE VENT STRUCTURE CAUSED THE STITCHING ON THE INNER VENT FLAP PANEL EDGE TAPE TOP ATTACH POINT ON TH	E PANEL TAPE TO FAIL WHICH, IN TURN, CAUSED A 28 INCH TEAR IN THE FABRIC OF THE INNER VENT FLAP PANEL. SUBMITTER SUGGES	TS REDESIGN OF THE ENTIRE VENT SYSTEM TO INCREASE OPERATING EFFECTIVENESS AND STRUCTURAL STRENGTH.		1	B	0	0 	0 			0	A14SO 					 
1995090800132	19950908	00132	EA 	1995	9	8	95ZZZX4428 	2	19950810	G	8530	73806	PUSH ROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					NR 1 CYL INT	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	6141Q					15285164	L2242115			ENGINE LOW STATIC. FOUND PUSH ROD WITH BOTH ENDS LOOSE AND TUBE MUSHROOMED. REPLACED PUSH ROD. INSPECTED ALL OTHER FO	R PROPER ADJUSTMENT - OK.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995090800133	19950908	00133		1995	9	8	95ZZZX4429 	4	19950816	G	6113	07526371	BULKHEAD 			CESSNA	182 	182L 	2072726	CE 										SPINNER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	42072	4354 				18258844				DURING ANNUAL INSPECTION OF AIRCRAFT, NOTED WHAT APPEARED TO BE VERY SMALL CRACKS RADIATING FROM PROP SPINNER BULKHEAD F	ASTENER HOLES. CRACKS VERY SMALL. CONFIRMED USING EDDY CURRENT INSPECTION AND ZYGLO. SUBMITTER SUGGESTS CLOSE INSPECT	ION OF THIS AREA. NO REPAIRS APPROVED. PART REPLACED WITH NEW PART.				1	H	7	1 	3O			NT	3A13 					 
1995090800134	19950908	00134	EA 	1995	9	8	95ZZZX4430 	2	19950821	G	7414	10682016	GEAR ASSY 		D6LN3000 	CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540J3C5 	41532	EA 					LT MAG	TEETH BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	1680R		244 		4092093	R18200512	RL2479940A			LEFT MAGNETO WAS REPORTED INOPERATIVE. FOUND APPROXIMATELY ONE-THIRD OF THE LEFT DISTRIBUTION GEAR TEETH MISSING. BROK	EN TEETH WERE SCATTERED THROUGHOUT THE MAGNETO. COULD HAVE DAMAGED THE RT PORTION OF THE MAGNETO. CAUSE IS UNKNOWN. N	O GEAR HOLDING DEVICE HAD BEEN USED SINCE MAG WAS PLACED IN SERVICE. SUBMITTER SUGGESTS THIS IS AN INHERENT DESIGN PROB	LEM.			1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1995090800135	19950908	00135	SO 	1995	9	8	95ZZZX4431 	2	19950816	G	8530	642068CP	CYLINDER 			CESSNA	182 	182L 	2072726	CE 	CONT 	O470 	O470R 	17026	SO 					CYL EXH VLV AREA	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	42072		1307 			18258844	1915477R			CYLINDER SHOWED LOW COMPRESSION. DETAILED INSPECTION REVEALED CRACK IN EXHAUST VALVE AREA ON HEAD NEAR VALVE EXHAUST PO	RT. CYLINDER WAS PREVIOUSLY WELDED IN THIS AREA. CYLINDER SCRAPPED. EXCHANGE UNIT INSTALLED. NO WAY OF KNOWING TIME 	SINCE NEW ON THIS CYLINDER. CYLINDER CHROME PLATED. SUBMITTER SUGGESTS RETIREMENT LIFE BE ESTABLISHED ON CYLINDERS AND	 TIMES TRACKED AND DATA PLATES INSTALLED.			1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995090800136	19950908	00136	SO 	1995	9	8	95ZZZX4432 	2	19950801	G	8530	SA63624210	VALVE GUIDE 		639272CD 	CESSNA	206 	U206G 	2073356	CE 	CONT 	O520 	IO520F 	17032	SO 					NR 6 CYL EXH	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	735ER		300 		A0916	U20604909	15961270F			INSPECTION FOUND EXHAUST VALVE GUIDE EXCESSIVELY LOOSE IN CYLINDER.						1	H	7	1 	3O	3	O		A4CE 	E5CE				 
1995090800137	19950908	00137		1995	9	8	95ZZZX4434 	3	19950817	G	6140	570011518	LINE 			CESSNA	441 	441 	2076020	CE 										BETA SWITCH	CRACKED 	B		A	WTXR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	2628M	4327 	1574 			4410151				AIRCRAFT WAS PULLED INTO HANGAR FOR MAINTENANCE. TECHNICIAN NOTICED OIL RUNNING OUT OF LT ENGINE COWLING. AFTER REMOVI	NG COWLING, FOUND LINE FROM UNFEATHERING PUMP TO NTS/BETA SWITCH CRACKED ALL THE WAY AROUND AT THE FERREL FOR THE 'B' NU	T AT THE MANIFOLD. (THIS IS A CESSNA SUPPLIED LINE). INSTALLED NEW LINE, GROUND RAN, LEAK CHECKED OK. SUBMITTER SUGGE	STS MANDITORY REPLACMENT AT ENGINE OVERHAUL. LINE IS MADE OF STAINLESS STEEL TUBING.			1	L	7	2 	3T			RT	A28CE 					 
1995090800138	19950908	00138	CE 	1995	9	8	95ZZZX4435 	1	19950726	G	5320	5044002870	STIFFENER 			BEECH 	90 	C90 	1152913	CE 										ELEV HINGE BRKT	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	4095S	6198 				LJ655				DURING A PRIMARY INSPECTION, A CRACK WAS DETECTED IN THE RT OUTBOARD AFT BULKHEAD STIFFENER AT THE LOWER BOLT HOLE FOR T	HE RT ELEVATOR INBOARD HINGE BRACKET. AD NOTE 77-22-01, PARA B-3, HAD BEEN COMPLETED 297 HRS PRIOR.					1	L	7	2 	3T				3A20 					 
1995090800139	19950908	00139	CE 	1995	9	8	95ZZZX4436 	1	19950722	G	3246	LM501310	BEARING CUP 	PARKERHANFIN	16294 	CESSNA	441 	441 	2076020	CE 										OTBD WHEEL HALF	LOOSE 	B			RTAR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	300NK					4410318				WHEN CLEANING BEARING DURING NORMAL INSPECTION, FOUND BEARING CUP LOOSE IN WHEEL HALF. 'MIKED' AND FOUND A .005 INCH 'L	OOSE' FIT. SHOULD BE AN INTERFERENCE FIT. REPLACED WHEEL HALF. (STC WHEEL/BRAKE ASSY).					1	L	7	2 	3T			RT	A28CE 					 
1995090800141	19950908	00141	EU 	1995	9	8	95ZZZX4438 	1	19950817	G	3260	D220733	DOWNLOCK SWITCH 			AMD 	FALC50	FALCON50MYST	2730106	EU 										NLG	DEFECTIVE 	D				A				UNSCHED LANDING 				N			FALSE WARNING 			CL	CLIMB 	1			GL	03	75W	3462 				152				DURING GEAR RETRACTION AFTER TAKEOFF, CREW DID NOT GET PROPER INDICATION OF 'INTRANSIT'. RETURNED AND REPLACED NLG DOWN	LOCK SWITCH AND OPS CHECKED ON JACKS. SYSTEM WORKED NORMAL.					2	L	7	3 	4F				A46EU 					 
1995090800143	19950908	00143		1995	9	8	95ZZZX4440 	4	19950716	G	2210	4034300	SWITCH 			LEAR 	35 	35A 	5170602	CE 										4-WAY TRIM	FAULTY 	B			TJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	240B					240				INTERMITTENTLY, THE PILOTS 4-WAY TRIM SWITCH WOULD FAIL WITH AUTOPILOT ENGAGED AND WOULD CAUSE TRIM FOR AUTOPILOT TO TRI	M PITCH UP, DISCONNECTING ANY OTHER PITCH MODES AND TRIM FULL NOSE UP ATTITUDE IF AUTOPILOT WAS NOT DISCONNECTED. THE C	AUSE IS APPARENTLY THE SWITCH PHYSICALLY BROKEN INTERNALLY.				2	L	7	2 	4F				A10CE 					 
1995090800144	19950908	00144		1995	9	8	95ZZZX4441 	4	19950727	G	2210		SLIP CLUTCH 	ARC 	462302811 	CESSNA	441 	441 	2076020	CE 										AUTOPILOT	DEFECTIVE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	74BY				1216	4410039				THE ROLL SERVO MOUNT CLUTCH SLIP SETTING IS 28 POUNDS. IT WOULD NOT SLIP AT 70 POUNDS. DIRT AND POSSIBLE OIL OVER YEAR	S SET UP CLUTCH. LOSS OF FLIGHT CONTROL IS POSSIBLE. SUBMITTER RECOMMENDS PERIODIC INSPECTIONS OF ALL 1,000 AUTOPILOT 	SLIP CLUTCHES. NOTE: CLUTCH SLIP DISCS WERE REPLACED FOR REPAIR.				1	L	7	2 	3T			RT	A28CE 					 
1995090800146	19950908	00146	EA 	1995	9	8	95ZZZX4443 	1	19950804	G	3242	164306153	BRAKE DISC 	WIPLINEINC 	6000 	DHAV 	DHC2 	DHC2MK1 	2800102	EA 										LT MLG	CORRODED 	B			NZBR	K				NONE 				O			OTHER 			LD	LANDING 	1			AL	05	2738G	416 			60137	1511				DHC-2/MK-I WITH WIPLINE 6000 AMPHIBIOUS FLOATS. PILOT REPORTED A 'CLUNK' SOUND FROM THE LEFT MAIN LANDING GEAR AFTER LA	NDING AND APPLYING BRAKES. THE MAINTENANCE INSPECTION REVEALED THE INBD BRAKE DISC SHEARED AT THE WELD DUE TO CORROSION	 AND THE INBOARD BRAKE CALIPER HAD BROKEN AT THE UPPER GUIDE PIN. BOTH LEFT MAIN LANDING GEAR BRAKE DISC AND INBOARD CA	LIPER WERE CHANGED. THIS IS A COMMON PROBLEM WITH THE WELDED TYPE BRAKE DISC COMPOUND BY SALT WATER OPERATIONS. RECOMM	END A FRESH WATER RINSE OF THE AIRCRAFT, ESPECIALLY THE LANDING GEAR AREA, AT THE END OF THE FLYING DAY. ALSO, ANNUAL R	EPLACEMENT OF BRAKE DISC. PART TT: 416.0 HRS/14 MONTHS.	1	H	7	1 	3R				A806 					 
1995090800147	19950908	00147	SW 	1995	9	8	95ZZZX4444 	1	19950721	G	5321	212030188001	FLOOR PANEL 			BELL 	212 	212 	1181420	SW 										FUSELAGE LT OTBD	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2FOR					30818				WHILE PERFORMING A SHEET METAL INSPECTION, FOUND SKIN CORRODED AND SEPARATED AROUND PERIMETER OF FLOOR PANEL. INADEQUAT	E (PRO-SEAL) AROUND PERIMETER OF PART.					1	G	7	1 	4U				H4SW 					 
1995090800148	19950908	00148	SW 	1995	9	8	95ZZZX4445 	1	19950721	G	5321	H2120301882	FLOOR PANEL 			BELL 	212 	212 	1181420	SW 										FUSELAGE RT OTBD	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2FOR				12278	30818				WHILE PERFORMING A SHEET METAL INSPECTION, FOUND SKIN CORRODED AND SEPARATED AROUND PERIMETER OF FLOOR PANEL. INADEQUAT	E (PRO-SEAL) AROUND PERIMETER OF PART.					1	G	7	1 	4U				H4SW 					 
1995090800149	19950908	00149	SW 	1995	9	8	95ZZZX4446 	1	19950721	G	5321	205031257067	FLOOR PANEL 			BELL 	212 	212 	1181420	SW 										LT FUEL CELL	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2FOR				13634	30818				WHILE PERFORMING A SHEET METAL INSPECTION, FOUND SKIN CORRODED AND SEPARATED AROUND PERIMETER OF LT CELL FLOOR PANEL. I	NADEQUATE (PRO-SEAL) AROUND PERIMETER OF PART.					1	G	7	1 	4U				H4SW 					 
1995090800150	19950908	00150	SW 	1995	9	8	95ZZZX4447 	1	19950721	G	5321	205032147079	FLOOR PANEL 			BELL 	212 	212 	1181420	SW 										FUSELAGE RT AFT	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2FOR				B52CHG1	30818				WHILE PERFORMING A SHEET METAL INSPECTION, FOUND SKIN CORRODED AND SEPARATED AROUND PERIMETER OF FLOOR PANEL. INADEQUAT	E (PRO-SEAL) AROUND PERIMETER OF PART.					1	G	7	1 	4U				H4SW 					 
1995090800151	19950908	00151	SW 	1995	9	8	95ZZZX4448 	1	19950807	G	6730	C4266311	CYLINDER HOUSING		206076062003	BELL 	206 	206L1 	1182107	SW 										MAIN ROTOR SERVO	MISMANUFACTURED 	B			ALGR	K				NONE 				L	W		NO TEST 	INADEQUATE Q C 		IN	INSP/MAINT 	1			SW	03					RH636312					ASSEMBLED SERVO SN RH-0827 FOR TESTING. SERVO FAILED MANUAL OPERATION TEST, PAGE 23, STEP 1, MANUFACTURER MM. MANUAL O	PERATION TEST STATES, 'THE FORCE REQUIRED AT INPUT LEVER TO START MOVING THE ACTUATOR AND MANUALLY CYCLE IT SHALL NOT EX	CEED 26 POUNDS.' ONE-HUNDRED POUNDS OF FORCE WAS REQUIRED TO MOVE THE ACTUATOR. UPON REMOVAL OF THE CYLINDER EXTENSION	 NOTED THE CYLINDER EXTENSION WAS BEING CONTACTED BY THE PISTON ON THE LEFT SIDE. AFTER PRECISE MEASURING, THE PISTON B	ORE WAS FOUND TO BE OFF-CENTER.		1	G	7	1 	3U				H2SW 					 
1995090800152	19950908	00152	SW 	1995	9	8	95ZZZX4449 	1	19950810	G	3710		PUMP 			MOONEY	M20 	M20R 	5870225	SW 										STANDBY VACUUM	MAKING METAL 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	1066U	240 				290005				SPLINE GEAR ON ENGINE MOUNTED STANDBY VACUUM PUMP MAKING METAL. SEVERE WEAR PUSHING METAL OFF EDGE OF SPLINE TEETH. NO	 LUBRICATION. FREE TO FALL INTO SUMP. LUBED WITH MOLY B. 290 HRS TT. MOONEY SM DOES NOT CALL FOR LUBRICATION.					1	L	7	1 	3O			RT	2A3 					 
1995090800153	19950908	00153	WP 	1995	9	8	95ZZZX4450 	1	19950712	G	6710	269A7117	LINK 		269A993 	HUGHES	269 	269A 	4470402	WP 										RT CYCLIC	BINDING 	D	S	A		K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			CE	01	1040S					560534				NOTED THAT THERE WERE OCCASIONAL RESTRICTIONS TO THE LATERAL MOVEMENT OF CYCLIC CONTROL. FURTHER DISCOVERED TWO WASHERS	 (PN AN960-416) ON BOTH SIDES OF LINK (PN 269A7117) WERE BECOMING JAMMED IN THE SLOT BECAUSE OF A WIDENING OF THE SLOT F	ROM WEAR. SUBMITTER SUGGESTED THESE TWO WASHERS BE REPLACED WITH DIFFERENT WASHERS (PN AN970-4). THESE WASHERS ARE SLI	GHTLY SMALLER IN OUTSIDE DIAMETER AND THICKER, BUT ARE STILL LARGER IN DIAMETER THAN SLOT ON THE LINK. SUBMITTER IS A M	ECHANIC WITH AN INSPECTION AUTHORIZATION, AND APPROVED THIS CHANGE AS A MINOR ALTERATION WITH A MAINTENANCE LOG BOOK ENT	RY. SUBMITTER STATED THIS PROBLEM COULD HAVE SERIOUS CONSEQUENCES SHOULD CYCLIC LATERAL MOVEMENT BECOME JAMMED.	1	G	7	1 	3O				4H12 					 
1995090800158	19950908	00158	NE 	1995	9	8	95ZZZX4451 	2	19950515	G	7510	3029297	TUBE 			CESSNA	500 	S550 	2076607	CE 	PWA 	JT15 	JT15D4 	52112	NE 					RT ENG ANTI-ICE	CHAFED 	B		A	CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	92QS	7765 				S5500092	PCE102288			DURING INSPECTION, FOUND T-SENSOR ANTI-ICE TUBE CHAFING ON BLEED AIR CROSS-OVER TUBE. TUBE WAS CHAFED HALF WAY THROUGH 	WALL THICKNESS. CLOSER INSPECTION NEEDED.					1	L	7	2 	4F	4	F	RT	A22CE 	E1NE				 
1995090800159	19950908	00159	WP 	1995	9	8	95ZZZX4452 	2	19950522	G	7320	625501038	LINE 			CESSNA	650 	650 	2076802	CE 	GARRTT	TFE731	TFE7313 	01518	WP 					LT ENG P2T2	CRACKED 	B			CWQR	K				NONE 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			GL	05	370TG					6500070	87317L			THE CREW INDICATED THE LEFT ENGINE WOULD NOT MAKE POWER AT CRUISE ALTITUDE. UPON INVESTIGATION, FOUND THE P2T2 SENSE LI	NE WAS CRACKED AT THE PROBE. SUBMITTER RECOMMENDS THE LINE BE REPLACED WITH A SUITABLE FLEXIBLE LINE. THIS WILL ELIMIN	ATE THE POSSIBILITY OF CRACKING DUE TO VIBRATION.				2	L	7	2 	4F	4	F		A9NM 	E6WE				 
1995090800160	19950908	00160	CE 	1995	9	8	95ZZZX4453 	1	19950522	G	5543	PN3A	BEARING 			CESSNA	500 	S550 	2076607	CE 										RUD LT/RT TAB	CORRODED 	B			CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	106QS	8557 				S5500106				DURING INSPECTION FOUND RUDDER, LEFT AND RIGHT TRIM TAB BEARINGS, CORRODED AND WORN. TKS ANTI-ICE FLUID MOST LIKELY CAU	SE OF CORROSION. SUBMITTER STATES THIS IS A COMMON PROBLEM. THE BEARINGS SHOULD BE MORE TKS/CORROSION RESISTANT.					1	L	7	2 	4F			RT	A22CE 					 
1995090800162	19950908	00162	EU 	1995	9	8	95ZZZX4455 	1	19950726	G	2435	23065181	STARTER 	LUCAS 		AMD 	FALC10	FALCON10 	2730101	EU 										START/GENERATOR	BEARING FAILED 	B			GR5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	174B		578 			142				FORWARD BEARING FAILED DUE TO SUSPECTED LACK OF LUBRICATION. THIS IS 3RD BEARING FAILURE ON THIS PART NUMBER STARTER/GE	NERATOR. CHAPTER 5 REQUIREMENT FOR BEARING REPLACEMENT IS 900 HOURS. WERE CHANGING AT 600 HOURS, BUT WILL NOW CHANGE A	T 500 HOURS.				2	L	7	2 	4F				A33EU 					 
1995090800166	19950908	00166	CE 	1995	9	8	95ZZZX4459 	1	19950418	G	5260	651900948	STEP 			CESSNA	500 	S550 	2076607	CE 										DETENT ARM	ARM BROKEN 	B			CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	98QS	7855 				S5500098				FOUND DETENT ARM BROKEN OFF ON UPPER STEP ASSEMBLY. SUBMITTER SUGGESTS ROUGH HANDLING OR MISALIGNMENT SUSPECT CAUSE. S	TRONGER DETENT ARM NEEDED.					1	L	7	2 	4F			RT	A22CE 					 
1995090800167	19950908	00167	CE 	1995	9	8	95ZZZX4460 	1	19950418	G	3297	G32H22	WIRE 			CESSNA	500 	S550 	2076607	CE 										FLAP COVE	DEFECTIVE 	B			CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	98QS	7855 				S5500098				DURING INSPECTION, RIGHT MAIN GEAR WOULD NOT EXTEND COMPLETELY DURING OPERATIONAL CHECK. FOUND WIRE NR G32H22 DEFECTIVE	 IN FLAP COVE. REPLACED WIRE. SUBMITTER STATED PROBLEMS WITH WIRING IN FLAP COVE AREA COMMON, BETTER WIRING PROTECTION	 NEEDED.				1	L	7	2 	4F			RT	A22CE 					 
1995090800171	19950908	00171	CE 	1995	9	8	95ZZZX4464 	1	19950801	G	3520	17400630	MASK 			CESSNA	500 	S550 	2076607	CE 										CABIN	TORN 	B			CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	211QS	5798 				S5500011				DURING PHASE 1 INSPECTION, FOUND 3 CABIN OXYGEN MASKS WITH TORN FACE MASK. WHERE THE RUBBER FACE MASK MEETS THE PLASTIC	 NOSE PIECE, APPEARS TO BE A WEAK AREA PRONE TO TEARING. SUBMITTER STATED THIS CONDITION IS COMMON ON THIS TYPE OF MASK	.				1	L	7	2 	4F			RT	A22CE 					 
1995090800172	19950908	00172	CE 	1995	9	8	95ZZZX4465 	1	19950817	G	2820	65235537	TUBE 			CESSNA	500 	550 	2076604	CE 										FUEL TANK	CHAFED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	13	12549	6421 				5500501				DURING TROUBLESHOOTING OF FUEL LEVEL LOW LIGHT, LEFT SIDE, FOUND BOOST PUMP WIRE HARNESS HAD CHAFED THROUGH APPROXIMATEL	Y 20-25 PERCENT OF WALL THICKNESS OF ALUMINUM TUBE, PN 6526355-37 (FIG. 01, ITEM 10, CHAPTER 28-20-00 IPB), AND INSULATI	ON OF HARNESS WORN THROUGH SLIGHTLY TO SHIELDING. REPLACED TUBE AND SEALED INSULATION PER CESSNA TECH REP. ACFT TT: 6	421.1 HRS.			1	L	7	2 	4F				A22CE 					 
1995090800173	19950908	00173	CE 	1995	9	8	95ZZZX4466 	1	19950821	G	2742	49701009	ACTUATOR 			CESSNA	650 	650 	2076802	CE 										PITCH TRIM	FAILED 	B			IW1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	118CD				187	6500118				PITCH TRIM ACTUATOR, SN 187, FAILED 16 FLIGHT HOURS AFTER INSTALLATION. SN 186 WAS INSTALLED IN ITS PLACE, AND IT FAILE	D ON THE FOLLOWING DAY (EXACT NUMBER OF HOURS IN USE AFTER INSTALLATION UNKNOWN AT THIS STATION).					2	L	7	2 	4F				A9NM 					 
1995090800174	19950908	00174	CE 	1995	9	8	95ZZZX4467 	1	19950821	G	2742	49701009	ACTUATOR 			CESSNA	650 	650 	2076802	CE 										PITCH TRIM	FAILED 	B			IW1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	118CD				186	6500118				PITCH TRIM ACTUATOR, SN 187, FAILED 16 FLIGHT HOURS AFTER INSTALLATION. SN 186 WAS INSTALLED IN ITS PLACE, AND IT FAILE	D ON THE FOLLOWING DAY (EXACT NUMBER OF HOURS IN USE AFTER INSTALLATION UNKNOWN AT THIS STATION).					2	L	7	2 	4F				A9NM 					 
1995090800175	19950908	00175	SO 	1995	9	8	95ZZZX4468 	1	19950712	G	7500	12034290025	VENT TUBE 			EMB 	120 	EMB120RT 		SO 										ENGINE VENT	CRACKED 	B			D2TR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25										IMPROPER REPAIR. ENGINE VENT TUBE WELDED WITH UNKNOWN TYPE OF ROD WHICH CRACKED AROUND THE WELD. (IMPROPER REPAIR PROC	EDURE.)					2	L	7	2 	4T			RT	A31SO 					 
1995090800176	19950908	00176	SO 	1995	9	8	95ZZZX4469 	1	19950811	G	2760	2R10415	RESTRICTOR 			LKHEED	1329 	132923E 	5263116	SO 										SPEED BRAKE	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	511TD	3143 			2128	5145				SPEED BRAKE SLOW TO EXTEND (90 SECONDS), RETRACTS NORMALLY IN 6 SECONDS. FOUND F.O.D. IN RESTRICTOR. POSSIBLY BELIEVE 	IT TO BE REMNANTS OF AN INTERNAL FILTER THAT WAS BUILT IN THE RESTRICTOR. THE F.O.D. LOOKS LIKE A 2 INCH BY .25 INCH OV	AL ALUMINUM PELLET.				2	L	7	4 	4J				2A15 					 
1995090800177	19950908	00177	CE 	1995	9	8	95ZZZX4470 	1	19950719	G	2910	551701089	LINE 			CESSNA	500 	560CESSNA 	2076750	CE 										GEAR RETRACT	CHAFED 	B		A	IY2R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	15	44GT	410 				5600252				HYDRAULIC FLUID NOTICED LEAKING FROM THE BELLY DURING THE OPERATOR'S PRE-FLIGHT. AFT CABIN FLOOR REMOVED TO LOCATE THE 	LEAK. AILERON CABLE RUNNING FORWARD FROM AILERON SECTOR ON RT SIDE HAD CHAFED INTO THE GEAR RETRACT LINE RUNNING FORWAR	D IN THIS AREA. RECOMMEND A ONE-TIME INSPECTION IN THIS AREA AND PARTICULAR ATTENTION TO THIS AREA DURING THE PHASE 5 I	NSPECTION.			2	L	7	2 	4F			RT	A22CE 					 
1995090800179	19950908	00179	CE 	1995	9	8	95ZZZX4472 	1	19950109	G	3010	PU306DT41	PROPORTION UNIT 			CESSNA	500 	S550 	2076607	CE 										ANTI-ICE SYSTEM	MALFUNCTION 	B			CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	151QS	5578 			D5387	S5500151				CREW BELIEVED TAIL TKS ANTI-ICE SYSTEM NOT OPERATING PROPERLY. FOUND RIGHT INBOARD HORIZONTAL TAIL TKS PANEL DRY. FOUN	D TKS PROPORTIONING UNIT DEFECTIVE. INTERNAL BLOCKAGE SUSPECT CAUSE OF DEFECT.					1	L	7	2 	4F			RT	A22CE 					 
1995090800180	19950908	00180	CE 	1995	9	8	95ZZZX4473 	1	19950816	G	5320	07106082	REINFORCEMENT 		0710600 	CESSNA	182 	182L 	2072726	CE 										FS 65.33	CORRODED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	42072	4354 				18258844				ANNUAL INSPECTION FOUND SEVERE CORROSION AT STA 65.33 BELOW FLOORBOARDS. STEEL REINFORCEMENT HAD CORRODED BADLY. SURRO	UNDING STRUCTURE STARTED TO CORRODE. REINFORCEMENT IS MAJOR STRUCTURE FOR LANDING GEAR BULKHEAD, PN 0710600, AND IS FAS	TENED WITH HI-SHEAR FASTENERS. REINFORCEMENT REPLACED WITH NEW. SURROUNDING STRUCTURE TREATED AND PRIMED. NUMEROUS ST	RUCTURAL PARTS HAD TO BE UNRIVETED TO AFFECT REPAIR. REPAIR WAS EXPENSIVE. SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS	 AREA ON OLDER AIRCRAFT.		1	H	7	1 	3O			NT	3A13 					 
1995090800181	19950908	00181	CE 	1995	9	8	95ZZZX4474 	1	19950809	G	5541	143100346	SPAR 		143100058 	CESSNA	337 	337G 	2075730	CE 										RUDDER	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	72086	2875 				33701518				AT ANNUAL, FOUND RIGHT RUDDER SPAR BROKEN AT BALANCE WEIGHT RIB ATTACH.						1	H	7	2 	3O				A6CE 					 
1995090800182	19950908	00182	CE 	1995	9	8	95ZZZX4475 	1	19950801	G	7900		BREATHER TUBE 			CESSNA	172 	172M 	2072418	CE 										CRANKCASE	MALFUNCTION 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	9608H					17266261				CRANKCASE BREATHER TUBE MALFUNCTION. STOCK 172M BREATHER TUBE HAD SLIPPED DOWN IN CLAMPS. LOWER CLAMP COVERED 'WHISTLE	 HOLE'. THIS COULD RESULT IN BREATHER TUBE BLOCKAGE WITH ICE DURING FLIGHT AT LOW OUTSIDE AIR TEMPERATURE. SAME PROBLE	M WAS ADDRESSED IN AD 82-07-02. (THIS AD WAS FOR MISSING WHISTLE HOLE IN STC APPROVED EQUIPMENT.) FIX WAS TO REPLACE B	REATHER TUBE CLAMPS. PART TOTAL TIME: 18 YEARS, 6,000 HOURS.			1	H	7	1 	3O			NT	3A12 					 
1995090800183	19950908	00183	SO 	1995	9	8	95ZZZX4476 	1	19950720	G	5341		SPAR ATTACH 			PIPER 	PA32 	PA32RT300 	7103215	SO 										WING	CORRODED 	B			AHVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	2578M					32RT7885005				DURING ANNUAL INSPECTION, COMPLIANCE WITH PIPER SB 977, INSPECTION OF REAR SPAR ATTACH FITTINGS IN THE CABIN FOR CORROSI	ON, AND FOUND THIS AREA SEVERELY CORRODED. SB IS APPLICABLE TO ALL PA28, PA32, PA34, AND PA44 SERIES OF AIRCRAFT. ALL 	INTERIOR AND FIBERGLASS INSULATION WAS REMOVED FROM THE WINDOWS DOWNWARD FOR FURTHER INSPECTION. THE FORWARD SPAR ATTAC	HMENT POINTS WERE ALSO VERY CORRODED. AS LIKE THE AFT AREA, THE FRONT IS ALSO A COMBINATION OF STEEL AND ALUMINUM. SB 	977 DOES NOT INCLUDE INSPECTION OF FORWARD AREA. THIS FRONT AREA IS NOT ABLE TO BE INSPECTED UNLESS INTERIOR SIDE PANEL	S AND FIBERGLASS INSULATION REMOVED. ALSO FOUND WERE 2 OTBD WING SPAR ATTACHMENT BOLTS ON LT SIDE SEVERELY CORRODED.	1	L	7	1 	3O				A3SO 					 
1995090800184	19950908	00184	CE 	1995	9	8	95ZZZX4477 	1	19950810	G	3230	25410802	RETRACTION ARM 			CESSNA	303 	T303 	2073820	CE 										MLG	CRACKED 	B	S	A	BWRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	303ND					T30300099				WHILE PERFORMING ANNUAL INSPECTION, FOUND RT MAIN GEAR RETRACTION ARM BUSHING WORN AND LOOSE. REMOVED ARM AND CLEANED P	ART. FOUND .100 INCH CRACK PROTRUDING FROM UPPER TOOLING HOLE. NOTE: MEB85-17, REV 1, WAS COMPLIED WITH APPROXIMATELY	 1,400 HOURS PREVIOUSLY AND, AT THAT TIME, SK303-30A KIT WAS INSTALLED.				1	L	7	2 	3O				A34CE 					 
1995090800185	19950908	00185	NE 	1995	9	8	95ZZZX4478 	3	19950130	G	6111	7863504	BLADE 													HAMSTD	5500	65500F1 	NE 	SHANK BUTT AREA	DAMAGED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		3603 	1539 		861521					SUBJECT BLADE RECEIVED WITH SCORING DAMAGE AROUND THE OUTSIDE DIAMETER OF THE BUTT AREA. DAMAGE EXISTS 360 DEGREES AROU	ND THE BUTT AND IS APPROXIMATELY .015 INCH DEEP BY .020 INCH HIGH. DAMAGE APPEARS TO HAVE BEEN CAUSED BY RESIDUAL SHOT 	PEEN BALLS WHICH WERE TRAPPED INSIDE THE BLADE PIN.														6	C	P13NE	 
1995090800186	19950908	00186	NE 	1995	9	8	95ZZZX4479 	3	19950130	G	6111	7863504	BLADE 													HAMSTD	5500	65500F1 	NE 	SHANK BUTT AREA	DAMAGED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		3481 			866867					SUBJECT BLADE WAS RECEIVED WITH SCORING DAMAGE AROUND THE OUTSIDE DIAMETER OF THE BUTT AREA. DAMAGE EXISTS 360 DEGREES 	AROUND THE BUTT AND IS APPROXIMATELY .015 INCH DEEP BY .015 INCH HIGH. DAMAGE APPEARS TO HAVE BEEN CAUSED BY RESIDUAL S	HOT PEEN BALLS WHICH WERE TRAPPED INSIDE THE BLADE PIN.														6	C	P13NE	 
1995090800187	19950908	00187	CE 	1995	9	8	95ZZZX4480 	1	19950522	G	3213	50411063	RING PACK 			CESSNA	421 	421C 	2076016	CE 										RT MLG STRUT	WORN 	B			CWQR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	05	3968G	4866 				421C0422				RIGHT MAIN STRUT LEAKING HYDRAULIC FLUID. DISASSEMBLED STRUT AND FOUND RING PACK SUPPORT INNER BEARING MATERIAL LOOSE, 	WORN AND TORN. REPLACED RING PACK SUPPORT AND O-RINGS. NORMAL WEAR AND POSSIBLE ROUGH GEAR HANDLING.					1	L	7	2 	3O				A7CE 					 
1995090800189	19950908	00189	EU 	1995	9	8	95ZZZX4482 	1	19950815	G	2720	T67B45219	CONTROL CABLE 			SLNSBY	T67 	T67M260 	8323006	EU 										RUDDER	FRAYED 	B		A	UNER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	7020D	697 				920625				DURING AN ANNUAL INSPECTION, THE RT RUDDER CABLE WAS FOUND FRAYED BY AFT PULLEY. FRAYED AREA RUNS BACK AND FORTH ON PUL	LEY. NO RECOMMENDATION AT THIS TIME. SLINGSBY IPC, CHAPTER 19, FIGURE 9, ITEM NR 24.					1	L	7	1 	3O			NT	A73EU 					 
1995090800190	19950908	00190	EU 	1995	9	8	95ZZZX4483 	1	19950815	G	7931	12634041	SENSOR 			SLNSBY	T67 	T67M260 	8323006	EU 										OIL PRESSURE	DEFECTIVE 	B			UNER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	3037T	426 				920640				OIL PRESSURE SENDING UNIT FAILING TO GIVE CORRECT READINGS. SUBMITTER RECOMMENDS TRYING A DIFFERENT MANUFACTURER. SLIN	GSBY IPC, CHAPTER 55, FIGURE 5, ITEM NR 3.					1	L	7	1 	3O			NT	A73EU 					 
1995090800191	19950908	00191	CE 	1995	9	8	95ZZZX4484 	1	19950816	G	7810	K1250860203	PIPE 			CESSNA	210 	T210N 	2073456	CE 										CYLS 2,4,6, EXH	MISINSTALLED 	B	S		CS3R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	17	5310A					21063362				WHILE PERFORMING A PRESSURE TEST OF THE EXHAUST IAW AD 71-09-07, NOTED EXCESSIVE LEAK AT THE CLAMP AFT OF THE NR 2 CYLIN	DER BELOW THE ALTERNATOR AND ENGINE DRIVEN FUEL PUMP. ONCE THE CLAMP WAS REMOVED, IT WAS NOTED THAT BOTH EXHAUST PIPES 	WERE THE SAME SIZE AND WOULD NOT SLIP-FIT INTO EACH OTHER. THE PIPES, PN 12508690-90, AND THE KNISLEY FAA-PMA'ED PIPE, 	PN K1250860-203, WERE NEVER INSTALLED CORRECTLY AND THE EXHAUST LEAK WAS BLOWING DIRECTLY ON THE ENGINE DRIVEN FUEL PUMP	. THIS WAS NOTED BY THE ANEROID HOUSING BEING STAINED BY THE EXHAUST.		1	H	7	1 	3O				3A21 					 
1995090800192	19950908	00192	EA 	1995	9	8	95ZZZX4485 	2	19950624	G	8510		IDLER SHAFT 			PIPER 	PA32 	PA32301 	7103207	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					PROP GOVERNOR	SCREW MISSING 	H	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	17	801MT	1818 				328306030	L2170548A			WHILE PERFORMING A ROUTINE OIL CHANGE ON A PIPER PA32301, A 10-32 SET SCREW WAS FOUND IN THE OIL SUMP SUCTION SCREEN. T	HE SCREW HAD OBVIOUSLY BEEN SMASHED AND WAS IN TWO PIECES. INVESTIGATION FOUND THE ONLY 10-32 SET SCREW IN THE IO-540 S	ERIES ENGINES WAS USED TO HOLD THE PROP GOVERNOR IDLER GEAR SHAFT IN THE FRONT OF THE CASE. AFTER REMOVING THE PROPELLE	R AND THE EXTERIOR CAP, PLACED A MAGNET ON THE IDLER SHAFT AND WAS ABLE TO NEARLY PULL IT OUT OF THE CASE. NOT KNOWING 	THE EXTENT OF DAMAGE INTERNALLY AND SINCE THE ENGINE WAS NEAR OVERHAUL TIME, THE OWNER OPTED TO REPLACE THE ENGINE WITH 	A FACTORY OVERHAULED ENGINE.	1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995090800193	19950908	00193		1995	9	8	95ZZZX4486 	4	19950714	G	3424	206070274101	INDICATOR 			BELL 	206 	206B 	1181511	SW 										COCKPIT	FAILED 	B			TU3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	303PD	816 			6072	4319				TURN AND SLIP INDICATOR GOT NOISEY, THEN QUIT WORKING.						1	G	7	1 	3U				H2SW 					 
1995090800194	19950908	00194	SW 	1995	9	8	95ZZZX4487 	1	19950714	G	7714	206075682109	INDICATOR 			BELL 	206 	206B 	1181511	SW 										ENG N1	DEFECTIVE 	B			TU3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	303PD	816 			0032	4319				N1 INDICATOR VERY ERRATIC NEEDLE (SMALL DIAL).						1	G	7	1 	3U				H2SW 					 
1995091500002	19950915	00002	EA 	1995	9	15	95ZZZX4488 	2	19950801	G	8520		CRANKSHAFT 			UNIVAR	108 	1082 	9230406	NM 	FRNKLN	6A4165	6A4165B3 	27025	EA 					REAR THROW	BROKE 	D				O				OTHER 				E	R	W	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	INADEQUATE Q C 	NR	NOT REPORTED 	1			EA	17	9619K	2778 	18 			2619	32076			CRANKSHAFT - REGROUND 18 HOURS EARLIER. AT OVERHAUL, BROKE AT REAR THROW WITH LOSS OF POWER. GRINDING MAY HAVE BEEN TH	E WORK OF AN AUTOSHOP WITH NO INTEREST IN FILLET RADIUS. ENGINE RAN SMOOTH UNTIL THEN. SECOND REPORTED BROKEN CRANKSHA	FT OF SAME TYPE.				1	H	7	1 	3O	3	O		A767 	E238				 
1995091500003	19950915	00003	NE 	1995	9	15	95ZZZX4489 	2	19950727	G	8530	399356	CYLINDER 			SCWZER	G164 	G164A 	3952704	EA 	PWA 	R1340 	R1340AN1 	52016	NE 					NR 4	FAILED 	G				A				UNSCHED LANDING 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			SW	11	6636Q					1694	P356716			CYLINDER HEAD HAD CRACKED ON THE EXHAUST ROCKER BOX ASSEMBLY AREA CAUSING ENGINE TO QUIT AND AIRCRAFT CRASHED.						1	Q	7	1 	3R	3	R		1A16 	5E2				 
1995091500004	19950915	00004	SO 	1995	9	15	95ZZZX4490 	1	19950727	G	3210	4027909	SIDE BRACE 			PIPER 	PA31 	PA31350 	7103110	SO 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	27329	4233 				317752150				WHILE COMPLYING WITH AD 88-05-05, DYE PENETRANT INSPECTION REVEALED CRACKED BRACE IN RADIUS OF PART AS SPELLED OUT IN AD	. CRACK COULD NOT BE SEEN WITH NAKED EYE OR MAGNIFICATION.					1	L	7	2 	3O				A20SO 					 
1995091500005	19950915	00005	SO 	1995	9	15	95ZZZX4491 	1	19950814	G	3213	6704014	TRUNNION 			PIPER 	PA34 	PA34200 	7103405	SO 										RT MLG	BOLT MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	1440T	3311 				347250310				DURING 100-HOUR INSPECTION, FOUND FORWARD TRUNNION FITTING HAD TOP RT BOLT MISSING, TOP LT AND BOTTOM RT BOLTS BENT AND 	LOOSE, AND 4TH BOLT LOOSE. PIPER SB 956 APPLIES TO THIS PROBLEM. COMPLIED WITH SB 956 ON ALL 4 TRUNNION FITITNGS.					1	L	7	2 	3O				A7SO 					 
1995091500006	19950915	00006	SO 	1995	9	15	95ZZZX4492 	2	19950720	G	8530		CYLINDER 								CONT 	O470 	O470U 	17026	SO 					EXHAUST SEAT	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01							467573			CYLINDER CRACKED TWO PLACES BETWEEN SPARK PLUG AND EXHAUST SEAT. EXHAUST SEAT CRACKED. CYLINDER CRACKED ALSO, THREE-QU	ARTERS AROUND. SUBMITTER RECOMMENDS CYLINDER TT SHOULD BE TRACKED AND CYLINDERS BE RETIRED AFTER 3 ENGINE T.B.O.'S. TH	IS IS A RECURRING PROBLEM WITH SECOND-RUN CYLINDERS. DO NOT SEE WITH FIRST-RUN CYLINDERS.									3	O			E273				 
1995091500007	19950915	00007	CE 	1995	9	15	95ZZZX4493 	1	19950727	G	5312	24110111	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RT MLG WELL	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	6418R	5118 				172RG0180				FOUND BULKHEAD WITH SEVERE CORROSION IN RT GEAR WELL WHERE LANDING GEAR PIVOT ATTACHES. RIVETS IN THIS LOCATION CORRODE	D AND SHEARED. EVIDENCE OF PLAY IN RT GEAR. COMPLETE BULKHEAD NEEDED REPLACEMENT. AIRCRAFT SPENT MOST OF ITS TIME IN 	SALT WATER ENVIRONMENT. ALSO, ENGINE EXHAUST FLOWS ACROSS THIS AREA. SUBMITTER SUGGESTS CLEAN AREA AND INSPECT THOROUG	HLY, ESPECIALLY IN CORROSIVE ENVIRONMENT.			1	H	7	1 	3O				3A17 					 
1995091500008	19950915	00008	EU 	1995	9	15	95ZZZX4494 	1	19950801	G	7931	12634041	SENSOR 			SLNSBY	T67 	T67M260 	8323006	EU 										OIL PRESSURE	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	7020D	685 				920625				OIL PRESSURE SENDING UNIT GIVES FALSE READINGS ON INSTRUMENT GAUGE. READINGS ARE ALSO DIFFERENT WHEN TESTING WHILE UNIT	 IS OFF THE ENGINE. SUBMITTER RECOMMENDS TRYING A DIFFERENT TYPE OIL PRESSURE SENDING UNIT.					1	L	7	1 	3O			NT	A73EU 					 
1995091500009	19950915	00009	GL 	1995	9	15	95ZZZX4495 	3	19950811	G	6110		PROPELLER 			CESSNA	421 	421B 	2076014	CE 						MCAULY	3AF34C	3AF34C92 	GL 	LOCK PLUG	MISOVERHAULED 	B			EBVR	K				NONE 				E	W		VIBRATION/BUFFET 	INADEQUATE Q C 		IN	INSP/MAINT 	1			GL	09	421CR					421B0224		746854		OWNER COMPLAINED OF PROPELLER VIBRATIONS. THE PROPELLER WAS REMOVED AND SENT TO OUR FACILITY FOR TRACK AND BALANCE CHECK	. FOUND BLADE ANGLE SPREAD .4 DEGREES. REMOVED CYLINDER TO INVESTIGATE AND FOUND OIL QUANTITY VERY LOW. REMOVED OIL A	ND FOUND PROPELLER ACTUATING PIN HOLES IMPROPERLY DRILLED. PISTON NOT MODIFIED PER SERVICE LETTER. EXPANSION LOCK PLUG	S DRILLED INCORRECTLY AND TWO RETENSION NUTS UNSERVICEABLE. THIS PROPELLER WAS RECENTLY OVERHAULED ACCORDING TO CUSTOME	R.		1	L	7	2 	3O				A7CE 		5	C	P22EA	 
1995091500010	19950915	00010	EA 	1995	9	15	95ZZZX4496 	2	19950815	G	8540	74996	IDLER GEAR 			CESSNA	172 	172 	2072402	CE 	LYC 	O320 	O320D2J 	41508	EA 					LT MAGNETO	TEETH MISSING 	D				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			CE	05	8450E					17272205	L1256839A			PILOT REPORTED BAD LT MAG DROP. LT MAG REMOVED AND VISUAL INSPECTION REVEALED MISSING TOOTH ON IDLER GEAR. ALL REMAINI	NG TEETH FOUND TO BE DISTORTED. IDLER GEAR BOSS ON CRANKCASE FOUND LOOSE. LT BOLT SAFETY BROKEN. RT HAD STUD WITH COT	TER PIN THROUGH NUT, HOWEVER, SHOULD HAVE BEEN BOLT WITH SAFETY WIRE. THE STUD APPEARS TO HAVE BACKED OUT NUT, COTTER P	IN AND ALL. PILOT OF A/C WENT TO OFF ON MAG SWITCH AND BACK ON AND NOTICED BACKFIRE. THIS AND IMPROPER INSTALLATION OF	 GEAR ARE SUSPECT TO THE FAILURE.		1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995091500011	19950915	00011	GL 	1995	9	15	95ZZZX4497 	3	19950824	G	6111		BLADE 			PIPER 	PA18 	PA18150 	7101828	SO 						MCAULY	1A175	1A175GM 	GL 	NR 2	BROKE 	G		A		A				UNSCHED LANDING 				E	D		VIBRATION/BUFFET 	INFLIGHT SEPARATION 		CR	CRUISE 	1			AL	03	3797Z	755 				187492		EC019		3.50 INCHES BROKE OFF NR 2 BLADE WHILE IN CRUISE FLIGHT. SUBMITTER STATED UNABLE TO DETERMINE CAUSE, NO VISIBLE NICKS. 	 FRACTURE APPEARED TO BE INSTANTANEOUS ACROSS THE FULL CHORD. NO ACCIDENT.					1	H	7	1 	3O				1A2 		5	N	P857	 
1995091500116	19950915	00116	SW 	1995	9	15	95ZZZX4505 	1	19950609	G	3340	A402AR	LIGHT 			BELL 	222 	222U 	1182140	SW 										ANTI-COLLISON	LENS CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	219HM	105 				47573				LIGHT CRACKED (LOWER ANTI-COLLISION LENS CRACKED). REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995091500257	19950915	00257	SO 	1995	9	15	95ZZZX4506 	2	19950821	G	8530		PUSH ROD 			BEECH 	55 	95B55B 		CE 	CONT 	O470 	IO470L 	17026	SO 					EXHAUST VALVE	BROKEN 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	09	527T					TC576				OIL LEAK TRACED TO BROKEN ROCKER BOSS AND ROCKER COVER. EXHAUST PUSH ROD BROKEN AND BENT. ENGINE MAY HAVE BEEN STARTED	 WITH STUCK EXHAUST VALVE SOME TIME IN PAST AND BENT PUSH ROD. PUSH ROD AND TUBE SHOWED SIGNS OF LONG TERM WEAR PRIOR T	O BREAKING.				1	L	7	2 	3O	3	O		3A16 	3E1				 
1995091500258	19950915	00258	EA 	1995	9	15	95ZZZX4507 	2	19950815	G	7414		BEARING 	BENDIX 	S200 	PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	IO540C4B5 	41532	EA 					MAG DRIVE	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	51ME					277854066				LEFT ENGINE WOULD NOT START. TROUBLESHOOT TO LEFT MAG. BEARINGS IN MAG WORN, CAM NOT ACTIVATING POINTS. WHEN REMOVING	 MAG, FOUND BEARING ON MAG DRIVE GEAR MISSING BALLS AND TEETH MISSING ON GEAR OR CHIPPED.					1	L	7	2 	3O	3	O		1A10 	1E4				 
1995091500260	19950915	00260	EU 	1995	9	15	95ZZZX4509 	1	19950824	G	5102	E3001	FABRIC 			CAMRON	MODELO	CAN 	1880203	EU 										BALLOON PANEL	MISMFG 	B			RB6R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	23										BLUE NYLON DURAFLIGHT FABRIC, PRE-CUT FOR AN 'A' SERIES 'K' PANEL, HAD 'RIP-STOP' IN ONLY ONE DIRECTION. CAMERON INV NR	 16526.					1	B	0	0 					B1EU 					 
1995091500261	19950915	00261	SO 	1995	9	15	95ZZZX4510 	2	19950801	G	8520	630826	BEARING 								CONT 	O520 	TSIO520R 	17040	SO 					CON ROD	WORN 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07		190 					269786R			ENGINE DISASSEMBLED AT 190 HRS TSO FOR INSP DUE TO PROP STRIKE. UNUSUAL WEAR ON ROD BEARINGS AND MAIN BEARINGS WAS OBSE	RVED. THE ROD BEARING WEAR WAS FOUND ONLY ON THE ROD-SIDE BEARINGS WHILE THE CAP-SIDE BEARINGS APPEAR NORMAL. ALL THE 	WORN BEARINGS SHOW HEAT STRESS DAMAGE. THE HEAT DAMAGE AND UNUSUAL WEAR ARE VERY ABNORMAL CONSIDERING THE LOW TIME IN S	ERVICE SINCE NEW (190 HRS). IDENTICAL SITUATION HAS OCCURRED 4 TIMES IN LAST 4 MONTHS ON 520 MODEL ENGINES OF SIMILAR L	OW TSO. ONE SIMILARITY OF ALL THE ENGINES IS, ALL USED AEROSHELL 15W-50 MULTIGRADE SYNTHETIC OIL.							3	O			E8CE				 
1995091500262	19950915	00262	SO 	1995	9	15	95ZZZX4511 	2	19950801	G	8520	642720	BEARING 								CONT 	O520 	TSIO520R 	17040	SO 					CRANK MAIN	WORN 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07		190 					269786R			ENGINE DISASSEMBLED AT 190 HRS TSO FOR INSP DUE TO PROP STRIKE. UNUSUAL WEAR ON ROD BEARINGS AND MAIN BEARINGS WAS OBSE	RVED. THE ROD BEARING WEAR WAS FOUND ONLY ON THE ROD-SIDE BEARINGS WHILE THE CAP-SIDE BEARINGS APPEAR NORMAL. ALL THE 	WORN BEARINGS SHOW HEAT STRESS DAMAGE. THE HEAT DAMAGE AND UNUSUAL WEAR ARE VERY ABNORMAL CONSIDERING THE LOW TIME IN S	ERVICE SINCE NEW (190 HRS). IDENTICAL SITUATION HAS OCCURRED 4 TIMES IN LAST 4 MONTHS ON 520 MODEL ENGINES OF SIMILAR L	OW TSO. ONE SIMILARITY OF ALL THE ENGINES IS, ALL USED AEROSHELL 15W-50 MULTIGRADE SYNTHETIC OIL.							3	O			E8CE				 
1995091500263	19950915	00263	CE 	1995	9	15	95ZZZX4512 	1	19950816	G	5753	3516505084	RIB 			BEECH 	55 	95B55B 		CE 										RT FLAP LE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	26DS	4735 				TC1324				DURING ANNUAL INSPECTION, FOUND SKIN CRACKED ON RT FLAP LEADING EDGE WHERE FLAP ACTUATOR ATTACHES TO FLAP. FOUND LEADIN	G EDGE RIB BROKEN. BROKEN RIB NOT VISIBLE FOR INSPECTION. PROBLEM CAUSES SKIN TO CRACK OUT AT FLAP ACTUATOR ATTACH BRA	CKET. REPAIR DIFFICULT DUE TO NO ACCESS TO CHANGE BROKEN RIB. SUSPECT CAUSED BY PEOPLE STEPPING ON FLAP ENTERING CABIN	. MANUFACTURER NEEDS TO ISSUE SB TO INSPECT, REPAIR, AND REINFORCE THIS AREA. SECOND FINDING.			1	L	7	2 	3O				3A16 					 
1995091500264	19950915	00264	GL 	1995	9	15	95ZZZX4513 	1	19950816	G	3230	19438310	BRACKET 			BLANCA	17 	1730A 	1220433	GL 										NLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	8223R	1301 				30407				BRACKET PASSED 10X INSPECTION ON AIRCRAFT. NOSE GEAR REMOVAL FOR REBUILD ALLOWED BRACKET INSPECTION WITH DRAG LINK REMO	VED. DYE PENETRANT REVEALED CRACKS OUT OF LOWER HOLE BOTH SIDES, HEADING TO EDGE OF BRACKET. BRACKET WAS SLIGHTLY BENT	 AT CRACKED HOLE.				1	L	7	1 	3O				A18CE 					 
1995091500265	19950915	00265		1995	9	15	95ZZZX4514 	4	19950816	G	6113	C3539	BULKHEAD 			BLANCA	17 	1730A 	1220433	GL 										SPINNER REAR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	8223R	2865 				30407				PROPELLER BULKHEAD CRACK FOUND DURING ANNUAL INSPECTION. POSSIBLE CAUSE OF CRACK IS SLIGHT DISHING OF BULKHEAD THAT IS 	FLATTENED OUT WHEN MOUNT BOLTS ARE TIGHTENED.					1	L	7	1 	3O				A18CE 					 
1995091500266	19950915	00266	SO 	1995	9	15	95ZZZX4515 	1	19950814	G	2720	6342006	PEDAL ASSY 			PIPER 	PA34 	PA34200 	7103405	SO 										PILOT RUDDER	MISREPAIRED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	15	1440T	3311 				347250310				FOUND ON A 100-HOUR INSPECTION THAT THE PILOT'S AND CO-PILOT'S RUDDER PEDALS WOULD NOT ALIGN WHEN ONE SIDE WAS PUT IN NE	UTRAL. FOUND A BRAZE REPAIR ON PILOT'S SIDE. ALSO, A SPLICE REPAIR ON COPILOT'S SIDE WITH TWO BOLTS WHICH HAD ELONGATE	D HOLES.				1	L	7	2 	3O				A7SO 					 
1995091500267	19950915	00267	CE 	1995	9	15	95ZZZX4516 	1	19950823	G	5751	12210897	HINGE 			CESSNA	177 	177 	2073704	CE 										AIL RIB WS 172	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	29406					17700877				DURING A 100-HOUR INSPECTION, BOTH CENTER AILERON HINGES WERE FOUND BENT AND THE LEFT HINGE WAS CRACKED APPROXIMATELY 3 	INCHES FORWARD OF HINGE BEARING. THERE IS NO OTHER APPARENT DAMAGE TO AILERON, WING, OR INBOARD AND OUTBOARD HINGES (WH	ICH SEEMS IMPOSSIBLE) AND IT HAS NOT BEEN SUBJECTED TO HIGH WINDS.				1	H	7	1 	3O			NT	A13CE 					 
1995091500268	19950915	00268	SO 	1995	9	15	95ZZZX4517 	1	19950725	G	7922	75944	VALVE 			PIPER 	PA32 	PA32R301 	7103218	SO 										THERMO BYPASS	SPRING BROKEN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	9128Z	1428 				3213008				WHILE COMPLYING WITH TEXTRON LYCOMING SB 518A, REMOVED THE BYPASS VALVE AND FOUND THE SPRING WHICH MAINTAINS PRESSURE ON	 THE SEAT BROKEN. PART OF THE SPRING HAD ROTATED AND WAS EXTENDING BEYOND THE VALVE SEAT. FATIGUE SUSPECTED AS CAUSE. 	 RECOMMEND INSPECTING SPRING AS WELL WHEN COMPLYING WITH SB 518A.				1	L	7	1 	3O				A3SO 					 
1995091500269	19950915	00269	SO 	1995	9	15	95ZZZX4518 	1	19950728	G	5712		RIB 			PIPER 	PA22 	PA22160 	7102214	SO 										RT FLAP ATTACH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	3442Z					227361				DURING ANNUAL INSPECTION, CRACKS FOUND AT RIB REAR ATTACHMENT AREA. ALSO, FOUND INBOARD FLAP ATTACHMENT CRACKED. AIRCR	AFT WAS DAMAGED AT APPROX 500 HOURS. RT WING WAS REBUILT WITH NEW RIBS. LT WING REPLACED WITH USED WING. LT WING WAS F	ROM A PA22-135. RT WING WAS ASSEMBLED IN REF TO LT WING. THE WINGS ARE DIMENSIONALLY THE SAME, BUT THE '160' WINGS HAV	E SMALLER RIB SPACING AND ONE ADDITIONAL RIB. THE '160' HAS VFE OF 95 COMPARED TO VFE 80 FOR THE '135'. BELIEVE USING 	'135' WING ON THIS AIRCRAFT WITH HIGHER FLAP EXTENSION SPEED CAUSED INCREASED STRESS ON THIS AREA. SIMILAR CRACKS FOUND	 IN LT WING WHEN REMOVED FOR RECOVER.	1	H	7	1 	3O				1A6 					 
1995091500270	19950915	00270	SO 	1995	9	15	95ZZZX4519 	1	19950806	G	3221	401511	BOLT 			PIPER 	PA25 	PA25235 	7102504	SO 										TAIL WHEEL	BROKEN 	G				O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			GL	11	7387Z	5300 				253346				BOLT SECURING TAIL WHEEL ASSY TO ACFT BROKE DURING TAKEOFF DURING A GLIDER/TOWING OPERATION. TAIL WHEEL DEFLECTED INTO 	LOWER PORTION OF RUDDER CAUSING RUDDER DISTORTION. SUBMITTER SUGGESTS BOLT BE REMOVED FOR INSPECTION IF AIRCRAFT IS USE	D FOR TOWING GLIDERS.				1	L	7	1 	3O				2A10 					 
1995091500271	19950915	00271	CE 	1995	9	15	95ZZZX4520 	1	19950711	G	7603		CONTROL CABLE 			CESSNA	182 	R182 	2072734	CE 										THROTTLE	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	736ZG					R18200899				THROTTLE CABLE HOUSING CHAFES LANDING GEAR RELAY AND HAS WORN DEEPLY INTO RELAY HOUSING. SPLIT 2 INCH LONG PIECE OF MIL	-H-6000, .3125 INCH, HOSE. PLIOBOND GLUE AND TYE-WRAP HOSE IN PLACE. NOTE: PROBLEM FOUND DURING ANNUAL INSPECTION.					1	H	7	1 	3O			RT	3A13 					 
1995091500272	19950915	00272	SW 	1995	9	15	95ZZZX4521 	1	19950824	G	5730		SKIN 			MOONEY	M20 	M20F 	5870214	SW 										RT WING	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	6996V	4565 				1358				THE RT WING SKIN AREA THAT IS FORWARD OF THE FLAP, WHERE THE FLAP FITS THE WING CONTOUR WHEN RETRACTED, WAS FOUND CRACKE	D. THE CRACK IS LOCATED NEXT TO THE INBOARD FLAP ATTACH SUPPORT ON THE UNDERSIDE OF THE RT WING SKIN. THE SUPPORT IS P	RIMARILY ATTACHED TO AN INTERNAL CAP STRIP, AND THE WING SKIN HELPS BY PROVIDING LATERAL SUPPORT. THE BASE ATTACHMENT M	AY HAVE CRACKED OR WEAKENED (WING SKIN HAS NOT YET BEEN REMOVED TO THOROUGHLY INSPECT), ALLOWING LATERAL FORCES SUFFICIE	NT TO CRACK THE SKIN.		1	L	7	1 	3O				2A3 					 
1995091500273	19950915	00273	GL 	1995	9	15	95ZZZX4522 	3	19950828	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	PROP	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	07	94377	4393 				15285658		RDA066		AN OIL LEAK WAS REPORTED. INVESTIGATION DISCLOSED A CRACK IN THE (FIXED PITCH) PROPELLER HUB RUNNING FROM THE HUB INSID	E DIAMETER, THROUGH THE EDGE OF ONE LEADING EDGE BOLT HOLE TO THE OUTSIDE DIAMETER OF THE HUB. THE FORWARD SPINNER BULK	HEAD ALSO HAD ONE 6 INCH CRACK AT THE SAME BOLT HOLE RUNNING TO THE EDGE OF THE BULKHEAD. CRANKSHAFT FORWARD SEAL WAS R	EPLACED; CRANKSHAFT RUN-OUT FOUND WITHIN ACCEPTABLE LIMITS. NEW PROP INSTALLED. SUGGEST PERIODIC BALANCING OF FIXED PI	TCH PROPS. AD89-26-10/SB 169C ALREADY C/W.		1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995091500274	19950915	00274	SW 	1995	9	15	95ZZZX4523 	1	19950818	G	3246	5736	WHEEL HALF 	BFGOODRICH 		SWRNGN	SA226 	SA226* 		SW 										MLG	DEFECTIVE 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09										DURING INSPECTION ON A WHEEL HALF, ONE MAIN WHEEL WAS FOUND UNSERVICEABLE. A REPLACEMENT WAS ORDERED, AND RECEIVED AN OV	ERHAULED WHEEL HALF. THIS WHEEL HALF HAD A RETURN-TO-SERVICE AND WORK ORDER FROM A REPAIR STATION THAT DOCUMENTED IT AS	 OVERHAULED, BUT DURING RECEIVING INSPECTION, CORROSION IN THE BEAD SEAT AREA WAS FOUND THAT SCRAPED THE WHEEL HALF. RE	CEIVING INSPECTIONS ARE IMPORTANT.			1	L	7	2 	4T			RT	A5SW 					 
1995091500275	19950915	00275	SO 	1995	9	15	95ZZZX4524 	1	19950822	G	2810	63913913	HOSE 		6399816 	PIPER 	PA28 	PA28R180 	7102809	SO 										TANK VENT	DETERIORATED 	B			RMMR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	4620J	4862 				28R30503				DURING REMOVAL OF THE RT FUEL TANK OF THIS AIRCRAFT, INSPECTION REVEALED BOTH FUEL VENT HOSES FOUND DETERIORATED TO THE 	POINT THAT VAPORS AND POSSIBLY LIQUID FUEL COULD BE LET INTO THE WING. LEFT TANK WAS ALSO REMOVED AND HOSES WERE FOUND 	DETERIORATED. ALSO, THE MAIN OUTLET HOSES, PN 63901-37, (ORIGINAL P/N) WERE INSTALLED. MFG CODES ON HOSES WERE 1Q68 AN	D 3Q67. ALL PARTS WERE REPLACED.			1	L	7	1 	3O				2A13 					 
1995091500276	19950915	00276	SO 	1995	9	15	95ZZZX4525 	1	19950822	G	2810	63913914	HOSE 		6399817 	PIPER 	PA28 	PA28R180 	7102809	SO 										TANK VENT	DETERIORATED 	B			RMMR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	4620J	4862 				28R30503				DURING REMOVAL OF THE RT FUEL TANK OF THIS AIRCRAFT, INSPECTION REVEALED BOTH FUEL VENT HOSES FOUND DETERIORATED TO THE 	POINT THAT VAPORS AND POSSIBLY LIQUID FUEL COULD BE LET INTO THE WING. LEFT TANK WAS ALSO REMOVED AND HOSES WERE FOUND 	DETERIORATED. ALSO, THE MAIN OUTLET HOSES, PN 63901-37, (ORIGINAL P/N) WERE INSTALLED. MFG CODES ON HOSES WERE 1Q68 AN	D 3Q67. ALL PARTS WERE REPLACED.			1	L	7	1 	3O				2A13 					 
1995091500277	19950915	00277	SO 	1995	9	15	95ZZZX4526 	2	19950829	G	8530	652112	ROTO COIL 			CESSNA	185 	A185F 	2072821	CE 	CONT 	O520 	IO520D 	17032	SO 					CYLINDERS 3-5	MAKING METAL 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	61423		1358 			18504180	282785R			WHEN REPLACING ROCKER COVER GASKETS BECAUSE OF OIL LEAKS, FOUND STEEL SLIVERS IN BOTTOM OF COVERS ON NR 3 AND NR 5 CYLIN	DERS. SENT SLIVERS TO CONTINENTAL TO BE ANALYZED. WAS INSTRUCTED BY CONTINENTAL TO REPLACE ALL ROTO COILS IN BOTH CYLI	NDERS. NO METAL FOUND IN OIL FILTER.				1	H	7	1 	3O	3	O		3A24 	E5CE				 
1995091500278	19950915	00278	SO 	1995	9	15	95ZZZX4527 	2	19950815	G	7310	641502	FITTING 			BEECH 	33 	F33A 	1151425	CE 	CONT 	O520 	IO520BB 	17032	SO 					FUEL PUMP	FAULTY 	B			KD4R	A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			SO	17	26UR	1321 				CE1274	578399			AFTER A NORMAL RUN-UP, ACFT LOST POWER ON TAKEOFF AT APPROX 300 FEET AGL. PILOT SWITCHED FUEL TANKS AND ADJUSTED MIXTUR	E CONTROL WITH NO RESULTS. A SAFE EMERGENCY LANDING WAS MADE ON THE DOWN-WIND RUNWAY. ENGINE WAS SHUT OFF AND ACFT TOW	ED TO MAINTENANCE HANGAR. INVESTIGATION REVEALED THE MAIN FUEL LINE FROM ENGINE DRIVEN FUEL PUMP TO CONTROL ASSY HAD BA	CKED OFF AT FUEL PUMP SIDE. FURTHER INVESTIGATION REVEALED THE THREADS ON THE 90-DEGREE ELBOW FITTING AT THE FUEL PUMP 	WERE SHARP AND SHOWED SIGNS OF WEAR. THE FITTING REPLACED WITH NEW UNIT. FUEL SYSTEM PRESSURE TESTED WITH NO LEAKS NOT	ED. ACFT REASSEMBLED AND RETURNED TO SERVICE.	1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995091500279	19950915	00279	SO 	1995	9	15	95ZZZX4528 	2	19950828	G	8530		SHAFT SUPPORT 			CESSNA	150 	150L 	2071826	CE 	CONT 	O200 	O200A 	17020	SO 					EXH ROCKER ARM	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	21997	3854 	411 			15074599	250401			DURING A SCHEDULED INSPECTION, (ACFT HAD SAT FOR ABOUT 6 MONTHS), THE COMPRESSION TEST WAS PERFORMED. NR 1 CYLINDER WAS	 BLOWING-BY FROM EXHAUST VALVE. TO STAKE THE VALVE, THE ROCKER BOX COVER WAS REMOVED. A BROKEN PIECE OF ROCKER ARM SHA	FT SUPPORT WAS FOUND INSIDE OF ROCKER BOX COVER. IT CAME OFF OF EXHAUST SIDE.				1	H	7	1 	3O	3	O		3A19 	E252				 
1995091500280	19950915	00280	SW 	1995	9	15	95ZZZX4529 	1	19950620	G	6230	206010443001	BEARING 			BELL 	206 	206B3 	1181506	SW 										SWASHPLATE	DEFECTIVE 	B			SL3R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	01					18410					INSTALLED NEW DUPLEX BEARING IN SWASHPLATE. BEARING VERY HARD TO ROTATE AND ROUGH WHEN ROTATED. NEW BEARINGS ORDERED A	ND INSTALLED.					1	G	7	1 	3U				H2SW 					 
1995091500281	19950915	00281	CE 	1995	9	15	95ZZZX4530 	1	19950824	G	6120	189894002	SOLENOID 			BEECH 	300 	300BEECH 	1152930	CE 										LT ENGINE	FAILED 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			CE	03	100BG	1991 			8903	FL6				GROUND IDLE SOLENOID FAILED ON THE LT ENGINE. DURING LANDING, THE LT PROPELLER REMAINED IN FLIGHT IDLE AND THE RT PROPE	LLER WENT INTO GROUND IDLE (FLATTER PITCH). THIS MADE FOR DIFFICULT HANDLING DURING LANDING ROLL-OUT.					2	L	7	2 	4T				A24CE 					 
1995091500282	19950915	00282	CE 	1995	9	15	95ZZZX4531 	1	19950823	G	3242		ROTOR DISK 	BFGOODRICH 		CESSNA	650 	650 	2076802	CE 										BRAKE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	442WT	1049 			21502	6507025				DURING ROUTINE TIRE CHANGES, WHEELS WERE REMOVED AND BRAKE ROTORS FELL OUT IN PIECES. REMOVED WHEELS FROM OPPOSITE GEAR	 AND BRAKE ROTORS WERE FOUND BROKEN ON THAT SIDE AS WELL. PILOTS SAY THEY ARE VERY 'GENTLE' ON THEIR BRAKES AS THEY DO 	NOT FLY INTO SHORT STRIPS AND THEY KNOW THAT THESE BRAKES ARE PRONE TO BREAKING.				2	L	7	2 	4F				A9NM 					 
1995091500283	19950915	00283	EA 	1995	9	15	95ZZZX4532 	2	19950814	G	7310	3011849A	LINE 			BEECH 	90 	E90 	1152914	CE 	PWA 	PT6 	PT6A28 		EA 					FUEL BYPASS	LEAK 	D		A		A				UNSCHED LANDING 				K			FLUID LOSS 			CR	CRUISE 	1			NE	03	323HA	2567 	2074 			LW323	PCE42080			PILOT NOTICED FUEL LEAKING FROM COWLING AT MID-NACELLE AREA. ALSO, A HIGHER FUEL FLOW INDICATION WAS NOTED. UPON INVES	TIGATION AFTER PRECAUTIONARY LANDING, IT WAS NOTED THE FUEL BYPASS LINE WAS LEAKING AT ONE END. A CRACK WAS DISCOVERED 	JUST AFT OF THE FERRULE, APPROXIMATELY THREE-FOURTHS OF THE CIRCUMFERENCE. A NEW LINE WAS INSTALLED AND THE AIRCRAFT RE	TURNED TO SERVICE. POSSIBLE PRE-LOADING AT INSTALLATION COULD HAVE CAUSED THE FAILURE.			1	L	7	2 	3T	4	T		3A20 	E4EA				 
1995091500285	19950915	00285	CE 	1995	9	15	95ZZZX4534 	1	19950522	G	3230		ACTUATOR 			CESSNA	500 	S550 	2076607	CE 										RT MLG	HOSE MISCONNECT 	B		A	CWQR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	05	106QS	8557 				S5500106				DURING INSPECTION, FOUND RIGHT MAIN GEAR ACTUATOR GEAR EXTEND AND AUXILIARY AIR HOSES CONNECTED TO WRONG PORTS. THERE A	RE TWO BRANDS OF ACTUATORS USED AND THEIR PORTS ARE OPPOSITE. THE PORTS SHOULD BE IN THE SAME POSITION ON EACH BRAND OF	 ACTUATOR. MORE ATTENTION SHOULD BE PAID TO ACTUATOR PLACARDS AND MAINTENANCE.				1	L	7	2 	4F			RT	A22CE 					 
1995091500286	19950915	00286	CE 	1995	9	15	95ZZZX4535 	1	19950807	G	2750	55651754	CONTROL CABLE 			CESSNA	500 	S550 	2076607	CE 										FLAP CONTROL	MISROUTED 	B		A	CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	126QS	7179 				S5500126				DURING PHASE 5 INSPECTION, FOUND FLAP CONTROL CABLES CAUGHT ON CONTROL COLUMN TUBE ASSEMBLY WHERE ELEVATOR SECTOR ASSEMB	LY CONNECTS. CABLES FOUND UNDAMAGED. IT IS UNKNOWN HOW LONG CABLES WERE IN THIS CONDITION. MORE CARE HAS TO BE TAKEN 	WHEN WORKING WITH CABLES AS IT APPEARS THE CABLES WERE ROUTED INCORRECTLY. LOSS OF FLAP CONTROL COULD HAVE HAPPENED.				1	L	7	2 	4F			RT	A22CE 					 
1995091500288	19950915	00288	GL 	1995	9	15	95ZZZX4537 	2	19950812	G	7210	A23034787	BEARING 								ALLSN 	250C 	250C20 	03013	GL 					GEARBOX	MAKING METAL 	B			UP9R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07		2745 			083		CAB832926			GEARBOX 2 1/2 BEARING STARTING TO MAKE METAL. ROLLERS STARTING TO GALL.											3	U			E4CE				 
1995091500289	19950915	00289	GL 	1995	9	15	95ZZZX4538 	2	19950817	G	7250	23001967	TURBINE WHEEL 								ALLSN 	250C 	250C20 	03013	GL 					NR 3	SHROUD CRACKED 	B			UP9R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07		2745 			HX73658		CKE832926			TURBINE NR 3 WHEEL SHROUD CRACKED THROUGH.											3	U			E4CE				 
1995091500290	19950915	00290	GL 	1995	9	15	95ZZZX4539 	2	19950813	G	7230	23031922	GEARSHAFT 								ALLSN 	250C 	250C20 	03013	GL 					SPUR ADAPTER	STEP WEAR 	B			UP9R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07		2745 			TH83938		CAE832926			SPUR ADAPTER GEARSHAFT SPLINES ON TURBINE END STEPPED.											3	U			E4CE				 
1995091500291	19950915	00291	GL 	1995	9	15	95ZZZX4540 	2	19950812	G	7210	A6887772	BEARING 								ALLSN 	250C 	250C20 	03013	GL 					GEARBOX PTO	SPALLED 	B			UP9R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07		2745 			044		CAE832926			PTO BEARING STARTING TO SPALL AND MOVE METAL.											3	U			E4CE				 
1995091500293	19950915	00293	EU 	1995	9	15	95ZZZX4542 	2	19950730	G	7314	7086002	PUMP 			BOEING	737 	737* 		NM 	CFMINT	CFM56 	CFM563B2 	13802	EU 					LT ENG HP FUEL	LEAKING 	B			GJPY	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	33					20127					WHEN STARTING LT ENGINE, HIGH PRESSURE FUEL PUMP LEAKED FUEL. REPLACED THE FUEL PUMP PER MM73-11-01. ADJUSTED AND RAN 	ENGINE PER TEST 6, ALL PARAMETERS WERE OKAY.					2	L	7	2 	4F	4	F	RT	A16WE 	E21EU				 
1995091500295	19950915	00295	CE 	1995	9	15	95ZZZX4544 	1	19950821	G	2133	10357626	OUTFLOW VALVE 	AIRESRCH 		CESSNA	500 	550 	2076604	CE 										CABIN PRESS	POPPET CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	362CP		1127 		31978	5504030				THIS VALVE WAS WORKING PROPERLY WHEN REMOVED FOR SB 550-21-41. FURTHER INSPECTION FOUND CRACK IN POPPET AREA. IF IT HA	D CRACKED MORE, IT IS POSSIBLE THAT THE CABIN WOULD HAVE DEPRESSURIZED. SUBMITTER STATES IF THIS SB APPLIES TO AIRCRAFT	, C/W AS SOON AS POSSIBLE OR HAVE FREQUENT INSPECTIONS UNTIL ACCOMPLISHMENT. THIS IS ALSO AIRESEARCH BULLETIN 103576-21	-4056.			1	L	7	2 	4F				A22CE 					 
1995091500296	19950915	00296	WP 	1995	9	15	95ZZZX4545 	1	19950808	G	5751	5910047502	TAB ASSY 			DOUG 	DC9 	DC9* 		WP 										WING	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15										PART WAS RECEIVED FOR REPAIR OF GROUND HANDLING DAMAGE. PART HAD AN ID TAG INDICATING OVERHAUL ON 6/95 BY ANOTHER REPAI	R STATION. TEAR DOWN FOUND CORROSION INTERNALLY OF CONTROL HORN FITTING, PN 3914776, FROM INSIDE TO OUTSIDE. HCB W.O. 	HEF12600 H42R886K.				2	L	7	2 	4F				A6WE 					 
1995091500297	19950915	00297	WP 	1995	9	15	95ZZZX4546 	2	19950815	G	7314	8973902	PUMP 			AYRES 	S2 	S2RRESTD 	0970101	SO 	GARRTT	TPE331	TPE3311 	01514	WP 					ENGINE FUEL	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	8034V	2400 				2453R	P91136			PILOT REPORTED OIL CONSUMPTION AT APPROXIMATELY 1 QUART PER HOUR. NO OIL FOUND AT THE FORWARD OR REAR CARBON SEALS. OI	L WAS DISCOVERED INSIDE THE FUEL PUMP BY A FUEL SAMPLE ANALYSIS FROM THE FUEL PUMP FILTER BOWL. ON ENGINES INCORPORATIN	G SB 72-0104 (WET SPLINE FUEL PUMP DRIVE), THE OIL CAN PASS THROUGH A SMALL ORIFICE IN THE FUEL PUMP IMPELLER SHAFT WHIC	H IS PACKED WITH A SPECIAL GREASE. ONCE THE GREASE IS WASHED AWAY, THE ENGINE FUEL PUMP DRAWS IN OIL INTO THE FUEL FLOW	. THE PROBLEM WAS REPAIRED BY GARRETT WITH A PLUG INSTALLED IN THE IMPELLER SHAFT. SUBMITTER STATES SECOND INCIDENT FO	UND IN 5 MONTHS.	1	L	7	1 	3R	3	T		A4SW 	E3WE				 
1995091500298	19950915	00298	SW 	1995	9	15	95ZZZX4547 	1	19950810	G	3340	727725	BREAKER 	KLIXON 		SWRNGN	SA226 	SA226TC 	8780404	SW 										COCKPIT	FAILED 	B			ATZR	K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			CE	09	1009R	21699				TC358				NAVIGATION LIGHT CIRCUIT BREAKER CAUSED SMOKE IN COCKPIT. DID NOT POP - CAUSE WAS SHORTED WIRE AT NAVIGATION LIGHT.						1	L	7	2 	4T				A8SW 					 
1995091500299	19950915	00299	EU 	1995	9	15	95ZZZX4548 	1	19950706	G	3233	T700A3230050000	ACTUATOR 			SOCATA	TBM 	TBM700 	8682000	EU 										NLG	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	07	56WF	732 				8				NOSE GEAR STRUT ACTUATOR LEAKING HYDRUALIC FLUID AT VENT SCREEN HOLES. THIS IS FROM FLUID BYPASSING O-RINGS IN ACTUATOR	. NO FIELD LEVEL REPAIR AT THIS TIME. UNIT MUST BE OVERHAUL/EXHCHANGE FROM VENDOR. AUGUST 11, 1995, AIRCRAFT OWNER HA	S BEEN WAITING FOR OVER 2 MONTHS FOR PART.				1	L	7	1 	3T			RT	A60EU 					 
1995091500302	19950915	00302	CE 	1995	9	15	95ZZZX4551 	1	19950825	G	2510		SEAT BELT 			BEECH 	35 	35BEECH 	1151502	CE 										LT FRONT	FAILED 	G	S	A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	05	3944N					D1202				AN UNAPPROVED ALTERATION TO THE LEFT FRONT INBOARD SEAT BELT ATTACH POINT WHICH FAILED DURING AN ACCIDENT. THE P.I.C WA	S EJECTED FROM THE AIRCRAFT IN SERIOUS CONDITION. THE ATTACH BRACKET AND CONNECTING BELT HAD BEEN MODIFIED.					1	L	7	1 	3O				A777 					 
1995091500303	19950915	00303	CE 	1995	9	15	95ZZZX4552 	1	19950821	G	3213	08412012	STRUT ASSY 			CESSNA	310 	310 	2074202	CE 										RT MLG	FAILED 	G		A		O				OTHER 				O			OTHER 			LD	LANDING 	1			EA	01	661R					35033				FAILURE OF RIGHT MAIN LANDING GEAR LOWER STRUT CAUSED AIRCRAFT TO VEER OFF RUNWAY CAUSING SUBSTANTIAL DAMAGE TO AIRCRAFT	. LOWER SECTION SEPARATED FROM UPPER SECTION AT WELDED JOINT. NOTE: RECOMMEND ALL WELDED JOINTS ON LOWER STRUT BE INS	PECTED, P/N OF CASTING, PN 0841215-3.				1	L	7	2 	3O			RT	3A10 					 
1995091500304	19950915	00304	EA 	1995	9	15	95ZZZX4553 	2	19950829	G	8520	954	STUD 			WACO 	YMF 	YMF 	9600412	EA 	JACOBS	R755 	L4MB 	35003	EA 					NR 7 CYLINDER	FAILED 	G	L			A				UNSCHED LANDING 				O			OTHER 			NR	NOT REPORTED 	1			SO	15	14128					4213	8339			FOLLOWING OVERHAUL, ENGINE WAS PUT IN SERVICE. AT 593 HOURS, CHANGED OUT THE NR 5 CYLINDER AND FOUND NOTHING THAT WOULD	 HAVE BEEN ALARMING OR INDICATIVE OF WHAT MIGHT HAPPEN. AT 680 HOURS SMOH, THE NR 7 CYLINDER BROKE ALL THE HOLD-DOWN ST	UDS, LIFTED .50 INCH OFF THE BASE AND WAS KEPT FROM COMPLETE SEPARATION ONLY BY THE COWLING AND OIL RETURN HOSES. EVEN 	THOUGH THE ENGINE WAS STILL RUNNING AND DEVELOPING SUBSTANTIAL POWER, THE PILOT MADE A PERFECT PRECAUTIONARY LANDING. U	PON TEARING DOWN ENGINE, DISCOVERED FOLLOWING: ALL STUDS ON NR 7 CYLINDER BROKEN. THREE ADDITIONAL STUDS, RANDOMLY LOC	ATED THROUGHOUT ENGINE, WERE ALSO BROKEN.	1	Q	7	1 	3R	3	R		ATC542 	TC121				 
1995091500305	19950915	00305	CE 	1995	9	15	95ZZZX4554 	1	19950908	G	2730	07601037	CONTROL ROD 			CESSNA	206 	U206G 	2073356	CE 										PILOTS YOKE	LOOSE RIVETS 	G	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	4637U	8053 				U20605017				DURING ROUTINE INSPECTION, FOUND PILOT YOKE PUSH ROD CONTROL TUBE ASSY WITH LOOSE RIVETS. NOTED .05 INCH PLAY IN CONNECT	ION. NEW PART RECEIVED FROM CESSNA AND INSPECTION REVEALED ALUMINUM RIVETS USED DURING ASSEMBLY IN PLACE OF CARBON STEEL	. CESSNA FACTORY VERIFIED CARBON STEEL RIVETS REQUIRED.				1	H	7	1 	3O				A4CE 					 
1995091500392	19950915	00392	EU 	1995	9	15	95ZZZX4555 	1	19950807	G	7922	53E19600	VALVE 			SLNSBY	T67 	T67M260 	8323006	EU 										THERMO BYPASS	MALFUNCTIONING 	B			UNER	O				OTHER 				M			OVER TEMP 			CR	CRUISE 	1			NM	03	3107K	217 				2166				AIRCRAFT DEVELOPED HIGH OIL TEMPERATURE (120 DEGREES CELSIUS) AND LOW OIL PRESSURE (60 PSI) DURING A ROUTINE TRAINING MI	SSION. OUTSIDE AIR TEMPERATURE WAS ABOVE 80 DEGREES FAHRENHEIT. AIRCRAFT PILOT MADE AN ATTEMPT TO COOL ENGINE DURING R	ETURN FLIGHT TO AIRFIELD. MAINTENANCE TECHNICIANS CHECKED ENGINE BAFFLE SEALS, TESTED OIL PRESSURE AND TEMPERATURE TRAN	SDUCERS AND CHECKED ENGINE OIL PRESSURE WITH A DIRECT READING GAUGE. THE OIL COOLER THERMAL BYPASS VALVE WAS TESTED BY 	PLACING THE UNIT IN OIL HEATED TO 120 DEGREES CELSIUS. BYPASS VALVE OPENED ABOVE 120 DEGREES CELSIUS. SEVERAL BYPASS V	ALVES HAVE MALFUNCTIONED IN THE T-3A FLEET. VALVES TESTED STARTED OPENING AT TEMPS ABOVE 120 DEGREES CELSIUS.	1	L	7	1 	3O			NT	A73EU 					 
1995100600488	19951006	00488	EU 	1995	10	6	95ZZZX4556 	1	19950807	G	7922	53E19600	VALVE 			SLNSBY	T67 	T67M260 	8323006	EU 										ENGINE	MALFUNCTIONING 	B			UNER	O				OTHER 				M			OVER TEMP 			CR	CRUISE 	1			NM	03	3064Q	295 				2151				AIRCRAFT DEVELOPED HIGH OIL TEMPERATURE (120 DEGREES CELSIUS) AND LOW OIL PRESSURE (60 PSI) DURING A ROUTINE TRAINING MI	SSION. OUTSIDE AIR TEMPERATURE WAS ABOVE 80 DEGREES FAHRENHEIT. AIRCRAFT PILOT MADE ATTEMPT TO COOL ENGINE DURING THE 	RETURN FLIGHT TO AIRFIELD. MAINTENANCE TECHNICIANS CHECKED ENGINE BAFFLE SEALS, TESTED OIL PRESSURE AND TEMPERATURE TRA	NSDUCERS AND CHECKED ENGINE OIL PRESSURE WITH DIRECT READING GAUGE. OIL COOLER TERMINAL BYPASS VALVE WAS TESTED BY PLAC	ING THE UNIT IN OIL HEATED TO 120 DEGREES CELSIUS. BYPASS VALVE OPENED ABOVE 120 DEGREES CELSIUS. SEVERAL BYPASS VALVE	S HAVE MALFUNCTIONED IN T-3A FLEET. VALVES TESTED STARTED OPENING AT TEMPS ABOVE 120 DEGREES CELSIUS.	1	L	7	1 	3O			NT	A73EU 					 
1995091500393	19950915	00393	EU 	1995	9	15	95ZZZX4557 	1	19950823	G	7922	53E19600	VALVE 			SLNSBY	T67 	T67M260 	8323006	EU 										THERMO BYPASS	LOOSE NUT 	B			UNER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	3094T	199 				2160				AIRCRAFT DEVELOPED HIGH OIL TEMPERATURE (120 DEGREES CELSIUS) AND LOW OIL PRESSURE (60 PSI) DURING ROUTINE TRAINING MISS	ION. SEVERAL AIRCRAFT IN THE FLEET HAD SIMILAR PROBLEMS WHICH WERE RESOLVED BY CHANGING DEFECTIVE THERMOSTATIC BYPASS V	ALVES. WHEN THIS VALVE WAS REMOVED, SECURING NUT FOR THE SPRING ASSY FELL INTO THE MECHANICS HAND AS HE REMOVED THE VAL	VE. TEXTRON LYCOMING SB NR 518C ADDRESSES LOOSE SECURING NUT. BUT THIS THERMOSTATIC BYPASS VALVE (PN 53E19600) HAS A S	ERIAL NUMBER OUTSIDE THE RANGE OF THOSE VALVES TO BE INSPECTED. A FLEET-WIDE INSPECTION REVEALED 25 OF 55 AIRCRAFT HAD 	LOOSE NUTS WITH S/N'S ALL ABOVE/HIGHER THAN S/N 53788. (WORN THREADS SN 54570).	1	L	7	1 	3O			NT	A73EU 					 
1995100600489	19951006	00489	EU 	1995	10	6	95ZZZX4558 	1	19950821	G	7922	53E19600	VALVE 			SLNSBY	T67 	T67M260 	8323006	EU 										ENGINE	MALFUNCTIONING 	B			UNER	O				OTHER 				M			OVER TEMP 			CR	CRUISE 	1			NM	03	3079Q	387 				2156				AIRCRAFT DEVELOPED HIGH OIL TEMPERATURE (120 DEGREES CELSIUS) AND LOW OIL PRESSURE (60 PSI) DURING A ROUTINE TRAINING MI	SSION. OUTSIDE AIR TEMPERATURE WAS ABOVE 80 DEGREES FAHRENHEIT. AIRCRAFT PILOT MADE ATTEMPT TO COOL ENGINE DURING RETU	RN FLIGHT TO THE AIRFIELD. MAINTENANCE TECHNICIANS CHECKED THE ENGINE OIL PRESSURE WITH A DIRECT READING GAUGE. OIL CO	OLER THERMAL BYPASS VALVE WAS TESTED BY PLACING THE UNIT IN OIL HEATED TO 120 DEGREES CELSIUS. THE BYPASS VALVE OPENED 	ABOVE 120 DEGREES CELSIUS. SEVERAL BYPASS VALVES HAVE MALFUNCTIONED IN THE T-3A FLEET. THE VALVES TESTED AT TEMPERATUR	ES ABOVE 120 DEGREES CELSIUS.	1	L	7	1 	3O			NT	A73EU 					 
1995091500394	19950915	00394	CE 	1995	9	15	95ZZZX4559 	1	19950811	G	2750	16952404717	CONTROL CABLE 			BEECH 	23 	B19 	1151215	CE 										FLAP CONTROL	FAILED 	D		A		O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			SW	05	5114R	12832				MB648				FLAP CABLE FAILED WHERE CABLE WRAPS AROUND FLAP TORQUE TUBE. VERY DIFFICULT TO SEE DURING INSPECTIONS. SUBMITTER STATE	D FOUND 3 OTHER CABLES IN FLEET WITH VARYING DEGREES OF FAILURE. SUBMITTER SUGGESTS MUCH CLOSER INSPECTION OF FLAP CABL	E DURING 100-HOUR ANNUALS. SEEM TO BE FAILING AROUND TORQUE TUBE WITH FLAPS IN UP POSITION, CABLE IS UNDER SPAR IN DOWN	 POSITION.			1	L	7	1 	3O			 	A1CE 					 
1995091500395	19950915	00395	SO 	1995	9	15	95ZZZX4560 	1	19950812	G	5500	641051000	NIPPLE 			PIPER 	J3 	J3 	7100502	SO 										TAILPLANE	WORN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	98674	2881 				18904				DURING RESTORATION OF THIS AIRCRAFT, THE TAILPLANE EXTERNAL BRACING WIRES NIPPLES MADE OF BRASS WERE FOUND BADLY WORN. T	HIS WAS IMPOSSIBLE TO SEE WITHOUT TAKING THE TENSION OFF THE BRACING WIRES. SUBMITTER SUGGESTS THIS SHOULD BE CHECKED O	N HIGH TIME AIRCRAFT OR ANNUAL INSPECTION. THIS COULD HAVE FAILED.				1	H	7	1 	3O				ATC660 					 
1995091500396	19950915	00396	CE 	1995	9	15	95ZZZX4561 	1	19950815	G	3244	850X10	TIRE 	GOODYEARAERO		CESSNA	185 	185A 	2072804	CE 											DAMAGED 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			AL	01	4145Y					1850345				THIS AIRCRAFT HAD STC SA 4305WE INCORPORATED, GAR-AERO 6 INCH TO 10 INCH WHEEL ADAPTERS WITH GOODYEAR 8.50-10 6-PLY TIRE	S. ON LANDING ROLL-OUT ON PAVED RUNWAY, THE LEFT TIRE WENT FLAT CAUSING THE AIRCRAFT TO GROUND LOOP. INVESTIGATION REV	EALED THE TIRE HAD COME LOOSE AT THE BEAD/RIM AND HAD CUT THE TUBE STEM. LOW TIRE PRESSURE AND LANDING ON DRY PAVED RUN	WAY MAY HAVE OVERLOADED THE BEAD/TIRE ADHESION ALLOWING TIRE TO SPIN ON WHEEL.			1	H	7	1 	3O				3A24 					 
1995091500397	19950915	00397	CE 	1995	9	15	95ZZZX4562 	1	19950831	G	5522	9661000612	SKIN 		96610006617 	BEECH 	58 	58 	1152740	CE 										ELEVATOR OTBD LE	CRACKED 	B			HBKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	7222V	2333 				TH1430				OUTBOARD LEADING EDGE BOTTOM SKIN CRACKED. CRACK LOCATED JUST OUTBOARD OF OUTBOARD ELEVATOR ATTACH POINT. SUBMITTER SU	GGESTS THE WEIGHT OF ELEVATOR BALANCE WEIGHT MAY HAVE CREATED STRESS AND CRACKED THE SKIN.					1	L	7	2 	3O				3A16 					 
1995091500398	19950915	00398	SO 	1995	9	15	95ZZZX4563 	1	19950706	G	2434	3656624	ALTERNATOR 	ELECTROSYS 		PIPER 	PA28 	PA28181 	7102807	SO 										FRONT ROTOR	BEARING WORN 	B			SJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	3023M	107 			4080479	287890285				DURING ANNUAL INSPECTION FOUND FAN, (INTERNAL), RUBBING HOUSING. ROTOR WOULD MOVE FORE AND AFT .25 INCH TO .3750 INCH A	ND UP AND DOWN SAME AMOUNT. SUSPECT BEARINGS AND HOUSING WORN OUT.					1	L	7	1 	3O				2A13 					 
1995091500399	19950915	00399	SO 	1995	9	15	95ZZZX4564 	2	19950819	G	8550	1002	OIL TUBE 			CESSNA	206 	U206G 	2073356	CE 	CONT 	O520 	IO520F 	17032	SO 					ENGINE	EXTENDER CRACKED	D				K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			AL	03	4975U	2000 				U2065179	284679R			THE EXTENDER CRACKED AT BOTTOM FLANGE AND THE TUBE FELL OFF THE ENGINE CAUSING OIL TO COME OUT OF ENGINE. SUBMITTER SUG	GESTS LARGER WELDS WOULD HELP HOLD IT TOGETHER BETTER.					1	H	7	1 	3O	3	O		A4CE 	E5CE				 
1995091500400	19950915	00400	SO 	1995	9	15	95ZZZX4565 	1	19950816	G	3230	7642603	DRAG BRACE 			PIPER 	PA28 	PA28R200 	7102811	SO 										NLG	CRACKED 	B			LCPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	7935C	5100 				28R7635122				DURING 100-HOUR INSPECTION, A CRACK WAS FOUND ON THE NLG DRAG BRACE IN THE RADIUS FORWARD OF THE ACTUATOR ATTACH POINT.						1	L	7	1 	3O				2A13 					 
1995091500401	19950915	00401	SO 	1995	9	15	95ZZZX4566 	1	19950816	G	5620	5666703	WINDOW 			PIPER 	PA42 	PA42 	7104202	SO 										CABIN	CRACKED 	B		A	R2JR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	18AF	3608 				428001063				WHEN CONDUCTING INSPECTION ON 1981 MODEL PA-42, MANDATORY SB 984 WAS C/W. TEN OF TWELVE CABIN SIDE WINDOWS INSPECTED SH	OW CRACKS BEYOND LIMITS OF SB 984. CRACKS NOT VISIBLE WITHOUT USING PRISM TO VIEW BEHIND STRUCTURE. NO REPAIRS APPROVE	D, WINDOWS MUST BE REPLACED AND RE-CHECKED AT 12-MONTH INTERVALS. SB 984 ALSO RECURS EACH 100 HOURS FOR WINDOWS PRESENT	LY INSTALLED. SUBMITTER SUGGESTS AD NOTE BE ISSUED TO ENSURE SB 984 COMPLIANCE.			1	L	7	2 	4T				A23SO 					 
1995091500402	19950915	00402	SO 	1995	9	15	95ZZZX4567 	1	19950816	G	5620	5666702	WINDOW 			PIPER 	PA42 	PA42 	7104202	SO 										CABIN	CRACKED 	B			R2JR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	18AF	3608 				428001063				WHEN CONDUCTING INSPECTION ON 1981 MODEL PA-42, MANDATORY SB 984 WAS C/W. TEN OF TWELVE CABIN SIDE WINDOWS INSPECTED SH	OW CRACKS BEYOND LIMITS OF SB 984. CRACKS NOT VISIBLE WITHOUT USING PRISM TO VIEW BEHIND STRUCTURE. NO REPAIRS APPROVE	D, WINDOWS MUST BE REPLACED AND RE-CHECKED AT 12-MONTH INTERVALS. SB 984 ALSO RECURS EACH 100 HOURS FOR WINDOWS PRESENT	LY INSTALLED. SUBMITTER SUGGESTS AD NOTE BE ISSUED TO ENSURE SB 984 COMPLIANCE.			1	L	7	2 	4T				A23SO 					 
1995091500403	19950915	00403	SO 	1995	9	15	95ZZZX4568 	1	19950823	G	7810	47C19845	TRANSITION PIPE 			PIPER 	PA46 	PA46350P 		SO 										RT EXH TEE	PERFORATED 	B		A	LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	12FA	1106 				4622106				WHILE PERFORMING INSPECTION ON AIRCRAFT, FOUND RT EXHAUST TRANSMISSION TEE BLISTERED. UPON REMOVAL, FOUND PERFORATION A	T THE BLISTERS. THESE PIPES ARE MADE OF FAIRLY THICK MATERIAL. PROBABLY CAUSED BY EROSION IN ADDITION TO EXCESSIVE HEA	T. SUBMITTER STATES THE TIT INDICATION SYSTEM SHOULD BE CHECKED FOR ACCURACY ON A REGULAR BASIS. CLOSE ATTENTION ALSO 	NEEDS TO BE PAID TO EXHAUST SYSTEMS. SHOULD BE INSPECTED AT EVERY OIL CHANGE.			1	L	7	1 	3O			RT	A25SO 					 
1995091500404	19950915	00404	CE 	1995	9	15	95ZZZX4569 	1	19950728	G	2730		ELEVATOR TUBE 			CESSNA	172 	172 	2072402	CE 										LT FLANGE	RIVETS SHEARED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	7019T					46619				ALL SIX RIVETS HOLDING ELEVATOR TUBE TO FLANGE WERE SHEARED OFF. THIS ALLOWED THE LT ELEVATOR TO MOVE INDEPENDENTLY FRO	M RT ELEVATOR OR CONTROL WHEEL. CONDITION WAS DISCOVERED DURING PRE-FLIGHT INSPECTION. OWNER WAS TALKED OUT OF FLYING 	IT IN THIS CONDITION. WHEN RT ELEVATOR WAS REMOVED AND CHECKED, MOVEMENT WAS DISCOVERED. THIS MOVEMENT WAS VERY SLIGHT	 AND NOT DETECTABLE ON THE AIRCRAFT. THE ONLY WAY TO CHECK FOR THIS IS TO MOVE ELEVATORS UP AND DOWN, OPPOSITE EACH OTH	ER, AND LOOK FOR MOVEMENT BETWEEN ELEVATOR TUBE AND FLANGE. NO MOVEMENT IS ACCEPTABLE.		1	H	7	1 	3O			NT	3A12 					 
1995091500405	19950915	00405	CE 	1995	9	15	95ZZZX4570 	1	19950725	G	7920	3608D0504	HOSE 			CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540J3C5 	41532	EA 					ENGINE OIL	FAILED 	D				A				UNSCHED LANDING 				Y	K		ENGINE STOPPAGE 	FLUID LOSS 		NR	NOT REPORTED 	1			EA	21	4702R	1067 			S1167	R18200605	12418440A			OIL COOLER TO ENGINE HOSE RUPTURED APPROXIMATELY 6 INCHES FROM FITTING. SUSPECT SOME KIND OF ACID PENETRATED THE HOSE I	N ONE SPOT APPROXIMATELY 3 INCHES TO 3.50 INCHES AND DETERIORATED THE METAL AWAY. HOSE LINING FAILED ON A REAL HOT DAY 	AND PUMPED ALL THE OIL OVERBOARD CAUSING ENGINE TO SEIZE.				1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1995091500406	19950915	00406	GL 	1995	9	15	95ZZZX4571 	1	19950801	G	7603		CONTROL CABLE 			AMTR 	KITFOX	KITFOX 	05613LZ	GL 										ENG THROTTLE	BROKEN 	G				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			EA	27	9KF	202 				134				AT CRUISE FLIGHT, ENGINE POWER SUDDENLY WENT TO IDLE WITH NO THROTTLE RESPONSE. THROTTLE CABLE BROKE DURING FLIGHT.						1	H	7	1 	3I			NC	EXPA1H71					 
1995091500407	19950915	00407	EU 	1995	9	15	95ZZZX4572 	1	19950714	G	2824		OVERFLOW VALVE 			WSK 	M18 	M18DROMADER 	9810102	EU 										INST PANEL	REQ RELABEL 	G				A				UNSCHED LANDING 				J	Y		WARNING INDICATION 	ENGINE STOPPAGE 		CR	CRUISE 	1			CE	05	168RA	1849 				1Z01515				PILOT STATED DURING FLIGHT, LT WING FUEL LOW WARNING LIGHT ILLUMINATED FOR 15 MINS PRIOR TO FORCED LANDING ACCIDENT. IN	VESTIGATION REVEALED ENG FUEL STARVATION. SUBMITTER RECOMMENDED FUEL OVERFLOW VALVE BE RE-LABLED TO READ 'EMERGENCY CRO	SS-FEED VALVE' IN ORDER TO ACCURATELY DEPICT ITS FUNCTION AND IDENTIFY TO THE PILOT DURING AN EMERGENCY. ADD A PLACARD 	FWD OF VALVE ON RT INST PANEL IN COCKPIT CITING 'AFTER HAVING NOTICED UNEQUAL FUEL CONSUMPTION FROM THE WING TANKS, OPEN	 THE EMERGENCY CROSS-FEED VALVE (FUEL OVERFLOW VALVE) AND RECOVER AIRPLANE TO LEVEL FLIGHT OR BANK AIRPLANE TOWARDS THE 	WING WITH LESS FUEL TO QUICKLY EQUALIZE THE FUEL LEVEL IN BOTH TANKS'. NTSB ACCID NR CHI95LA221.	1	L	7	1 	3O				A47EU 					 
1995091500408	19950915	00408	CE 	1995	9	15	95ZZZX4573 	1	19950802	G	7120	653305	BRACKET 			BEECH 	58 	58 	1152740	CE 										RT AFT ENG MT	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11	18414	1447 	376 			TH861				WHILE C/W AD 91-15-20, FOUND RIGHT ENGINE LOWER NR 1 CYLINDER BRACKET BROKEN IN TWO. NOTE: AD 95-03-14, PN 630695, APP	LIES TO LEFT LOWER BRACKET. THIS WAS RIGHT LOWER BRACKET. SUBMITTER STATED AD 95-03-14 SHOULD APPLY TO BOTH ENGINE MOU	NT BRACKETS.				1	L	7	2 	3O				3A16 					 
1995091500409	19950915	00409	EU 	1995	9	15	95ZZZX4574 	1	19950616	G	5712	T67G20003	RIB 			SLNSBY	T67 	T67M260 	8323006	EU 										LT/RT WING	SKIN DEBOND 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	30364	297 				2132				A ONE-TIME INSPECTION FOUND WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTERLINE.						1	L	7	1 	3O			NT	A73EU 					 
1995091500410	19950915	00410	EU 	1995	9	15	95ZZZX4575 	1	19950616	G	5712	T67G20003	RIB 			SLNSBY	T67 	T67M260 	8323006	EU 										LT/RT WING	SKIN DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	7020D	662 				2109				A ONE-TIME INSPECTION FOUND WING SKIN DEBONDING FROM NR 2 RIB 31 INCHES FROM CENTERLINE.						1	L	7	1 	3O			NT	A73EU 					 
1995091500411	19950915	00411	EU 	1995	9	15	95ZZZX4576 	1	19950616	G	5712	T67G20003	RIB 			SLNSBY	T67 	T67M260 	8323006	EU 										LT/RT WING	SKIN DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3037X	346 				2137				A ONE-TIME INSPECTION FOUND WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTERLINE.						1	L	7	1 	3O			NT	A73EU 					 
1995091500412	19950915	00412	EU 	1995	9	15	95ZZZX4577 	1	19950616	G	5712	T67G20003	RIB 			SLNSBY	T67 	T67M260 	8323006	EU 										LT/RT WING	SKIN DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3037H	101 				2135				A ONE-TIME INSPECTION FOUND WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTERLINE.						1	L	7	1 	3O			NT	A73EU 					 
1995091500413	19950915	00413	EU 	1995	9	15	95ZZZX4578 	1	19950616	G	5712	T67G20003	RIB 			SLNSBY	T67 	T67M260 	8323006	EU 										LT/RT WING	SKIN DEBONDED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	30377	357 				2138				A ONE-TIME INSPECTION FOUND WING SKIN DEBONDING FROM NR 2 RIB, 31 INCHES FROM CENTERLINE.						1	L	7	1 	3O			NT	A73EU 					 
1995091500414	19950915	00414	SO 	1995	9	15	95ZZZX4579 	1	19950809	G	5711		SPAR 			PIPER 	PA28 	PA28180 	7102808	SO 										LT WING	CORROSION 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	5235L	2214 				284529				CORROSION FOUND ON MAIN WING SPAR BEHIND FUEL TANK. SUBMITTER RECOMMENDS TANK REMOVAL FOR SPAR INSPECTION EVERY 5 YEARS	.					1	L	7	1 	3O				2A13 					 
1995091500415	19950915	00415	SO 	1995	9	15	95ZZZX4580 	1	19950706	G	7603	90113	PUSH/PULL TUBE 			AYRES 	S2 	S2RR1340NORM	0970210	SO 										ENG THROTTLE	DISCONNECTED 	G		A		A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			AG	AGRICULTURE 	1			SW	11	5654X					1854R				AIRCRAFT ENGAGED IN AERIAL APPLICATION OF CHEMICALS (DRY FERTILIZER). EXPERIENCED LOSS OF ENGINE POWER AND MADE A FORCE	D LANDING. THE AIRCRAFT WAS DESTROYED BY FIRE AND THE PILOT WAS NOT INJURED. INVESTIGATION OF THE AIRCRAFT REVEALED TH	E THROTTLE CONTROL PUSH/PULL TUBE SEPARATED FROM THE CARBURETOR THROTTLE ARM. DRILLED BOLT, NUT, AND COTTER PIN WERE MI	SSING. SUBMITTER SUGGESTS BOLT INSTALLATION SHOULD BE CHECKED FREQUENTLY.			1	L	7	1 	3R				A3SW 					 
1995091500416	19950915	00416	NE 	1995	9	15	95ZZZX4581 	2	19950710	G	7322		INLET SCREEN 			AYRES 	S2 	S2RR1340NORM	0970210	SO 	PWA 	R1340 	R1340AN1 	52016	NE 					CARBURETOR	CLOGGED 	G		A	KOIG	A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			AG	AGRICULTURE 	1			SW	11	8972Q					1642R				AIRCRAFT EXPERIENCED LOSS OF ENGINE POWER DURING AERIAL APPLICATION. AIRCRAFT WAS SUBSTANTIALLY DAMAGED DURING A FORCED	 LANDING. INVESTIGATION REVEALED PARTICLES OF RUBBER ON CARBURETOR FUEL INLET SCREEN AND CARBURETOR BOWL CONTAINED WATE	R AND RUST CONTAMINATES. SUBMITTER RECOMMENDS 137 FAR OPERATORS CHECK FUEL SUPPLY FOR CONTAMINATION AND FUEL HOSES FOR 	SERVICE ABILITY. FUEL SCREENS AND FUEL BOWL SHOULD BE THOROUGHLY INSPECTED DURING 100-HOUR AND ANNUAL INSPECTION.			1	L	7	1 	3R	3	R		A3SW 	5E2				 
1995091500417	19950915	00417	EA 	1995	9	15	95ZZZX4582 	1	19950809	G	8110	12768	BEARING 			SCWZER	G164 	G164B 	3952802	EA 	PWA 	R985 	R985AN14B 	52008	NE 					SUPERCHARGER	FAILED 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CL	CLIMB 	1			CE	09	6771Q		496 			28013	18437			ENGINE EXPERIENCED TOTAL LOSS OF POWER SHORTLY AFTER TAKEOFF. AIRCRAFT CRASHED. NO INJURY TO PIC, AIRCRAFT INCURRED SU	BSTANTIAL DAMAGE. SUBSEQUENT INSPECTION DISCLOSED THE FAILURE OF THE THREE SUPERCHARGER IMPELLER SUPPORT BEARINGS, PN 1	2768. TWENTY-NINE DAMAGED ROLLERS RETRIEVED FROM BLOWER SUPPORT BEARING CAVITY. ENGINE TT: 7,245.5 HOURS. ENGINE T.S	.O.: 495.5 HOURS.			1	Q	7	1 	3R	3	R		1A16 	5E1				 
1995091500418	19950915	00418		1995	9	15	95ZZZX4583 	1	19950821	G	7922	75944	VALVE 								LYC 	O320 	O320E2D 	41508	EA 					THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03			891 				L2974527A			WHILE COMPLYING WITH LYCOMING SB NR 518C DURING 100-HOUR INSPECTION, FOUND THERMOSTATIC OIL BYPASS VALVE HAD LOOSE CRIMP	 NUT, ACCOMPLISHED REPAIR IAW LYCOMING SERVICE INSTRUCTION NR 1423 AND REINSTALLED.										3	O			E274				 
1995091500419	19950915	00419	EA 	1995	9	15	95ZZZX4584 	2	19950731	G	8530	LW190001	VALVE 			PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E2A 	41508	EA 					ENGINE	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CE	03	95207	1311 				2825842	L2544527A			VALVE STEM CRACKED JUST BELOW HEAD OF VALVE. THE HEAD OF THE VALVE FALLING INTO THE CYLINDER CAUSED MAJOR DAMAGE TO THA	T CYLINDER. SUBMITTER SUGGESTS DETONATION MAY HAVE BEEN A FACTOR. NOTE: AUTO FUEL WAS BEING USED.					1	L	7	1 	3O	3	O		2A13 	E274				 
1995091500420	19950915	00420	SO 	1995	9	15	95ZZZX4585 	1	19950824	G	3213	6704212	FITTING 			PIPER 	PA28 	PA28R200 	7102811	SO 										LT AFT TRUNNION	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	2818R	5380 				28R35299				ONE-HUNDRED HOUR INSPECTION FOUND LT AFT GEAR SUPPORT BROKEN IN HALF. NO FURTHER DAMAGE FOUND. NO REPORTED DIFFICULTIE	S OR HARD LANDINGS BY PILOTS.					1	L	7	1 	3O				2A13 					 
1995091500421	19950915	00421	SW 	1995	9	15	95ZZZX4586 	1	19950817	G	8120	60051004	HOUSING 	ROTOMASTER 	646396 	MOONEY	M20 	M20K 	5870220	SW 	CONT 	O360 	TSIO360GB 	17025	SO 					TURBOCHARGER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	5659L		555 		010902	250762	309812			WHILE COMPLYING WITH AD 82-27-03 IAW ROTO MASTER SERVICE LETTER 27A, RAY JAY SERVICE LETTER 21, FOUND TURBO HOUSING CRAC	KED BEYOND ALLOWABLE LIMITS. THIS SCROLL IS THE NEW TYPE TURBINE HOUSING.					1	L	7	1 	3O	3	O		2A3 	E9CE				 
1995091500422	19950915	00422	SO 	1995	9	15	95ZZZX4587 	1	19950116	G	2740	62701104	CONTROL CABLE 			PIPER 	PA28 	PA28180 	7102808	SO 										TRIM SERVO	FRAYED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	56717	3178 				287405028				AIRCRAFT EQUIPPED WTIH PIPER ELECTRIC TRIM SERVO. FOUND CABLE 40 PERCENT BROKEN THROUGH RT SERVO PULLEYS AND DRIVE MECH	ANISM. SERVO AND CABLE DAMAGE LOCATED AFT OF BAGGAGE COMPARTMENT BULKHEAD NEXT TO BATTERY BOX. CORROSION DOES NOT SEEM	 TO BE FACTOR. SUBMITTER SUGGESTS BROKEN CABLE WOULD RESULT IN LOSS OF TRIM CONTROL AND POSSIBLE PITCH CONTROL DIFFICUL	TY.			1	L	7	1 	3O			 	2A13 					 
1995091500423	19950915	00423	SW 	1995	9	15	95ZZZX4588 	1	19950818	G	5540	91402009	HINGE FITTING 		450000 	MOONEY	M20 	M20C 	5870208	SW 										VERT STAB UPPER	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	5888Q	2910 				3152				LOWER ATTACHMENT EAR OF UPPER RUDDER ATTACH HINGE ASSY ON VERTICAL STABILIZER FOUND CRACKED DURING ANNUAL INSPECTION. F	URTHER INVESTIGATION REVEALED LOWER EAR OF LOWER HINGE BRACKET, PN 914002-13, OF VERTICAL STABILIZER CRACKED ALSO. IMPR	OPER RUDDER BOLT INSTALLATION AND RUDDER INSTALLATION SUSPECT CAUSE.				1	L	7	1 	3O				2A3 					 
1995091500424	19950915	00424	SO 	1995	9	15	95ZZZX4589 	1	19950816	G	7602	1240700	CONTROL CABLE 			PIPER 	PA18 	PA18150 	7101828	SO 										MIXTURE CONTROL	LOOSE 	G				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			GL	03	4158W	136 				1809102				ENGINE LOST A SLIGHT AMOUNT OF POWER WHILE PULLING A BANNER. PILOT MADE EMERGENCY LANDING, NO DAMAGE TO AIRCRAFT. MIXT	URE CONTROL CABLE SLIPPED IN HOLD DOWN CLAMP. MIXTURE CONTROL CLAMP WAS RETORQUED, CABLE WAS RE-RIGGED. THROTTLE CABLE	 WAS ALSO RE-RIGGED. ENGINE WAS GROUND RUN, TEST FLOWN, AND FOUND AIRWORTHY.				1	H	7	1 	3O			 	1A2 					 
1995091500425	19950915	00425	SO 	1995	9	15	95ZZZX4590 	1	19950116	G	5720		GAP SEAL 			PIPER 	PA28 	PA28180 	7102808	SO 										LT WING FLAP	DAMAGED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	56717	3061 				287405028				LT WING, TRAILING EDGE INBOARD AT ROOT, FLAP-TO-WING GAP SEAL. INSTALLATION IAW STC SA780GL AND STC SA928GL. WHEN FLAP	 LOWERED, GAP SEAL WAS CRUMPLED AND JAMMED INTO GAP AREA CAUSING POSSIBLE BINDING OF FLAP. RT WING GAP SEAL CRACKED AT 	7 RIVETS ALONG LENGTH OF REAR SPAR. SUSPECT MATERIAL FATIGUE AND VIBRATION OR MISALIGNMENT. SUBMITTER RECOMMENDS ALERT	 NOTICE AND INSPECTION FOR CLEARANCE.			1	L	7	1 	3O				2A13 					 
1995091500426	19950915	00426	EA 	1995	9	15	95ZZZX4591 	2	19950815	G	7322		CARBURETOR TUBE 	FACET 	MA4SPA 	CESSNA	172 	172P 	2072436	CE 	LYC 	O320 	O320D2J 	41508	EA 					ACCEL PUMP	LOOSE 	D				A				UNSCHED LANDING 				O			OTHER 			NR	NOT REPORTED 	1			NM	01	54635		1715 		CK49853	17275018	RL1496639A			RPM COULD NOT BE REDUCED BELOW 2,000 RPM IN-FLIGHT, NECESSITATING POWER-OFF LANDING. INSPECTION REVEALED THE CARBURETOR	 ACCELERATOR PUMP DISCHARGE TUBE HAD COME LOOSE AND LODGED IN THE THROTTLE VALVE PREVENTING FULL CLOSURE OF THROTTLE. T	HE OVERHAUL MANUAL SPECIFIES THE TUBE IS HELD IN PLACE WITH LOCTITE ONLY. SUBMITTER RECOMMENDS REDESIGN SO THE TUBE IS 	MECHANICALLY HELD IN PLACE OR ELSE A REGULAR INSPECTION INTERVAL TO DETERMINE IF THE TUBE IS LOOSE. ENGINE TT: 3,882 H	OURS. ENGINE TSOH: 1,714 HOURS.		1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995091500427	19950915	00427	CE 	1995	9	15	95ZZZX4592 	1	19950812	G	7810	125401214	SHROUD ASSY 		CL560200101 	CESSNA	172 	172RG 	2072438	CE 										ENGINE EXHAUST	CHAFE MUFFLER 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	6141R					172RG0093				SCREWS ATTACHING THE SHROUD TO THE MUFFLER CAME OUT CAUSING SHROUD TO SIT ON THE COILS OF THE MUFFLER. IT THEN RUBBED T	HROUGH COILS. THIS AIRCRAFT IS ON A 50-HOUR INSPECTION PROGRAM, SO IT HAPPENED WITH 50 HOURS.					1	H	7	1 	3O				3A17 					 
1995091500428	19950915	00428	CE 	1995	9	15	95ZZZX4593 	2	19950818	G	8530	SA632310S	GASKET 			MOONEY	M20 	M20K 	5870220	SW 	CONT 	O360 	TSIO360MB 	17025	CE 					ROCKER COVER	SCREWS LOOSE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	52202	16 				251204				AFTER TALKING TO ANOTHER MECHANIC WHO HAD SIMILAR PROBLEM (LOOSE ROCKER COVER SCREWS), CHECKED SUBJECT AIRCRAFT AND FOUN	D LIKE CONDITION. DUE TO SILICONE GASKETS BEING INSTALLED, FOUND SCREWS WOULD LOOSEN OVER TIME. RE-INSTALLED SCREWS US	ING LOCKTITE TO PREVENT RECURRENCE. SUBMITTER STATED IT SHOULD BE NOTED THESE GASKETS DID NOT COME WITH SPECIAL INSTALL	ATION INSTRUCTIONS TO THIS EFFECT. IF CONDITION IS ALLOWED TO EXIST, COVER SEPARATION AND OIL LOSS COULD RESULT.			1	L	7	1 	3O	3	O		2A3 	E9CE				 
1995091500429	19950915	00429	SW 	1995	9	15	95ZZZX4594 	2	19950829	G	8500		ENGINE 			CESSNA	195 	195 	2073102	CE 	JACOBP	R755 	R755B2 	35007	SW 					POWER SECTION	FAILED 	H				A				UNSCHED LANDING 				K	B	E	FLUID LOSS 	SMOKE/FUMES/ODORS/SPARKS 	VIBRATION/BUFFET 	NR	NOT REPORTED 	1			SW	01	9368A					7447	11465			PILOT REPORTED SUDDEN SEVERE VIBRATION APPROXIMATELY 20 MINUTES INTO FLIGHT FOLLOWED WITHIN 1-2 MINUTES BY COMPLETE LOSS	 OF OIL PRESSURE TO ZERO. APPROXIMATELY 6 MINUTES TO LANDING WITH RISE IN OIL TEMP OFF SCALE, INCREASED VIBRATION, BURN	ING ODOR AND PROGRESSIVE POWER LOSS. HAD NORMAL RECENT FLIGHTS, NORMAL START, RUN-UP, AND INITIAL FLIGHT BEFORE PROBLEM	 STARTED. BRIEF INSPECTION AFTER LANDING DID NOT IDENTIFY PROBLEM, ALTHOUGH THERE WAS A LARGE AMOUNT OF OIL ALONG BELLY	 AND SOME ON PROP. MECHANICS CURRENTLY WORKING TO ASCERTAIN PROBLEM.		1	H	7	1 	3R	3	R	NC	A790 	TC237				 
1995091500430	19950915	00430	SO 	1995	9	15	95ZZZX4595 	1	19950812	G	3246	40120	WHEEL HALF 	PARKERHANFIN		PIPER 	PA34 	PA34200T 	7103406	SO 										RT MLG	CRACKED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	36657					347870352				OUTBOARD WHEEL HALF HAS CORROSION AT FLANGE RADIUS, AND HAS A 2 INCH CRACK IN RADIUS.						1	L	7	2 	3O				A7SO 					 
1995091500431	19950915	00431	EA 	1995	9	15	95ZZZX4596 	2	19950906	G	8530		VALVE 			PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E3D 	41508	EA 					ENGINE EXHAUST	FAILURE 	G	S			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	07	1689J	1604 				2824092	L3330627			EXHAUST VALVE FAILURE. ENGINE HAS 1,601 HOURS SINCE NEW.						1	L	7	1 	3O	3	O		2A13 	E274				 
1995091500432	19950915	00432	SO 	1995	9	15	95ZZZX4597 	2	19950905	G	8530	653426A4	CYLINDER 			CESSNA	175 	175A 	2072504	CE 	CONT 	O300 	GO300* 	17022	SO 					NR 2 CYLINDER	GUIDE WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	6821E	84 				56321	14017			VALVE GUIDE WORN EXCESSIVELY. WOULD NOT PASS COMPRESSION CHECK. OWNER STATED HE WAS NOT USING AUTO FUEL. VALVE GUIDE 	WAS REPLACED.					1	H	7	1 	3O	3	O		3A17 	E298				 
1995091500695	19950915	00695	SW 	1995	9	15	95ZZZX4598 	1	19950901	G	3233	1057005G	MOTOR 	DUKES 		MOONEY	M20 	M20J 	5870219	SW 										MLG ACTUATOR	BRUSH BROKEN 	B			HBKR	O				OTHER 				O			OTHER 			AP	APPROACH 	1			SW	11	201WB	8 			0144	240107				AIRCRAFT HAD A GEAR UP LANDING. FOUND A BRUSH BROKEN IN THE LANDING GEAR ACTUATOR MOTOR.						1	L	7	1 	3O				2A3 					 
1995091500696	19950915	00696	SO 	1995	9	15	95ZZZX4599 	2	19950818	G	7414	6220	MAGNETO 	SLICK 		CESSNA	210 	T210N 	2073456	CE 	CONT 	O520 	TSIO520R 	17040	SO 					ENG LT MAG	FAILED 	H				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			WP	17	37AA	348 			91030039	21062989				ENGINE BECAME ROUGH IN-FLIGHT. FOUND WOULD RUN BETTER ON RT MAG ONLY. INVESTIGATION FOUND WHEN LEFT MAG REMOVED. IT W	AS DESTROYED BY AN INTERNAL FIRE. SUSPECT OIL LEAK INTO PRESSURED MAG AND IGNITED.					1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995091500697	19950915	00697	CE 	1995	9	15	95ZZZX4600 	1	19950811	G	3230	130909B130	BOLT 			BEECH 	90 	C90A 	1152911	CE 										LT MLG STRUT	MISSING 	D				K				NONE 				O			OTHER 			LD	LANDING 	1			WP	25	490JT	1630 				LJ1312				LEFT MAIN LANDING GEAR ASSEMBLY COLLAPSED ON LANDING. THE LOWER DRAG LINK TO STRUT ASSEMBLY BOLT WAS MISSING. IT IS NO	T CLEAR WHY THE BOLT WAS MISSING. THE BOLT WAS PRESENT 9 HOURS AND 28 LANDINGS PRIOR.					1	L	7	2 	3T			RT	3A20 					 
1995091500698	19950915	00698	NE 	1995	9	15	95ZZZX4601 	2	19950823	G	7250	311046201	RING SUPPORT 		311440701 	CESSNA	500 	550 	2076604	CE 	PWA 	JT15 	JT15D4 	52112	NE 					GAS GEN CASE	BROKEN 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	84EA	1163 				5500484	71375			DURING PHASE 25/HOT SECTION INSPECTION, IMPACT DAMAGE WAS NOTED ON THE NR 2 TURBINE BLADES. FURTHER DISASSEMBLY REVEALE	D 2 SECTIONS OF THE DEFLECTOR RING HAD BROKEN OFF. THESE SECTIONS WERE APPROXIMATELY 1.50 INCHES LONG AND LOCATED AT TE	N O'CLOCK AND 1:30 O'CLOCK IN LINE WITH DIFFUSER PIPES. THE DEFLECTOR RING WAS ALSO BROKEN IN HALF AT THE TEN O'CLOCK P	OSITION. ONE MISSING RING SECTION WAS FOUND LODGED IN THE GAS GENERATOR CASE. THE OTHER TRAVELLED AFT RESULTING IN DAM	AGE TO THE HIGH TURBINE ASSY AND LOW TURBINE BALANCE ASSY. NO COCKPIT INDICATION OF FAILURE WAS NOTED.		1	L	7	2 	4F	4	F		A22CE 	E1NE				 
1995091500699	19950915	00699	NE 	1995	9	15	95ZZZX4602 	2	19950823	G	7250	3028601	BLADE 		3023411 	CESSNA	500 	550 	2076604	CE 	PWA 	JT15 	JT15D4 	52112	NE 					HP TURBINE	DAMAGED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	84EA	1869 			5M028	5500484	71375			DURING PHASE 25/HOT SECTION INSPECTION, ALL 71 HIGH TURBINE BLADES WERE FOUND NICKED, DENTED AND BROKEN BY IMPACT DAMAGE	 FROM DEFLECTOR - RING FAILURE. NUMEROUS BLADES WERE MISSING FORWARD ONE-QUARTER OF OUTBOARD LEADING EDGE. NO COCKPIT 	INDICATION WAS NOTED AS TIP CLEARANCES FOR REMAINDER OF BLADE WAS STILL IN TOLERANCE. ALL BLADES WERE REPLACED WITH NEW	.			1	L	7	2 	4F	4	F		A22CE 	E1NE				 
1995091500700	19950915	00700	NE 	1995	9	15	95ZZZX4603 	2	19950823	G	7250	3131060C212	SHROUD SEGMENT 		3031461 	CESSNA	500 	550 	2076604	CE 	PWA 	JT15 	JT15D4 	52112	NE 					HP TURBINE	GOUGED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	84EA	1869 			PWC9001700	5500484	71375			DURING PHASE 25/HOT SECTION INSPECTION, ALL HIGH PRESSURE TURBINE SHROUD SEGMENT WIRE FOUND GOUGED. DAMAGE WAS CAUSED B	Y FAILURE OF DEFLECTOR RING AND RESULTING HIGH TURBINE BLADE DAMAGE. ALL SHROUD SEGMENTS WERE REPLACED.					1	L	7	2 	4F	4	F		A22CE 	E1NE				 
1995091500701	19950915	00701	NE 	1995	9	15	95ZZZX4604 	2	19950823	G	7250	3022202	BLADE 		3022722 	CESSNA	500 	550 	2076604	CE 	PWA 	JT15 	JT15D4 	52112	NE 					LP TURBINE	DAMAGED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	84EA	5736 	1869 		6M040	5500484	71375			DURING PHASE 25/HOT SECTON INSPECTION, IMPACT DAMAGE WAS FOUND ON 2ND STAGE LOW TURBINE. THIS WAS CAUSED BY FAILURE OF 	DEFLECTOR RING. UNIT WAS SENT TO P & WC, DISASSEMBLED, BLENDED AND REASSEMBLED. NO COCKPIT INDICATIONS OF DAMAGE WERE 	NOTED PRIOR TO HOT SECTION INSPECTION.				1	L	7	2 	4F	4	F		A22CE 	E1NE				 
1995091500702	19950915	00702	WP 	1995	9	15	95ZZZX4605 	2	19950712	G	7250	31038393	SEAL PLATE 		31033155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		5829 			1233151925		P70110C			DURING SCHEDULED INSPECTION, FOUND SEAL PLATE CRACKED 5 PLACES. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROV	IDE INCREASED SEAL PLATE TENSION AGAINST FIRST STAGE ROTOR ASSEMBLY. INCREASED TENSION ON THE SEAL FLANGE RESULTS IN CR	ACKING AT THE SEAL PLATE FLANGE EDGE. NO SIGNS OF ABNORMAL/OVERTEMP OPERATION. SUBMITTER SUGGESTS ENGINEERING REVIEW C	AUSE/EFFECT. NOTE: THIS IS A CRITICAL LIFE-LIMITED COMPONENT WITH LIMIT OF 20,000 CYCLES. THIS IS THE 7TH SEAL FOUND 	CRACKED. CSN: 5,865.							4	T			E4WE				 
1995091500703	19950915	00703	WP 	1995	9	15	95ZZZX4606 	2	19950721	G	7250	31038393	SEAL PLATE 		31033155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		5952 			1233151955		P70106C			DURING INSPECTION/REPAIR FOR LOW POWER, FOUND SEAL PLATE CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO IN	CREASE SEAL PLATE TENISON AGAINST FIRST STAGE ROTOR ASSEMBLY. INCREASED TENSION OF THE SEAL FLANGE RESULTS IN CRACKING 	AT THE EDGE PROPOGATING RADIALLY INWARD. SUBMITTER SUGGESTS ENGINEERING REVIEW CAUSE/EFFECT. NOTE: THIS IS A CRITICAL	 LIFE-LIMITED COMPONENT. LIFE LIMIT IS 20,000 CYCLES. THIS IS THE EIGHTH SEAL FOUND CRACKED. TOTAL CYCLES, 7,221.								4	T			E4WE				 
1995091500704	19950915	00704	WP 	1995	9	15	95ZZZX4607 	2	19950821	G	7250	31038939	SEAL PLATE 		31033155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		6135 			1233151943		P70105C			DURING INSPECTION/REPAIR FOR LOW POWER, FOUND SEAL PLATE CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO IN	CREASE SEAL PLATE TENSION AGAINST FIRST STAGE ROTOR ASSEMBLY. INCREASED TENSION ON THE SEAL FLANGE RESULTS IN CRACKING 	AT THE EDGE PROPOGATING RADIALLY INWARD. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING REVIEW CAUSE/EFFECT. NOTE: THIS	 IS A CRITICAL LIFE-LIMITED COMPONENT. LIMIT IS 20,000 CYCLES. THIS IS THE 9TH SEAL PLATE FOUND CRACKED. TOTAL CYCLE	S, 7,427.							4	T			E4WE				 
1995091500705	19950915	00705	CE 	1995	9	15	95ZZZX4608 	1	19950825	G	3520	99120575	ALTITUDE SWITCH 			CESSNA	500 	550 	2076604	CE 										OXYGEN SYSTEM	DEFECTIVE 	B			CWQR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			GL	05	109GA	4685 			0598	5500124				DURING PHASE 5 INSPECTION, OXYGEN SYSTEM FAILED FUNCTIONAL CHECK. OXYGEN MASK DEPLOYED AT 12,400 FEET WHEN THEY SHOULD 	DEPLOY AT 13,500 FEET, PLUS OR MINUS 600 FEET. DEFECTIVE BAROMETRIC ALTITUDE SWITCH CAUSED DISCREPANCY. INTERNAL FAILU	RE OF WEAKNESS OF SWITCH LIKELY CAUSE.				1	L	7	2 	4F				A22CE 					 
1995091500706	19950915	00706	CE 	1995	9	15	95ZZZX4609 	1	19950829	G	3240	5161651	VALVE 			RKWELL	NA265 	NA26540 	6402608	CE 										POWER BRAKE	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	306NT		37 			282030				VALVE WAS REMOVED FROM AIRCRAFT DUE TO INTERNAL BYPASSING CAUSING HYDRAULIC PUMP TO CYCLE CONTINUOUSLY. UNIT TIME IN SE	RVICE SINCE REPAIR: 37.3 HRS. SUBMITTER STATED LOW-TIME FAILURES OF THESE UNITS HAS BEEN COMMON IN FLEET OF 17 AIRCRAF	T. INTERNAL BYPASSING CONDITIONS ARE COMMON IN BOTH OVERHAULED AND REPAIRED UNITS. AIRCRAFT TOTAL TIME: 10,697.7 HRS.	 TOTAL LANDINGS: 7,306.			2	L	7	2 	4J				A2WE 					 
1995091500707	19950915	00707	NE 	1995	9	15	95ZZZX4610 	2	19950817	G	7240	616315	COMB CHAMBER 			DOUG 	DC9 	DC9* 		WP 	PWA 	JT8 	JT8D17 	52049	NE 					REAR FLANGE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		32050			1242		688018			INSPECTION FOUND COMBUSTION CHAMBER OUTER CASE REAR FLANGE CRACKED BETWEEN BOLT HOLES. REF AD 87-11-07 AND ASB5676. TC	: 26,507.					2	L	7	2 	4F	4	F		A6WE 	E2EA				 
1995020300316	19950203	00316	SO 	1995	2	3	95ZZZX479 	1	19950108	G	3230	8628003	LINK ASSY 			PIPER 	PA44 	PA44180 	7104402	SO 										NLG	PIN SHEARED 	G	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	2197Z	200 				447995293				PIPER ISSUED NOSE GEAR MODIFICATION KIT NR 764-378V HAS TO CHANGE THE COTTER PIN IN THE LOWER NOSE GEAR LINK ASSY TO A L	ONGER SIZE. THE 424-051 COTTER PIN IS TOO SMALL AND HAS CAUSED A NOSE GEAR FAILURE DUE TO THE COTTER PIN SHEARING OFF A	ND THE NUT BACKING OFF THE DOWNLOCK ASSY. KIT WAS INSTALLED APPROXIMATELY 200 HOURS EARLIER.				1	L	7	2 	3O				A19S0 					 
1995020300318	19950203	00318	CE 	1995	2	3	95ZZZX481 	1	19950109	G	7810	08507126	TUBE 			CESSNA	401 	401 	207590C	CE 										RT EXHAUST	CRACKED 	E		A		A				UNSCHED LANDING 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			SW	07	3260Q	2520 				4010060				PILOT NOTICED SPARKS COMING FROM RIGHT INBOARD LOWER NACELLE FORWARD OF WING LEADING EDGE. LANDING WAS MADE WITHOUT INC	IDENT. INVESTIGATION REVEALED THE EXHAUST TUBE FROM THE RIGHT TRANSITION HEAD INBOARD TO THE SLIP JOINT ASSY HAD BULGED	 AND CRACKED TWO INCHES AFT OF THE CONNECTION TO THE SLIP JOINT ASSY (0850660-9). EXHAUST GASES BURNED THE CANTED WEB B	ULKHEAD BELOW THE HOLE THROUGH WHICH THE CRACKED TUBE PASSES. THE NACELLE SKIN NEARBY WAS ALSO BURNED. ENGINE MOUNT RA	IL WAS NOT AFFECTED. NO WIRING OR ELECTRICAL SYSTEM WAS AFFECTED. 'SPARKS' ASSUMED TO BE MOLTEN METAL DROPS. AREA 2 I	NCHES BY 2 INCHES WAS MELTED IN CANTED BULKHEAD.	1	L	7	2 	3O				A7CE 					 
1995020300322	19950203	00322	EU 	1995	2	3	95ZZZX485 	1	19950109	G	5713	NOR75081	STRINGER 			PARTEN	P68 	P68 		EU 										TOP WING SKIN	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	28FG	3621 				325180B				ALL 8 STRINGERS (4 EACH WING) HAVE MULTIPLE CRACKS/BREAKS. THESE STRINGERS ARE ONLY VISIBLE BY UNRIVETING WING SKIN OR 	REMOVING ENGINE FIREWALL. THE MATERIAL THICKNESS OF .020 INCH APPEARS TO BE INADEQUATE.					1	H	7	2 	3O				A31EU 					 
1995020300323	19950203	00323	CE 	1995	2	3	95ZZZX486 	1	19950111	G	3230	35815109	CONTROL CABLE 			BEECH 	35 	V35TC 	1151540	CE 										MLG UPLOCK	FRAYED 	B			FE4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	411EG					D8184				DURING ROUTINE INSPECTION, FOUND BOTH LEFT AND RIGHT MAIN LANDING GEAR UPLOCK CABLES WITH STRANDS BROKEN. LEFT CABLE CA	USE UNKNOWN. RIGHT CABLE POSSIBLE CORROSION CAUSE. LEFT CABLE TT 541. RIGHT CABLE TT 4450.					1	L	7	1 	3O			 	3A15 					 
1995020300324	19950203	00324	SO 	1995	2	3	95ZZZX487 	1	19950112	G	2910	11200302	SWITCH 	PARKERHANFIN		PIPER 	PA46 	PA46350P 		SO 										HYD PUMP	INTERMITTENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	801SW	183 				4622073				THIS SWITCH WAS CHANGED 183 HOURS AGO PER SB 964A, PART I. NEVER HAD ANY PROBLEMS UNTIL NEW SWITCH WAS INSTALLED, THEN,	 SWITCH INTERMITTENT. HAVE TO TAP SWITCH AT TIMES TO MAKE HYDRAULIC PUMP WORK, GIVES NO WARNING WHEN IT FAILS, PIPER PN	 765-457. PARKER HANNIFIN PN 112-00302.				1	L	7	1 	3O			RT	A25SO 					 
1995020300325	19950203	00325	SO 	1995	2	3	95ZZZX488 	2	19950105	G	8530	629117	ROTOR CAP 								CONT 	O520 	IO520* 	17032	SO 					VALVE	DEFECTIVE 	B			YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11										THREE EACH VALVE ROTOR CAPS RECEIVED ON 3 NEW CYLINDERS. TWO OF THE 3 WILL NOT ROTATE. ONE OF THE 3 HAS NO INTERNAL PA	RTS. ONE VALVE ROTOR CAP BROKEN. TOTAL TIME 350 HOURS.										3	O			E5CE				 
1995020300326	19950203	00326	SO 	1995	2	3	95ZZZX489 	2	19950105	G	8520	643629	RETAIN PLATE 								CONT 	O520 	IO520* 	17032	SO 					CRANKSHAFT	DEFECTIVE 	B			YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11										INSPECTION FOUND 12 EACH TORSIONAL DAMPENER RETAINING PLATES FAULTY. THEY WERE MARKED BY CONT. AS REJECT PARTS, BUT SHI	PPED TO US AS AIRWORTHY PARTS.										3	O			E5CE				 
1995020300327	19950203	00327	SO 	1995	2	3	95ZZZX490 	2	19950105	G	8530	646283	VALVE 								CONT 	O520 	IO520* 	17032	SO 					CYLINDER INTAKE	DEFECTIVE 	B			YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11										INSPECTION FOUND TWO INTAKE VALVES DEFECTIVE. ONE VALVE HAS OUT-OF-ROUND STEM. ONE VALVE HAS WARPED VALVE HEAD.											3	O			E5CE				 
1995020300335	19950203	00335	SO 	1995	2	3	95ZZZX498 	1	19950111	G	5751	4019013	SPAR 			PIPER 	PA31 	PA31310 	7103103	SO 										RT BL 175.12	CRACKED 	B			J8SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	64BR	11898				31365				WHILE COMPLYING WITH PIPER SB 974, AILERON HINGE INSPECTION AND REPLACEMENT, FOUND AILERON SPAR, DOUBLER AND RIB CRACKED	 UNDER INBOARD HINGE BRACKET. SUBMITTER RECOMMENDS AIRWORTHINESS DIRECTIVE FOR MANDATORY COMPLIANCE WITH THIS SERVICE B	ULLETIN.				1	L	7	1 	3O			RT	A20SO 					 
1995020300336	19950203	00336	SO 	1995	2	3	95ZZZX499 	1	19950111	G	5712	4042307	RIB 			PIPER 	PA31 	PA31310 	7103103	SO 										RT STAB BL 490	CRACKED 	B			J8SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	64BR	11898				31365				DURING 100-HOUR INSPECTION, FOUND RIB INSIDE RT WHEELWELL CRACKED. ALSO, FOUND RT LANDING GEAR UPPER BUMPER ASSY, PN 43	016-01, CRACKED, AND, SKIN ABOVE THE BUMPER ASSY CRACKED. SUSPECT CAUSE - LANDING GEAR COMING INTO UPLOCK TOO HARD AND 	HITTING UPPER BUMPER ASSY. COULD NOT DUPLICATE ON GROUND AND DURING TEST FLIGHT, GEAR UP OPERATIONAL NORMAL.				1	L	7	1 	3O			RT	A20SO 					 
1995020300338	19950203	00338		1995	2	3	95ZZZX501 	4	19950112	G	2215	1C4701518P	SERVO 	CENTURY 																AUTOPILOT	CORRODED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03					8734					SERVO WAS SENT IN FOR TEST AND REPAIR AS NECESSARY. UNIT WAS HEAVILY CORRODED. ENGAGE SOLENOID WAS STICKING IN ENGAGED	 POSITION. CLUTCH SETTING FOUND AT 750 POUNDS AND ERRATIC (50 TO 65 POUNDS DEPENDENT UPON ROTATION POINT. SHOULD BE SE	T AT 37 PLUS OR MINUS 4 POUNDS.) UNIT FAILED BECAUSE RECOMMENDED ANNUAL/1,000 HOUR TESTING AND RECERTIFICATION NOT BEIN	G DONE.																 
1995020300339	19950203	00339	EA 	1995	2	3	95ZZZX502 	2	19950118	G	8550		LINE 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					REAR CASE OIL	CHAFE/BURN 	H				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			SW	99	132MF					317782072				DURING FLIGHT, PILOT NOTICED SMOKE COMING FROM OUTBOARD OF RIGHT NACELLE. PILOT SHUT DOWN ENGINE AS A PRECAUTION AND RE	TURNED TO BASE. MAINTENANCE DISCOVERED OIL PRESSURE LINE FROM REAR CASE TO FIREWALL HAD COME IN CONTACT WITH EXHAUST WH	ICH BURNED A HOLE THROUGH THE FIRESLEEVE AND THEN THE HOSE CAUSING OIL TO BURN ON THE EXHAUST.				1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995092200172	19950922	00172	NE 	1995	9	22	95ZZZX5025 	2	19950901	G	8510	408119904	GEAR 		408136005 						LYC 	LTS101	LTS101650B1 	41560	NE 					OUTPUT	CHROME DEFECT 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	07					87D037					CHROME PLATING ON PN 4-081-199-04 BEARING JOURNAL WAS FOUND TO HAVE AN AIR POCKET IN CHROME APPROXIMTELY .1250 INCH FROM	 END OF PART. DISCONTINUITY WAS ON A NON-FUNCTIONAL SURFACE AND PART WAS SALVAGED BY REMOVING ALL CHROME IN THIS AREA. 	 THIS IS NOT THE FIRST INSTANCE OF PROBLEMS RANGING FROM LEAKING MASKING TO AIR POCKETS IN CHROME FROM THIS VENDOR.									3	U			E5NE				 
1995092200173	19950922	00173	SO 	1995	9	22	95ZZZX5026 	1	19950831	G	1420	4090A	BOLT 	PARKERHANFIN		PIPER 	PA34 	PA34200 	7103405	SO 										LT MLG WHEEL	SHEARED 	B		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	15338					347350051				ON PRE-FLT, LT WHEEL ASSY FOUND WITH ONE BOLT HEAD SHEARED OFF. PIPER DOES OFFER A HEAVY DUTY WHEEL KIT FOR THIS AIRCRA	FT. DASH 90A IS A THREE-BOLT WHEEL, 40-120C IS A SIX-BOLT WHEEL.					1	L	7	2 	3O			 	A7SO 					 
1995092200174	19950922	00174	SO 	1995	9	22	95ZZZX5027 	1	19950823	G	5740	6244803	FITTING 			PIPER 	PA28 	PA28RT201 	7102818	SO 										WING ATTACH	CORRODED 	D	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	2142X	3665 				28R7918089				THE AFT WING SPAR ATTACHMENT FITTINGS WERE INSPECTED FOR CORROSION IAW SB NR 977. NO CORROSION WAS FOUND PER SB, HOWEVE	R, DURING THE REMOVAL OF CORROSION FROM THE INBOARD END OF THE RIGHT FLAP, THE SEALANT BETWEEN FUSELAGE AND THE FITTING 	WAS KNOCKED OFF REVEALING CORROSION ON THE AFT EDGE OF THE FITTING. FITTING WAS REMOVED AND CORROSION WAS NOTED WHERE T	HE FITTING ATTACHES TO THE AFT LOWER COCKPIT ASSEMBLY AND ON THE FORWARD SIDE BETWEEN THE FRAME AND THE FITTING. SUBMIT	TER RECOMMENDS SEALANT BE REMOVED FROM THE FUSELAGE AREA FOR INSPECTION OF THE OUTSIDE AREA OF THE FITTINGS DURING THE P	ERFORMANCE OF THE SB.	1	L	7	1 	3O				2A13 					 
1995092200175	19950922	00175	SO 	1995	9	22	95ZZZX5028 	2	19950903	G	7414	10357586	DISTRIBUTOR GEAR	BENDIX 	101630601 	CESSNA	402 	402C 	207590R	CE 	CONT 	O520 	TSIO520VB 	17040	SO 					MAGNETO	TEETH MISSING 	E	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	3249M	359 			A148802ER	402C0296	266997R			ENGINE HAD SLIGHT ROUGHNESS AND TIMING JUMP TO THE TIME OF FAILURE. FOUND DISTRIBUTOR GEAR TEETH MISSING. RECOMMEND SH	IMS BE CHECKED FOR GEAR FREEDOM AND UNIT BE REPLACED AT ONE-HALF OF SPECIFIC T.B.O. OF MAGNETO.					1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995092200176	19950922	00176	CE 	1995	9	22	95ZZZX5029 	1	19950816	G	3230	504501019	TORQUE TUBE 			CESSNA	421 	421B 	2076014	CE 										LT MLG WELL	BROKEN 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	421HW	6150 			578	421B0477				LEFT GEAR WELL MLG TORQUE TUBE FOUND BROKEN. SUBMITTER RECOMMENDS THIS PART BE REMOVED AND MAGNAFLUXED AT 5,000 HOURS A	ND EACH 1,000 HOURS THEREAFTER, ON ALL AFFECTED AIRCRAFT.					1	L	7	2 	3O				A7CE 					 
1995092200177	19950922	00177	SO 	1995	9	22	95ZZZX5030 	2	19950822	G	7414	10357426	DISTRIBUTOR BLK 		S6LN25 	PIPER 	PA34 	PA34200T 	7103406	SO 	CONT 	O360 	TSIO360EB 	17025	SO 					RT MAG	CRACKED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4377X		496 		A179401DR	347670352				DURING A MAGNETO 500-HOUR INSPECTION, ONE MOUNTING HOLE FOR THE DISTRIBUTER BLOCK WAS FOUND CRACKED.						1	L	7	2 	3O	3	O		A7SO 	E9CE				 
1995092200178	19950922	00178	SO 	1995	9	22	95ZZZX5031 	2	19950822	G	7414	10357426	DISTRIBUTOR BLK 		S6LN25 	PIPER 	PA34 	PA34200T 	7103406	SO 	CONT 	O360 	TSIO360EB 	17025	SO 					MAG LT	CRACKED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4377X		496 		A179405DR	347670352				DURING MAGNETO 500-HOUR INSPECTION, ONE MOUNTING HOLE OF THE DISTRIBUTOR BLOCK WAS FOUND CRACKED.						1	L	7	2 	3O	3	O		A7SO 	E9CE				 
1995092200179	19950922	00179	SO 	1995	9	22	95ZZZX5032 	1	19950831	G	5280	6709014	DOOR 			PIPER 	PA34 	PA34220T 	7103420	SO 										LT MLG	SEPARATION 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9249N	296 				3448048				BOTH MLG DOORS HAD FIBERGLASS LAMINATION SEPARATING FROM FRAME AT FORWARD UPPER CORNER AND AT HINGE LINE. FOUND DURING 	ANNUAL INSPECTION. SUSPECT EXCESSIVE VIBRATION CAUSED BY PROP WASH. WEAK CONSTRUCTION, RECOMMEND A METAL DOOR.					1	L	7	2 	3O				A7SO 					 
1995092200180	19950922	00180	SO 	1995	9	22	95ZZZX5033 	1	19950831	G	5280	6709015	DOOR 			PIPER 	PA34 	PA34220T 	7103420	SO 										RT MLG	SEPARATION 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9249N	296 				3448048				BOTH MLG DOORS HAD FIBERGLASS LAMINATION SEPARATING FROM FRAME AT FORWARD UPPER CORNER AND AT HINGE LINE. FOUND DURING 	ANNUAL INSPECTION. SUSPECT EXCESSIVE VIBRATION CAUSED BY PROP WASH. WEAK CONSTRUCTION, RECOMMEND A METAL DOOR.					1	L	7	2 	3O				A7SO 					 
1995092200181	19950922	00181	SO 	1995	9	22	95ZZZX5034 	2	19950831	G	8530	646743	PISTON 			PIPER 	PA34 	PA34220T 	7103420	SO 	CONT 	O360 	TSIO360KB 	17025	SO 					NR 2 CYLINDER	ERODED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9249N	296 				3448048	320200			OWNER REPORTED AN INCREASE IN OIL CONSUMPTION ON A SQUAK FOR ANNUAL INSPECTION. ENGINE APPEARED TO OPERATE NORMALLY ON 	RUN-UP. COMPRESSION CHECK REVEALED NR 2 CYLINDER AT 25 PSI. LEAKING PART RINGS. REMOVED CYLINDER AND FOUND NR 1 PISTO	N CROWN DAMAGE. FIFTY PERCENT OF EDGE SEEMED TO BE MELTED AWAY AND FIRST RING FLANGE BROKEN. SUSPECT MATERIAL DEFECT.				1	L	7	2 	3O	3	O		A7SO 	E9CE				 
1995092200182	19950922	00182	SO 	1995	9	22	95ZZZX5035 	1	19950829	G	2730	4035700	BELLCRANK 		4070400 	PIPER 	PA31T 	PA31T 	7103124	SO 										ELEVATOR	BEARING FAULTY 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	700LT	4500 				31T7920046				BEARINGS IN BELLCRANK ASSY, 40357-00, TIGHTENED UP, BUT NOT FROZEN COMPLETELY. BOLT THAT SECURES BELLCRANK TO BRACKETS,	 40704-00, AND 40704-01, WAS ROTATING WITH BELLCRANK. ROTATION OF BOLT CAUSED NUT TO LOOSEN, ALLOWING BELLCRANK TO SHIF	T, ROTATION OF BOLT ELONGATED BRACKETS' MOUNTING HOLES. BRACKETS MADE FROM ALUMINUM, SHOULD HAVE STEEL OR BRONZE BUSHIN	GS IN BOLT HOLES. NO INSPECTION REQUIREMENT IN MAINTENANCE. SCHEDULE TO LOOSEN CABLES AND CHECK BELLCRANK BEARINGS. R	EPLACED BRACKETS WITH NEW PARTS FROM APEX. REPLACED BEARINGS IN BELLCRANK.		1	L	7	2 	3T				A8EA 					 
1995092200183	19950922	00183	SO 	1995	9	22	95ZZZX5036 	1	19950829	G	2150	452691	BEARING 		501352 	PIPER 	PA31T 	PA31T 	7103124	SO 										COMPRESSOR DRIVE	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	700LT					31T7920046				FREON COMPRESSOR DRIVE SHAFT HAS 300-HOUR INSPECTION INTERVALS. BEARING FAILED CAUSING DRIVE SHAFT TO SHEAR AT SPLINE E	ND. DRIVE ASSY WAS 8.3 HOURS FROM NEXT INSPECTION. BEARING WAS OK AT LAST INSPECTION. TOTAL TIME ON BEARING WAS NOT K	NOWN. SUBMITTER SUGGESTED DRIVE ASSY BEARINGS SHOULD BE REPLACED AT 2,000-HOUR INTERVALS. MIGHT SAVE REPLACING $700 SH	AFT.			1	L	7	2 	3T				A8EA 					 
1995092200184	19950922	00184	CE 	1995	9	22	95ZZZX5037 	1	19950901	G	3230	3582508714	RETRACT ROD 			BEECH 	55 	95B55 	1152706	CE 										NLG	FAILED 	G				O				OTHER 				O			OTHER 			CL	CLIMB 	1			EA	21	700DM	9371 				TC967				DURING LANDING GEAR RETRACTION, A LOUD POP WAS HEARD. NO UNUSUAL INDICATIONS WERE OBSERVED. UPON GEAR EXTENSION, ALSO,	 NO UNUSUAL INDICATIONS OBSERVED. ALL GEAR INDICATED DOWN AND LOCKED, HOWEVER, THE NOSE GEAR COLLAPSED ON LANDING. INV	ESTIGATION DISCLOSED THE RETRACT ROD FAILED AT THE ATTACHMENT PLUNGER, PN 35-825094-4. THE PLUNGER SHOWED SIGNS OF A PR	EVIOUS FRACTURE. SUBMITTER RECOMENDS CLOSE INSPECTION AT EACH 100 HOURS OF OPERATION. THIS TYPE OF FAILURE DOES NOT GI	VE AN UNSAFE NOSE GEAR INDICATION ON THIS MODEL SERIES.		1	L	7	2 	3O				3A16 					 
1995092200185	19950922	00185	CE 	1995	9	22	95ZZZX5038 	1	19950830	G	7603	6325553	LEVER 			CESSNA	206 	U206 	2073306	CE 										THROTTLE	BROKE 	D	S			A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			WP	19	8467Q					U20603325				THROTTLE LEVER BROKE AT END OF LEVER WHERE THROTTLE ROD END ATTACHES ALLOWING THROTTLE TO DISCONNECT FROM ENGINE. AIRCR	AFT LANDED WITHOUT DAMAGE OR INJURY.					1	H	7	1 	3O				A4CE 					 
1995092200186	19950922	00186	SO 	1995	9	22	95ZZZX5039 	1	19950829	G	7810	40B21011	TAILPIPE 			PIPER 	PA46 	PA46350P 		SO 										EXHAUST	CRACKED 	B		A	LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9172V	1119 				4622038				DURING ANNUAL INSPECTION, FOUND LEFT EXHAUST TAILPIPE CRACKED AROUND THE ENTIRE CIRCUMFERENCE. THE ONLY THING SECURING 	TAILPIPE WAS THE LOWER WASTEGATE EXHAUST CLAMP. SUBMITTER STATED THIS APPEARS TO BE CAUSED BY PRELOAD ON THE EXHAUST SY	STEM.				1	L	7	1 	3O			RT	A25SO 					 
1995020300341	19950203	00341		1995	2	3	95ZZZX504 	1	19950101	G	2432	V012LKB	CELL 	MARATHON 	CA1542 															BATTERY	WRONG PART 	B			RD4D	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					7205159					INBOUND INSPECTION OF MARATHON BATTERY, PN 28659, TYPE CA-154-2, REVEALED 19 SAFT MANUFACTURED CELLS, PN V012CKB, INSTAL	LED IN CAN. MARATHON CELL PN 15M220 IS THE PROPER TYPE WHICH SHOULD BE USED FOR THIS BATTERY PART NUMBER APPLICATION. A	CCORDING TO THE 'INSTRUCTION MANUAL SINTERED-PLATE, NICKEL CADMIUM BATTERIES' BY MARATHON, PAGE 30, PARA 10.2, 'BATTERY 	REASSEMBLY', SECTION 1, 'IF A CELL MUST BE REPLACED, USE ONLY NEW OR REBUILT CELLS MANUFACTURED BY MARATHON BATTERY COMP	ANY'. BATTERY CONDEMNED AND RETURNED TO CUSTOMER. SOUTHERN AIR TRANSPORT.															 
1995092200187	19950922	00187	GL 	1995	9	22	95ZZZX5040 	1	19950828	G	2720		FAIRLEAD 			TCRAFT	BC 	BC12D 	8850316	GL 										RUD CABLE AFT	EXCESS WEAR 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	96539	1800 				8839				SLOT WORN IN BOTH LEFT AND RIGHT REAR CABLE GUIDES WITH SOME STRAND WEAR ON CABLES. RUDDER CABLES ARE BOTH ROUTED THROU	GH 3 FAIRLEADS IN AFT PORTION OF FUSELAGE WITH PROMINENT DEFLECTION AT AFT LEAD. TOTAL TIME, 1,800 HOURS. SUBMITTER SU	GGESTS CHECKING WEAR ON CABLE STRANDS AT AFT FAIRLEAD FOR EXCESS WEAR. REMOVE CLIP ON FAIRLEAD AND ROTATE 90 DEGREES TO	 180 DEGREES TO PROVIDE NEW WEAR SURFACE OR REPLACE FAIRLEAD. AIRCRAFT SUBJECTED TO YEARS OF GRASS FIELD OPERATIONS. C	OULD HAVE CONTRIBUTED ABRASIVE DIRT AND DUST TO OILS ON CABLE CAUSING ACCELERATED WEAR.		1	H	7	1 	3O				A696 					 
1995092200188	19950922	00188	SO 	1995	9	22	95ZZZX5041 	1	19950607	G	3222	MS20365524	NUT 	PARKERHANFIN	4477A 	GULSTM	AA5 	AA5A 	3960106	SO 										NLG AXLE	BACKED OFF 	D	S			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	99	9684U	2707 				AA5A0050				AXLE NUT 'LOCK TYPE', BACKED OFF DURING NORMAL USE. SUBMITTER SUGGESTS THERE SHOULD NOT BE A NUT ON BOTH SIDES OF THE A	XLE. ONE SIDE SHOULD HAVE A PERMANENT HEAD AND THE OTHER SHOULD HAVE A CASTELLATED NUT WITH A COTTER KEY.					1	L	7	1 	3O				A16EA 					 
1995092200189	19950922	00189	NM 	1995	9	22	95ZZZX5042 	1	19950808	G	5302	A02320	TAILBOOM 			ROBSIN	R22 	R22BETA 		NM 										1782 REV X	DENTED 	B			YT2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	980SM	2707 				1980				TAILBOOM HAS DENT IN FORWARD RIGHT SIDE DUE TO LANDING WITH SIDEWARD MOTION.						1	G	7	1 	3O				H10WE 					 
1995092200190	19950922	00190	EU 	1995	9	22	95ZZZX5043 	1	19950810	G	5530	350A1400200802	STABILIZER 			SNIAS 	350 	AS350B 	8680801	EU 										RT DOUBLER	CRACKED 	B	S		SZTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	911NW	3370 				1605				CRACK FOUND DURING T-INSPECTION, 500 HOUR, AND 2 T-INSPECTIONS. AD NOT APPLICABLE. PART MODIFIED IAW AM 507-2367. REP	LACED WITH FACTORY NEW ASSY.					1	G	7	1 	3U				H9EU 					 
1995092200191	19950922	00191	EU 	1995	9	22	95ZZZX5044 	1	19950814	G	6730		SERVO 			AGUSTA	A109 	A109A2 	0260120	EU 										RT AFT M/R	REQ ADJUSTMENT 	B			AOSR	A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			CL	CLIMB 	1			EA	11	500WK					7341				NOTED SEVERE VERTICAL VIBRATION SHORTLY AFTER TAKEOFF THAT INCREASED IN MAGNITUDE. RETURNED AND LANDED. RT AFT M/R SER	VO FRICTION FOUND LOW, ADJUSTED PER MM. RT FWD M/R SERVO CAP NUT FOUND SLIGHTLY LOOSE, SECURED. ADJUSTED CYCLIC MIN FR	ICTION PER MM.				1	G	7	2 	3U				H7EU 					 
1995092200192	19950922	00192	WP 	1995	9	22	95ZZZX5045 	1	19950811	G	7120	369A8204	MOUNT 			HUGHES	369 	369D 	4470706	WP 										ENG LOWER	LOOSE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V	4312 				4904870				LOWER ENGINE MOUNT FOUND LOOSE ON LEFT SIDE AND BOLT HOLE ELONGATED. PART REPLACED. MANUFACTURER'S TORQUE IS 40 INCH/P	OUNDS AT THIS POINT. THE BOLT IS STAINLESS CLOSE TOLERANCE. THE STRUCTURE IS STAINLESS AND THE MOUNT IS STEEL. THIS S	EEMS LIKE A LIGHT TORQUE.				1	G	7	1 	3U				H3WE 					 
1995092200193	19950922	00193	EU 	1995	9	22	95ZZZX5046 	1	19950812	G	5302		SKIN 			BOLKMS	117 	BK117B1 	5626012	EU 										TAILBOOM	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	13	193BK	1630 				7158				ON PRE-FLIGHT INSPECTION, MECHANIC FOUND A 2.5 INCH SKIN CRACK ON LEFT SIDE OF TAILBOOM BELOW INTERMEDIATE GEARBOX AT FS	 10,000 (MM). REPAIRED BY INSTALLING DOUBLER, PN 117-30106.15. ACFT TT 1,630.2 HOURS.					1	G	7	2 	3U				H13EU 					 
1995092200194	19950922	00194	WP 	1995	9	22	95ZZZX5047 	1	19950815	G	7910	369H8308	SEAL 			HUGHES	369 	369E 	4470707	WP 										OIL TANK	CRACKED 	H	S			K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	15	600TP		6800 			0128E				PILOT FLEW 2.2 HOURS ON DRUG SURVEILLANCE FLIGHT. UPON RETURN TO BASE, PILOT NOTED ON POST-FLIGHT, A LARGE PUDDLE OF OI	L FORMING ON RAMP UNDER FIREWALL AREA. SUBSEQUENT INVESTIGATION EXPOSED A CRACKED RUBBER 'SEAL' COUPLING BETWEEN OIL FI	LLER CAP AND OIL TANK. THIS IS HIGH TEMPERATURE/HIGH PRESSURE AREA. CRACK COULD HAVE RESULTED IN TOTAL LOSS OF ENGINE 	OIL. SUBMITTER STATED PART SHOULD BE TIME-CHANGE ITEM AT APPROXIMATELY 3,000 HOUR INTERVALS. PART CANNOT BE EXAMINED O	N PRE-FLIGHT, OR PROPERLY INSPECTED AT 100-HOUR INSPECTIONS.		1	G	7	1 	3U				H3WE 					 
1995092200434	19950922	00434		1995	9	22	95ZZZX5048 	4	19950727	G	3453	4530103	LORAN 		R21 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105MH				29481	S419				LORAN WILL NOT POWER UP AT INITIAL INSTALLATION.						1	G	7	2 	3U				H3EU 					 
1995092200435	19950922	00435	EU 	1995	9	22	95ZZZX5049 	1	19950703	G	6410	11731742	BLADE 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	ERODED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117M	241 			507	S7023				BLADE LEADING EDGE ERODED.						1	G	7	2 	3U				H13EU 					 
1995020300342	19950203	00342	SO 	1995	2	3	95ZZZX505 	2	19950101	G	8500		ENGINE 			PIPER 	J3 	J3C65 	7100510	SO 	CONT 	C90 	C9012F 	17009	SO 					FUEL SYSTEM	MALFUNCTIONED 	G				O				OTHER 				Y			ENGINE STOPPAGE 			TO	TAKEOFF 	1			EA	01	70548					17557	40059812			ENGINE POWER FAILURE DURING TAKEOFF. MAINTENANCE INVESTIGATION AND POST-ENGINE RUN WAS CONDUCTED. ENGINE RAN SATISFACT	ORY. MAINTENANCE ADVISED, SUSPECT FUEL STARVATION DUE TO FREEZING OF WATER CONTAMINATION IN LOW SECTION OF FUEL LINE.					1	H	7	1 	3O	3	O		A691 	E252				 
1995092200436	19950922	00436	EU 	1995	9	22	95ZZZX5050 	1	19950810	G	3340	MS2771927	SWITCH 			BOLKMS	117 	BK117A3 	5626015	EU 										SEARCH LIGHT	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117M	154 				S7023				SEARCH LIGHT SWITCH INOPERATIVE (IN THE EXTEND POSITION). REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995092200437	19950922	00437	EU 	1995	9	22	95ZZZX5051 	1	19950720	G	3340	A7151	HOUSING 			BOLKMS	117 	BK117B1 	5626012	EU 										LIGHT	BRACKET CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117VU	280 				7211				MOUNTING BRACKET CRACKED. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995092200440	19950922	00440		1995	9	22	95ZZZX5054 	4	19950708	G	2562	E0115	ANTENNA 			BOLKMS	105 	BO105S 	5626006	EU 										ELT	BROKEN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105NG	56 				S632				BROKEN FLIGHT ANTENNA. REMOVED AND REPLACED.						1	G	7	2 	3U				H3EU 					 
1995092200441	19950922	00441		1995	9	22	95ZZZX5055 	4	19950711	G	3416	5934P1	ALTIMETER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105NG	60 			9G004	S632				ALTIMETER KNOB PULLS OUT AND DISENGAGES FROM NEEDLE. OVERHAULED 6-1-96.						1	G	7	2 	3U				H3EU 					 
1995092200442	19950922	00442	EU 	1995	9	22	95ZZZX5056 	1	19950606	G	6410	365A12002000	BLADE 			AEROSP	SA365 	AS365N2 	8680815	EU 										T/R	COIL LOOSE 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	291LL	152 			20109	6402				COIL LOOSE IN T/R BLADE. REPLACED BLADE.						1	G	7	2 	3U			RT	H10EU 					 
1995092200443	19950922	00443	EU 	1995	9	22	95ZZZX5057 	1	19950606	G	6410	365A12002000	BLADE 			AEROSP	SA365 	AS365N2 	8680815	EU 										T/R	COIL LOOSE 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	291LL	878 			20102	6402				COIL LOOSE. REPLACED BLADE.						1	G	7	2 	3U			RT	H10EU 					 
1995092200444	19950922	00444	EU 	1995	9	22	95ZZZX5058 	1	19950606	G	6410	365A12002000	BLADE 			AEROSP	SA365 	AS365N2 	8680815	EU 										T/R	COIL LOOSE 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	291LL	523 			20845	6402				COIL LOOSE. REPLACED BLADE.						1	G	7	2 	3U			RT	H10EU 					 
1995092200445	19950922	00445	EU 	1995	9	22	95ZZZX5059 	1	19950801	G	6410	365A12002000	BLADE 			AEROSP	SA365 	AS365N2 	8680815	EU 										T/R	COIL LOOSE 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	291LL	878 			20103	6402				COIL LOOSE. REPLACED BLADE.						1	G	7	2 	3U			RT	H10EU 					 
1995092200446	19950922	00446	SW 	1995	9	22	95ZZZX5060 	1	19950722	G	3340	A7151	HOUSING 			BELL 	222 	222U 	1182140	SW 										LIGHT	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	219HM	63 				47573				CRACKED LIGHT HOUSING. REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995092200447	19950922	00447	SW 	1995	9	22	95ZZZX5061 	1	19950530	G	3340	A7151	LIGHT 			BELL 	222 	222U 	1182140	SW 										MOUNT	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	219HM					47573				LIGHT MOUNT CRACKED. REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995092200448	19950922	00448	EU 	1995	9	22	95ZZZX5062 	1	19950727	G	8000	SP461300	SWITCH 			BOLKMS	117 	BK117B1 	5626012	EU 										START SYS	INTERMITTENT 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	212AE					7222				SWITCH INTERMITTENT. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995092200449	19950922	00449		1995	9	22	95ZZZX5063 	4	19950624	G	3416	1042011968E	ENCODER 			BOLKMS	BK117 	BK117C1 	5626025	EU 										ALTIMETER	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	181 			149716	7505				'CODE OFF' FLAG WILL NOT PULL WHEN POWER IS APPLIED. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200450	19950922	00450	EU 	1995	9	22	95ZZZX5064 	1	19950630	G	7712	117902011	INDICATOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										TRIPLE TACH	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	13 			116	7505				NR 1 NEEDLE LAGS NR 2 NEEDLE AFTER 40 PERCENT RPM ATTAINED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200451	19950922	00451	EU 	1995	9	22	95ZZZX5065 	1	19950630	G	2150	11709511	EVAPORTATOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										FITTING	LEAKING 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	595 			106	7505				EVAPORATOR LEAKING AT FITTING. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200452	19950922	00452	EU 	1995	9	22	95ZZZX5066 	1	19950630	G	2150		EVAPORATOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										COILS	LEAKING 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	595 			107	7505				EVAPORATOR LEAKING AT COILS AND FITTINGS. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200453	19950922	00453	EU 	1995	9	22	95ZZZX5067 	1	19950706	G	6730		SERVO MONITOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										SERVO SYSTEM	ERROR CODES 	B			TI1R	K				NONE 				N			FALSE WARNING 			NR	NOT REPORTED 	1			SW	05	317MC	568 			90050146	7505				CONTINUAL ERROR CODES GENERATED IN-FLIGHT. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200454	19950922	00454		1995	9	22	95ZZZX5068 	4	19950624	G	3410	7002353913	SENSOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										AIR DATA	OUT OF TOLERANCE	B			TI1R	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	05	317MC	591 			93040894	7505				IAS HOLD MODE TEST STEP 8.7 OUT OF TOLERANCE (INDICATING 107 KNOTS - AIRSPEED INDICATOR 100 KNOTS).						1	G	7	2 	3U			NC	H13EU 					 
1995092200455	19950922	00455		1995	9	22	95ZZZX5069 	4	19950719	G	2216	7012409901	ACTUATOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										DUPLEX PITCH	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	646 			89070121	7505				ERROR CODES AND TROUBLESHOOTING FOUND ACTUATOR FAILURE INTERNALLY. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200456	19950922	00456		1995	9	22	95ZZZX5070 	4	19950722	G	2216	7012409901	ACTUATOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										DUPLEX PITCH	FAULTY 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	6 			90060144	7505				ACTUATOR ERROR CODES E47, E35, E27. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200457	19950922	00457		1995	9	22	95ZZZX5071 	4	19950708	G	2216	7012409901	ACTUATOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										PITCH TRIM	ERROR CODE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	60 			91050161	7505				ACTUATOR SOUNDS ROUGH, SHOWS ERROR CODES ON AUTOPILOT. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200458	19950922	00458	EU 	1995	9	22	95ZZZX5072 	1	19950719	G	6730	7012693901	SERVO MONITOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										SERVO SYSTEM	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	630 			95030183	7505				TROUBLESHOOTING AND FOUND SERVO MONITOR INOPERATIVE (R2-710 SHORTED AND SERVO MONITOR REC INOPERATIVE). TROUBLESHOT AND	 REPLACED.					1	G	7	2 	3U			NC	H13EU 					 
1995092200459	19950922	00459	EU 	1995	9	22	95ZZZX5073 	1	19950719	G	6730	7012693901	SERVO MONITOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										SERVO SYSTEM	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	630 			91010155	7505				TROUBLESHOOTING AND FOUND SERVO MONITOR INOPERATIVE (R2-710 SHORTED AND SERVO MONITOR REC INOPERATIVE). TROUBLESHOT AND	 REPLACED.					1	G	7	2 	3U			NC	H13EU 					 
1995092200460	19950922	00460	EU 	1995	9	22	95ZZZX5074 	1	19950703	G	3340	A7151	LIGHT 			BOLKMS	BK117 	BK117C1 	5626025	EU 										BRACKET	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	605 				7505				LIGHT BRACKET CRACKED. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200461	19950922	00461	EU 	1995	9	22	95ZZZX5075 	1	19950722	G	6730	7012693901	SERVO MONITOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										SERVO SYSTEM	ERROR CODES 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	6 			90050143	7505				ERROR CODES E47, E35, AND E27. (REMOVED WITH D. PITCH ACTUATOR). REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200462	19950922	00462	EU 	1995	9	22	95ZZZX5076 	1	19950803	G	2900	2811T10001	MIXING VALVE 			BOLKMS	BK117 	BK117C1 	5626025	EU 										HYD	LEAKING 	B			TI1R	K				NONE 				K	J		FLUID LOSS 	WARNING INDICATION 		NR	NOT REPORTED 	1			SW	05	317MC	258 			015	7505				VALVE LEAKING. TRIPS CAUTION LIGHT ON CAUTION PANEL. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200463	19950922	00463	EU 	1995	9	22	95ZZZX5077 	1	19950806	G	6710	10513142	ROD END 			BOLKMS	BK117 	BK117C1 	5626025	EU 										M/R	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	698 				7505				WORN ROD END ASSY, 4 EACH. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200464	19950922	00464	EU 	1995	9	22	95ZZZX5078 	1	19950806	G	6710	10513141	ROD END 			BOLKMS	BK117 	BK117C1 	5626025	EU 										M/R	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	698 				7505				WORN ROD END ASSY, 4 EACH. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200465	19950922	00465		1995	9	22	95ZZZX5079 	4	19950724	G	3421	O504007926	GYRO 			BOLKMS	BK117 	BK117C1 	5626025	EU 										COCKPIT ATTITUDE	LIGHT INOP 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	657 			5147	7505				GYRO LIGHTING INOPERATIVE. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200466	19950922	00466	EU 	1995	9	22	95ZZZX5080 	1	19950623	G	6220	1171120301	ROD ASSY 			BOLKMS	BK117 	BK117C1 	5626025	EU 										M/R	BEARING LOOSE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	591 			0390	7505				BEARING LOOSE AND RUSTED. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995092200467	19950922	00467		1995	9	22	95ZZZX5081 	4	19950802	G	3160	06604021111	SYMBOL GENERATOR			BOLKMS	BK117 	BK117C1 	5626025	EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	252 			2188	7505				SYMBOL GENERATOR WILL NOT HOLD DEAD ON COARSE IN NAV MODE.						1	G	7	2 	3U			NC	H13EU 					 
1995092200468	19950922	00468	EU 	1995	9	22	95ZZZX5082 	1	19950613	G	6210	1171310315	BUSHING 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	312LF	307 				7083				BUSHING DUE REPLATING - WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995092200469	19950922	00469	EU 	1995	9	22	95ZZZX5083 	1	19950722	G	6720	11731822	PITCH LINK 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	BEARING WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	313LF	351 			0037	7138				BEARING WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995092200470	19950922	00470	EU 	1995	9	22	95ZZZX5084 	1	19950722	G	6720	11731822	PITCH LINK 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	BEARING WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	313LF	351 			0082	7138				BEARING WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995092200471	19950922	00471	EU 	1995	9	22	95ZZZX5085 	1	19950610	G	2150	090161	RECEIVER DRIER 			AEROSP	SA365 	SA365N1 	8680668	EU 										AIR CONDITIONER	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	365SC	28 				6298				AIR CONDITIONER COMPRESSOR LOCKED UP POLLUTING SYSTEM WITH BURNED OIL. REMOVED AND REPLACED.						1	G	7	2 	3U				H10EU 					 
1995092200472	19950922	00472	GL 	1995	9	22	95ZZZX5086 	2	19950425	G	7320	222360703101	SOLENOID 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					ENGINE	DEFECTIVE 	B			SL3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	230TX	327 			651	23014				SOLENOID DEFECTIVE. NEW SOLENOID INSTALLED.						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995092200473	19950922	00473	GL 	1995	9	22	95ZZZX5087 	2	19950517	G	7320	222360703101	SOLENOID 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					ENGINE	DEFECTIVE 	B			SL3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	230TX	337 			653	23014				SOLENOID DOES NOT WORK CONSISTENTLY. IT SOMETIMES DOES NOT OPEN AND SOMETIMES DOES NOT CLOSE.						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995092200474	19950922	00474	SW 	1995	9	22	95ZZZX5088 	1	19950425	G	7931	222060096103	SWITCH 			BELL 	230 	230 	1182149	SW 										OIL PRESS	DEFECTIVE 	B			SL3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	230TX	327 			002A	23014				OIL PRESSURE LIGHT DOES NOT GO OUT WHEN PRESSURE APPLIED. NEW SWITCH INSTALLED.						1	G	7	2 	3U			NC	H9SW 					 
1995092200475	19950922	00475	SW 	1995	9	22	95ZZZX5089 	1	19950505	G	7931	222375019009	TRANSDUCER 			BELL 	230 	230 	1182149	SW 										OIL PRESS	DEFECTIVE 	B			SL3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	230TX	335 			4547233	23014				OIL PRESSURE INDICATION IN COCKPIT NOT READING. INSTALLED NEW TRANSMITTER.						1	G	7	2 	3U			NC	H9SW 					 
1995092200476	19950922	00476	SW 	1995	9	22	95ZZZX5090 	1	19950524	G	7931	222060096103	SWITCH 			BELL 	230 	230 	1182149	SW 										OIL PRESS	DEFECTIVE 	B			SL3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	230TX	345 			045A	23014				OIL PRESSURE LIGHT DID NOT GO OUT AFTER OIL PRESSURE APPLIED. NEW SWITCH INSTALLED.						1	G	7	2 	3U			NC	H9SW 					 
1995092200477	19950922	00477	SW 	1995	9	22	95ZZZX5091 	1	19950811	G	6210	MS150011	FITTING 			BELL 	206 	206L3 	1182108	SW 										BLADE GRIP	LEAKS 	B			TU3R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	07	112TV	6011 				51123				FITTING WAS INSTALLED ON NEW GRIP, PN 206-011-132-113A, SN A-5845. GRIP INSTALLED 8-2-95 AT 6008.2 HOURS ACFT TT. ON 8	-11-95, 6011.0 HOURS ACFT TT. THE GREASE FITTING HAD LEAKED A LARGE AMOUNT OF GREASE (30 PERCENT OF TOTAL AMOUNT ONTO H	UB). FITTING REPLACED, LEAK CHECKED AND FOUND OK.				1	G	7	1 	3U				H2SW 					 
1995092200478	19950922	00478	SW 	1995	9	22	95ZZZX5092 	1	19950719	G	7722	206375006101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	400SL	97 			165	45235				TOT INDICATOR FAILS TO INDICATE TEMPERATURE.						1	G	7	1 	3U				H2SW 					 
1995092200479	19950922	00479		1995	9	22	95ZZZX5093 	4	19950729	G	3421	5040017901	GYRO 			BELL 	206 	206L1 	1182107	SW 										COCKPIT ATTITUDE	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	400SL	1 			3572	45235				INSTRUMENT PUTS OUT ERRATIC PUFFING NOISES. FLAG NEVER RETRACTS. SUSPECT IMPROPER BENCH CHECK TECHNICALS.						1	G	7	1 	3U				H2SW 					 
1995092200480	19950922	00480	SW 	1995	9	22	95ZZZX5094 	1	19950712	G	3340	A469A	FLASH TUBE 			BELL 	206 	206L1 	1182107	SW 										STROBE LIGHT	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	400SL	3 				45235				INOPERATIVE FLASH TUBE. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995092200481	19950922	00481		1995	9	22	95ZZZX5095 	4	19950710	G	3421	4021541671	GYRO 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT HORIZ	PRECESSES 	B			TI3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	4493X				87061533	S7038				PRECESSES - WILL NOT HOLD ATTITUDE. OVERHAUL DONE ON 8-23-94, INV NR 62281 AND TESTED ON P/O 88573, ORDER NR 75988.						1	G	7	2 	3U				H13EU 					 
1995092200482	19950922	00482	EU 	1995	9	22	95ZZZX5096 	1	19950720	G	6220	904A33633156	BEARING 			AEROSP	AS355 	AS355F1 	8680810	EU 										SPHERICAL THRUST	WORN 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	5789X				O226	5100				SPHERICAL THRUST BEARINGS WORN BEYOND LIMITS. REPLACED THRUST BEARINGS.						1	G	7	2 	3U				H11EU 					 
1995092200483	19950922	00483	EU 	1995	9	22	95ZZZX5097 	1	19950720	G	6220	904A33633156	BEARING 			AEROSP	AS355 	AS355F1 	8680810	EU 										SPHERICAL THRUST	WORN 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	5789X				0209	5100				SPHERICAL THRUST BEARINGS WORN BEYOND LIMITS. REPLACED THRUST BEARINGS.						1	G	7	2 	3U				H11EU 					 
1995092200484	19950922	00484	EU 	1995	9	22	95ZZZX5098 	1	19950720	G	6220	904A33633156	BEARING 			AEROSP	AS355 	AS355F1 	8680810	EU 										SPHERICAL THRUST	WORN 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	5789X				0204	5100				SPHERICAL THRUST BEARINGS WORN BEYOND LIMITS. REPLACED THRUST BEARINGS.						1	G	7	2 	3U				H11EU 					 
1995092200485	19950922	00485	EU 	1995	9	22	95ZZZX5099 	1	19950720	G	6220	114986P	BEARING 			AEROSP	AS355 	AS355F1 	8680810	EU 										FREQ ADAPTER	WORN 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	5789X	176 				5100				BEARING WORN BEYOND LIMITS.						1	G	7	2 	3U				H11EU 					 
1995020300347	19950203	00347	CE 	1995	2	3	95ZZZX510 	1	19950109	G	2432		BATTERY 			LEAR 	23 	23LEAR 	5170102	CE 										DC SYSTEM	MALFUNCTION 	E				K				NONE 				J			WARNING INDICATION 			CR	CRUISE 	1			SO	04	13SN					23009				PILOT REPORTED A GRADUAL LOSS OF COMMUNICATION AND NAVIGATIONAL RADIOS. EN ROUTE, BACK TO MORRISTOWN AIRPORT, CREW REPO	RTED THEY WERE ABLE TO ACHIEVE FUNCTION OF ALL RADIOS. FUNCTIONAL TEST AND THOROUGH INSPECTION OF SWITCH PANEL, CIRCUIT	 BREAKER PANEL, RELAY PANEL, CURRENT LIMITERS, AND WIRING NORMAL. REPLACED BATTERIES. TEST FLIGHT OF AIRCRAFT NORMAL. 	 SUBSEQUENT TEST RUNS OF AIRCRAFT RESULTED IN REPLACEMENT OF LT GENERATOR AND RT VOLTAGE REGULATOR.			1	L	7	2 	4J				A5CE 					 
1995092200486	19950922	00486	SW 	1995	9	22	95ZZZX5100 	1	19950801	G	6330	222031605109	FLEXTURE 			BELL 	222 	222U 	1182140	SW 										M/R XMSN	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	6992	95 			LK0026	47521				FORWARD LOWER BUFFER PAD FELL OFF. REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995092200487	19950922	00487		1995	9	22	95ZZZX5101 	4	19950824	G	3421	206075607103	GYRO 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	721SP	209 			415	45486				INOPERATIVE ATTITDE GYRO.						1	G	7	1 	3U				H2SW 					 
1995092200554	19950922	00554	EU 	1995	9	22	95ZZZX5102 	1	19950811	G	2150	JBS30011	EVAPORATOR MOUNT			BOLKMS	BK117 	BK117C1 	5626025	EU 										AIR CONDITIONER	CRACKED 	B	L		BAQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	911TG	632 				7506				DURING ROUTINE BATTERY CHANGE, MECH NOTICED 3 OUT OF 4 MOUNTS ON A/C EVAPORATOR ASSY CRACKED. UNIT JUST INSPECTED 5 DAY	S PRIOR WITH NO DEFECTS. UNIT LOCATED BETWEEN ENG EXHAUST EJECTORS. THESE AFT COWLING ARE NOT NORMALLY REMOVED BETWEEN	 ENG CHANGES OR MAJOR INSPECTIONS WITH EXCEPTION OF 1 COWLING REMOVED TO SERVICE BATTERY. IT IS KNOWN BY MFG THIS PROBL	EM EXISTS. REF A.E.C. LETTER DATED MAY 2, 1995. AN INTERVAL TIME NEEDS TO BE ESTABLISHED SO UNIT CAN BE REPEATEDLY INS	PECTED, 25 FLIGHT HRS SEEMS ADEQUATE. SB OR TECH BULLETIN NEEDS TO BE ISSUED. UNIT SITS ABOVE T/R DRIVE SHAFT & REQUIR	ES A CERTIFIED TECH TO EVACUATE FREON SYS & SERVICE UNIT ACCORDING TO FED REGULATIONS, A SERVICE NOT READILY AVAILABLE.	1	G	7	2 	3U			NC	H13EU 					 
1995092200555	19950922	00555	SO 	1995	9	22	95ZZZX5103 	1	19950830	G	7160		VALVE 			GULSTM	AA1 	AA1C 	0631214	SO 										CARB AIR BOX	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	9560U	1600 				AA1C0057				CARBURETOR HEAT VALVE BROKEN AND PARTIALLY JAMMED. SHAFT ROTATING NORMALLY. NO HEAT GETTING TO CARBURETOR BRACKET. FI	LTER NOT REPLACED SINCE 1991, OVER 400 HOURS. SUBMITTER SUGGESTS NEOPRENE GASKET IS A POOR DESIGN FOR GRUMMAN AA-1C AIR	BOX, VERY LITTLE OF THE GASKET IS SANDWICHED AT THE LOWER LIP.				1	L	7	1 	3O				A11EA 					 
1995092200556	19950922	00556	SO 	1995	9	22	95ZZZX5104 	2	19950801	G	8530	SA629690	PISTON PIN 			PIPER 	PA28 	PA28R201T 	7102813	SO 	CONT 	O360 	TSIO360F 	17025	SO 					NR 2 CYLINDER	BROKEN 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	03	327LP	122 				28R7803275	281050R			NR 2 CYLINDER PISTON PIN FAILED AT MIDSECTION (BROKEN IN HALF). SUBSEQUENT FAILURE OF NR 2 PISTON AND METAL CONTAMINATE	D SUPERIOR AIR PARTS SUPPLIED PISTON PIN WITH A SHIP DATE OF 11-8-94. CAUSE UNKNOWN.					1	L	7	1 	3O	3	O		2A13 	E9CE				 
1995092200557	19950922	00557	CE 	1995	9	22	95ZZZX5105 	1	19950515	G	2720	03101965	SPRING 			CESSNA	172 	172N 	2072434	CE 										LT RUD RETURN	BROKEN 	D				K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			EA	17	6317F		4123 			17273189				PILOTS REPORTED AIRCRAFT REQUIRES FULL TRIM TO MAINTAIN A STRAIGHT COURSE IN CRUISE. FOUND SPRING BROKEN IN CONTROL BOX	 UNDER FLOOR TO LEFT RUDDER CABLE LINKAGE. REPLACED RUDDER RETURN SPRING. CONTROL THEN NORMAL.					1	H	7	1 	3O			NT	3A12 					 
1995092200558	19950922	00558		1995	9	22	95ZZZX5106 	1	19950817	G	7922	SL53E19600	VALVE 								LYC 	O360 	O360A4A 	41514	EA 					THERMO BYPASS	DEFECTIVE 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	99							L1256836A			TO COMPLY WITH SB 518C. A NEW THERMOSTATIC BYPASS VALVE WAS INSTALLED. DURING RUN-UP TEST, THE NEW VALVE FAILED TO CON	TROL OIL TEMPERATURE. THE VALVE WAS RETURNED TO VENDOR AND ANOTHER NEW ONE WAS INSTALLED AND FUNCTIONED SATISFACTORY.										3	O			E286				 
1995092200559	19950922	00559	SO 	1995	9	22	95ZZZX5107 	2	19950830	G	8530	21479	VALVE 			BBAVIA	7 	7AC 	2110102	SW 	CONT 	C85 	C8512 	17008	SO 					NR 3 CYL EXH	BROKEN 	G				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			SO	09	82560	2246 				7AC1197	23693612			EMERGENCY LANDING MADE AFTER EXHAUST VALVE HEAD SEPARATED. THIS ENGINE HAD 732 HRS SINCE 'TOP' OVERHAUL AND 2,246 HOURS	 SINCE NEW. THIS IS THE 446-HOUR PAST MANUFACTURER'S RECOMMENDED TIME.					1	H	7	1 	3O	3	O		A759 	E233				 
1995092200560	19950922	00560	CE 	1995	9	22	95ZZZX5108 	1	19950816	G	3213	12414231	SADDLE 			CESSNA	210 	210J 	2073439	CE 										LT MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	3387S	3192 				21059187				DURING ANNUAL INSPECTION AND C/W AD 76-14-07R2, FOUND LT MAIN LANDING GEAR SADDLE CRACKED IN RADIUS OF FORWARD END.						1	H	7	1 	3O				3A21 					 
1995092200561	19950922	00561	GL 	1995	9	22	95ZZZX5109 	3	19950831	G	6111	V84334	BLADE 			GULSTM	500 	500B 	0141106	SW 						HARTZL	HCA3V	HCA3VK2 	GL 	SHANK	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17					A93360			557		INSPECTION FOUND CRACKED BLADE SHANK.						1	H	7	2 	3O				6A1 		5	C	P6EA	 
1995020300348	19950203	00348	CE 	1995	2	3	95ZZZX511 	1	19950104	G	3230	12805042	UPLOCK VALVE 			CESSNA	210 	210K 	2073446	CE 										NLG	MISSING PART 	D				O				OTHER 				W			INADEQUATE Q C 			LD	LANDING 	1			SW	99	8223M					21059233				AIRCRAFT NOSE GEAR COLLAPSED AFTER A LANDING GROUND ROLL WITH MINOR DAMAGE TO AIRCAFT AND PROP BLADES. INSPECTION FOUND	 NOSE GEAR UPLOCK VALVE, THAT HAD BEEN REPLACED PRIOR TO FLIGHT WITH A USED UNIT, MISSING A SMALL CHECK BALL CAUSING A L	ARGER CHECK BALL TO WEDGE WITHIN ITS SEAT. AIRCRAFT ON JACKS PERFORMED AS REQUIRED AND LOCKED. IN-FLIGHT, THE DOWNLOCK	S WOULD NOT FULLY LOCK, ONLY PART WAY. USED UNITS SHOULD BE INSPECTED CLOSELY BEFORE INSTALLING IN AIRCRAFT.			1	H	7	1 	3O				3A21 					 
1995092200562	19950922	00562	EA 	1995	9	22	95ZZZX5110 	2	19950613	G	8530	LW14995	SPRING 			CESSNA	172 	172 	2072402	CE 	LYC 	O360 	O360A4M 	41514	EA 					SHROUD SPRING	BROKEN 	B			BJFR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	6338F	521 				17273195	L2944236A			ON 100-HOUR ENGINE INSPECTION, NR 1 CYLINDER WAS FOUND TO HAVE A LEAKING PUSHROD GASKET. UPON REMOVING ROCKER COVER TO 	REPLACE PUSHROD GASKET, THE SHROUD TUBE SPRING WAS FOUND BROKEN. UPON RESEARCH, FOUND THIS ENGINE WAS NOT EFFECTED BY L	YCOMING SB 519, DUE TO ENGINE OVERHAUL DATE.				1	H	7	1 	3O	3	O	NT	3A12 	E286				 
1995092200563	19950922	00563	EA 	1995	9	22	95ZZZX5111 	2	19950613	G	8530		GASKET 			CESSNA	172 	172 	2072402	CE 	LYC 	O360 	O360A4M 	41514	EA 					NR 1 PUSHROD	LEAKING 	B			BJFR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	23	6338F	521 				17273195	L2944236A			ON 100-HOUR ENGINE INSPECTION, NR 1 CYLINDER WAS FOUND TO HAVE A LEAKING PUSHROD GASKET. UPON REMOVING ROCKER COVER TO 	REPLACE PUSHROD GASKET, THE SHROUD TUBE SPRING WAS FOUND BROKEN. UPON RESEARCH, FOUND THIS ENGINE WAS NOT EFFECTED BY L	YCOMING SB 519, DUE TO ENGINE OVERHAUL DATE.				1	H	7	1 	3O	3	O	NT	3A12 	E286				 
1995092200564	19950922	00564	GL 	1995	9	22	95ZZZX5112 	3	19950831	G	6111	V84334	BLADE 			GULSTM	500 	500B 	0141106	SW 						HARTZL	HCA3V	HCA3VK2 	GL 	SHANK	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17					A93369			BJ545		INSPECTION FOUND CRACKED BLADE SHANK.						1	H	7	2 	3O				6A1 		5	C	P6EA	 
1995092200565	19950922	00565	GL 	1995	9	22	95ZZZX5113 	3	19950831	G	6111	V84334	BLADE 			GULSTM	500 	500B 	0141106	SW 						HARTZL	HCA3V	HCA3VK2 	GL 	SHANK	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17					A94412			BJ545		INSPECTION FOUND CRACKED BLADE SHANK.						1	H	7	2 	3O				6A1 		5	C	P6EA	 
1995092200567	19950922	00567	GL 	1995	9	22	95ZZZX5115 	3	19950829	G	6114		HUB 			CESSNA	402 	402C 	207590R	CE 						MCAULY	3AF32C	3AF32C93 	GL 	THREADS	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17		1891 						801989		INSPECTION FOUND CRACK IN THREADS OF HUB SOCKET.						1	L	7	2 	3O				A7CE 		5	C	P22EA	 
1995092200568	19950922	00568	EA 	1995	9	22	95ZZZX5116 	2	19950801	G	7414		BEARING 			PIPER 	PA25 	PA25235 	7102504	SO 	LYC 	O540 	O540G1A5 	41532	EA 					MAG DRIVE	FAILED 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			SW	13	8566L		520 			254990				MAG DROP 400 RPM, BUT SMOOTH. FOUND MAGNETO DRIVE BEARING FAILURE, RETARDING TIMING. BALLS OF BEARING COMING OUT OF BE	ARING CAGE AND EATING UP THE REAR OF CASE AND THEN AFTER MAKING SPACE AVAILABLE, FELL INTO THE ENGINE TIMING GEARS.					1	L	7	1 	3O	3	O		2A10 	E295				 
1995092200569	19950922	00569	EA 	1995	9	22	95ZZZX5117 	2	19950827	G	7414	1051676	CAPACITOR 			PIPER 	PA25 	PA25235 	7102504	SO 	LYC 	O540 	O540G1A5 	41532	EA 					MAGNETO	CORRODED 	H	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	13	8566L	550 				254990				MAG REMOVED FOR OVERHAUL AND PACKING OF BEARINGS BECAUSE OF TIME AND ROUGHNESS. CAPACITOR WAS FOUND TO BE LEAKING OR BU	ILDING CORROSION SIMILAR TO BATTERY CORROSION WHERE THE WIRE EXITS THE CAPACITOR HOUSING. CAPACITOR HAD NOT FAILED, BUT	 FAILURE WAS IMMINENT.				1	L	7	1 	3O	3	O		2A10 	E295				 
1995092200570	19950922	00570	CE 	1995	9	22	95ZZZX5118 	1	19950503	G	2730		BELLCRANK 			CESSNA	404 	404CESSNA 	2075901	CE 										FS 387.22	BROKEN LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	105AK	9037 				40400833				FOUND ON 100-HOUR INSPECTION, UPPER ATTACH POINT OF ELEVATOR BELLCRANK BROKEN LOOSE FROM BULKHEAD ASSY, STA 387.22. SUB	MITTER STATED ATTACH STRUCTURE BUILT TOO LIGHT FOR STRESSES OF ELEVATOR CABLE TENSION AND BELLCRANK STOP BLOCK. FABRICA	TED A BOX STRUCTURE OUT OF 4130, .040 INCH STEEL AND ATTACHED WITH NR 8 STRUCTURAL SCREWS.				1	L	7	2 	3O				A25CE 					 
1995092200571	19950922	00571	SO 	1995	9	22	95ZZZX5119 	1	19950809	G	2750	1642300	BELLCRANK 			PIPER 	PA23 	PA23250 	7102308	SO 										RT FLAP	BROKEN 	H		A		O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			GL	25	13981	3127 				274599				PILOT EXTENDED FLAPS AND ACFT BEGAN TO ROLL LEFT. FLAPS WERE RETRACTED IMMEDIATELY AND ACFT LANDED UNEVENTFULLY. INSPE	CTION FOUND RT FLAP BELLCRANK BROKEN AT CHANNEL WHERE ARM IS ATTACHED. LOG BOOKS INDICATE THIS PART WAS INSPECTED AND R	EWORKED PER SB 671 7/12/81 AND SUBSEQUENT VISUAL INSPECTIONS WERE ACCOMPLISHED AT INTERVALS REQUIRED BY AD 8104-05R1, PA	RA B(2). WALL THICKNESS WAS SEVERELY REDUCED BY CORROSION INSIDE CHANNEL, BUT NO OUTSIDE EVIDENCE OF CORROSION WAS VISI	BLE. SUBMITTER SUGGESTS, PARA B(2) OF AD SHOULD REQUIRE REPLACEMENT OF ALL OLD BELLCRANKS AND ESTABLISH A LIFE LIMIT ON	 ALL NEW BELLCRANKS (I.E: 10 YEARS).	1	L	7	2 	3O				1A10 					 
1995092200572	19950922	00572	SO 	1995	9	22	95ZZZX5120 	1	19950811	G	3230	4098600	BRACKET 			PIPER 	PA31 	PA31350 	7103110	SO 										NLG	BROKEN 	D		A		K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	01	601DA	8614 				318453002				NOSE GEAR ACTUATOR REINFORCEMENT BRACKET CRACKED AND FAILED. NOSE GEAR COULD NOT FULLY ACTUATE MICROSWITCH IN DOWN POSI	TION. RECOMMEND NEW REINFORCEMENT BRACKET BE ISSUED AS WAS DONE WITH TYPE AIRCRAFT MAIN GEAR REINFORCEMENT BRACKETS.					1	L	7	2 	3O				A20SO 					 
1995092200573	19950922	00573		1995	9	22	95ZZZX5121 	4	19950907	G	6113	D4812P	BULKHEAD 		84000800 	PIPER 	PA46 	PA46310P 	7104605	SO 										SPINNER	CRACKED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	91094					468608007				DURING INSPECTION, FOUND SPINNER CRACKED. REMOVED SPINNER AND INSPECTED SPINNER BULKHEAD. FOUND BULKHEAD CRACKED AT MO	UNTING HOLE AND SPINNER ATTACH HOLE. SUSPECT PROBLEM CAUSED BY SPINNER NOT BEING PROPERLY SHIMMED TO HUB. THIS ALLOWS 	SPINNER TO MOVE AND FLEX BULKHEAD. SUBMITTER STATED FAILURE TO CHECK SPINNER FIT COULD CAUSE FAILURE OF SPINNER WITH PO	SSIBLE CATASTROPHIC DAMAGE.			1	L	7	1 	3O				A25SO 					 
1995092200574	19950922	00574	CE 	1995	9	22	95ZZZX5122 	1	19950829	G	7160	04500704	HEAT FLAP 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					CARB AIR BOX	SEAL DETACHED 	D				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			SW	99	6561H					15284181	L1735415			AIRCRAFT LOST POWER DURING FLIGHT. PILOT MADE AN UNEVENTFUL EMERGENCY LANDING. UPON FURTHER INSPECTION, FOUND CARBURET	OR HEAT FLAPPER SEAL HAD BROKEN OFF AND A PIECE LODGED IN CARBURETOR VENTURI. UPON REMOVAL OF PIECE OF SEAL, AIRCRAFT D	EVELOPED FULL POWER. RECOMMEND CLOSER DETAILED INSPECTION OF THIS SEAL AT 100-HOUR AND ANNUAL INSPECTIONS.				1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995092200575	19950922	00575	SO 	1995	9	22	95ZZZX5123 	1	19950628	G	8120	07A19870	BRACKET 		46C19839 	PIPER 	PA46 	PA46350P 		SO 	LYC 	O540 	TIO540AE2A 	41532	EA 					LT TURBO	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	415JH	168 				4622007	CL955261A			DURING ROUTINE INSPECTION, LEFT TURBO ATTACH BRACKET FOUND CRACKED ALL THE WAY THROUGH AT TOP ATTACH POINT. ALSO, REMOV	ED BRACKET, PN 07F19872, FOR DYE PENETRANT INSPECTION DUE TO POSSIBLE EXCESS STRESS DUE TO MAIN BRACKET BROKEN. NO DISC	ONTINUITY FOUND. REINSTALLED STRUT BRACKET AND NEW FACTORY TURBO BRACKET. (ASSEMBLED ATTACH HARDWARE WITH LOCKTITE.)				1	L	7	1 	3O	3	O	RT	A25SO 	E14EA				 
1995092200576	19950922	00576	CE 	1995	9	22	95ZZZX5124 	1	19950613	G	2410	76906	BRACKET 			CESSNA	172 	172 	2072402	CE 										ALTERNATOR MOUNT	BROKEN 	B			BJFR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	6338F	820 				17273195				UPON REMOVING THE ALTERNATOR TO REPAIR A WIRE, THE ALTERNATOR BRACKET WAS FOUND BROKEN. THE BREAK ORIGINATED IN THE AFT	 BRACKET MOUNTING HOLE. ON FURTHER INSPECTION, A CRACK WAS ALSO FOUND IN ONE OF THE ALTERNATOR MOUNT BOLT HOLES.					1	H	7	1 	3O			NT	3A12 					 
1995092200577	19950922	00577	SO 	1995	9	22	95ZZZX5125 	1	19950705	G	8120	557584	COUPLING CLAMP 			PIPER 	PA31 	PA31325 	7103105	SO 	LYC 	O540 	TIO540F2BD 	41532	EA 					LT TURBO EXH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	117JP	826 	826 			317612086	L866561A			DURING 100-HOUR INSPECTION, FOUND LEFT ENGINE TURBO EXHAUST COUPLING CLAMP CRACKED IN V-BAND SEGMENT. THIS CLAMP IS THE	 NEW IMPROVED COUPLING CLAMP. REF PIPER SB644D.					1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995092200579	19950922	00579	EA 	1995	9	22	95ZZZX5127 	2	19950816	G	8530		PIPE 			GULSTM	AA1 	AA1A 	0630710	SO 	LYC 	O235 	O235L2C 	41505	EA 					NR 3 CYLINDER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	10FA					AA1A0337				DURING ANNUAL INSPECTION, FOUND FUEL STAINS AT NR 3 CYLINDER. REMOVED NR 3 CYLINDER INTAKE PIPE AND FOUND PIPE FLANGE C	RACKED ONE-THIRD AROUND TOP. THIS MAY BE CRACKED BY IMPROPER SEAT OR AGE. NEW PIPE INSTALLED THAT HAD A THICKER FLANGE	. TOTAL TIME, 1,806.6 HOURS.				1	L	7	1 	3O	3	O		A11EA 	E223				 
1995092200580	19950922	00580		1995	9	22	95ZZZX5128 	1	19950901	G	3340	A402AR	LENS 	WHELEN 	A407AR 															STROBE	BROKEN 	B			YV3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05		15 								SUBMITTER STATES ONE DESIGN OF THE STROBE LENS USES FOUR NARROW REFLECTOR RETAINERS WHICH ALLOW THE UPPER REFLECTOR TO F	ALL ONTO THE FLASH TUBE CAUSING BREAKAGE OF THE FLASH TUBE.																		 
1995092200581	19950922	00581	CE 	1995	9	22	95ZZZX5129 	1	19950831	G	3010	5100106371	LINE 			CESSNA	414 	414A 	2075907	CE 										WING DE-ICE	DETERIORATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	414ST	1600 				4140119				DE-ICE BOOTS ON WINGS INFLATE DURING FLIGHT. VACUUM SIDE DE-ICE LINE ON RIGHT SIDE BENEATH A DUCT APPARENTLY HAS MOISTU	RE IN IT. CENTER FLOOR FS 173 RT. THE MOISTURE AND LOCATION OF THIS LINE CAUSE CORROSION TO SET IN. EATS HOLES IN LIN	E. ABOUT SIZE OF NR 40 DRILL. HOLES ALLOW CABIN PRESSURIZATION AIR TO ENTER AND PRESSURIZE WING DE-ICE BOOTS.				1	L	7	2 	3O				A7CE 					 
1995020300350	19950203	00350	SO 	1995	2	3	95ZZZX513 	1	19950106	G	7500	12034290021	VENT TUBE 			EMB 	120 	EMB120RT 		SO 	PWA 	118 	PW118 		NE 					BLEED SYSTEM	CRACKED 	B			D2TR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25										THE WELDING PROCEDURE USED IN THE PREVIOUS REPAIR IS QUESTIONABLE, THE WELD IS CRACKING AROUND THE PERIMETER OF THE REPA	IR PATCH PLATE. THE WELDING WAS COMP. BY AN UNKNOWN REPAIR FACILITY. THE VENT TUBE IS PART OF THE ENGINE BLEED AIR SYS	TEM.				2	L	7	2 	4T	4	T	RT	A31SO 	E20NE				 
1995092200582	19950922	00582	NM 	1995	9	22	95ZZZX5130 	1	19950801	G	3222		BUSHING 			CHILD 	S1 	S1TPITTS 	0110303	NM 										TAIL WHEEL	EXCESS WEAR 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	7FD					1059				THE TAIL OF THE AIRPLANE STARTED TO 'WOBBLE' ON LANDING. EXAMINATION FOUND THE NUT ON THE AXLE HAD BEEN TURNED ONLY ENO	UGH TO INSERT THE COTTER KEY. CONSEQUENTLY, THE WHEEL BUSHING WAS COMPLETELY WORN OUT ON ONE SIDE.					1	Q	7	1 	3O				A8SO 					 
1995092200583	19950922	00583	NM 	1995	9	22	95ZZZX5131 	1	19950801	G	2820		FITTING 			CHILD 	S1 	S1TPITTS 	0110303	NM 										MAIN TANK	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	15	7FD					1059				THE FUEL OUTLET AT THE REAR BOTTOM OF THE MAIN TANK WAS LEAKING SIGNIFICANTLY. IMPOSSIBLE TO TELL IF PIPE LUBRICATION W	AS USED, BUT NO PIPE TAPE WAS NOTED. FITTINGS TIGHTENED THREE-QUARTER TURN.					1	Q	7	1 	3O				A8SO 					 
1995092200584	19950922	00584	NM 	1995	9	22	95ZZZX5132 	1	19950801	G	2720		CONTROL CABLE 			CHILD 	S1 	S1TPITTS 	0110303	NM 										RUDDER	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	7FD					1059				THE HOLES IN THE REAR FUSELAGE FOR EXIT OF THE RUDDER CABLES DOES NOT ALIGN WITH THE CABLES. CONSEQUENTLY, THE CABLES A	RE RUBBING ON THE FABRIC AND THE CABLES ARE STARTING TO WEAR. THIS MIS-ALIGNMENT IS VERY OBVIOUS AND HAS BEEN NOTED ON 	SEVERAL TECHNICAL INSPECTIONS REQUIRED FOR COMPETITION AEROBATICS.				1	Q	7	1 	3O			 	A8SO 					 
1995092200585	19950922	00585	NM 	1995	9	22	95ZZZX5133 	1	19950801	G	2822		FITTING 			CHILD 	S1 	S1TPITTS 	0110303	NM 										WOBBLE PUMP	LEAKING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	7FD					1059				FUEL STARTED SEEPING AROUND FITTING. ALUMINUM FITTINGS WERE USED IN ALUMINUM HOUSING. NO PIPE TAPE USED AND MINIMUM PI	PE LUBRICATION. ON REMOVAL, IT WAS DIFFICULT TO TELL IF FITTING WAS STRIPPED ON INSTALLATION OR REMOVAL. HOWEVER, THER	E WERE NO SAFETY WIRES USED ON FITTING OR PLUG.				1	Q	7	1 	3O				A8SO 					 
1995092200586	19950922	00586		1995	9	22	95ZZZX5134 	4	19950801	G	6122		GOVERNOR 			CHILD 	S1 	S1TPITTS 	0110303	NM 										PROPELLER	MISADJUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	7FD					1059				DUE TO VARIATION IN RPM, THE PROP, GOVERNOR, AND ENGINE OIL PRESSURE WERE INVESTIGATED. THE PROP WAS RETURNED TO HARTZE	LL AND NO PROBLEM FOUND. LYCOMING SENT A REP TO CHECK OIL PRESSURES AND FOUND GOOD PRESSURES. THE ORIGINAL GOVERNOR AN	D TWO OTHERS WERE TESTED. IT WAS NEVER CLEAR IF THE FACTORY ORIGINAL GOVERNOR WAS SET CORRECTLY. IT SEEMS THE ORIGINAL	 GOVERNOR WAS SET TOO HIGH. CONSEQUENTLY, THERE MAY HAVE BEEN CONSIDERABLE OVERSPEEDING OF THE PROP. THE METER USED BY	 THE FACTORY TO CHECK RPM IN-FLIGHT IS NOT ADEQUATE DURING AEROBATICS.		1	Q	7	1 	3O				A8SO 					 
1995092200587	19950922	00587	NM 	1995	9	22	95ZZZX5135 	1	19950801	G	7810		CLAMP 			CHILD 	S1 	S1TPITTS 	0110303	NM 										EXHAUST	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	7FD					1059				THE PAIR OF EXHAUST CLAMPS USED TO SECURE THE CROSS-OVER EXHAUST HAVE BROKEN EITHER ONE OR BOTH EVERY 30-40 HOURS. WHEN	 ENOUGH PIECES REMAINED, THEY WERE SENT TO THE AVIAT. A TOTAL OF SEVEN CLAMPS HAVE BROKEN, EVERY CRACK IS THE SAME PLAC	E.				1	Q	7	1 	3O				A8SO 					 
1995092200588	19950922	00588	NM 	1995	9	22	95ZZZX5136 	1	19950801	G	7714		TACHOMETER 			CHILD 	S1 	S1TPITTS 	0110303	NM 										ENG RPM	ERRATIC 	D				K				NONE 				O			OTHER 			TO	TAKEOFF 	1			SW	15	7FD					1059				THE TACHOMETER WOULD NOT INDICATE A CONSTANT RPM SETTING ON TAKEOFF OR DURING AEROBATIC MANEUVERS. THERE WAS A 100-150 	RPM LAG. IT WAS IMPOSSIBLE TO DETERMINE IF THE RPM WAS SET CORRECTLY, AN IMPORTANT FACTOR CONSIDERING THE LARGE RESONAN	CE LIMITATIONS FOR AEROBATICS. THE TACHOMETER WAS CHECKED BY MITCHELL AND FOUND TO HAVE NO PROBLEMS. A SECOND TACH (NO	W ON AIRPLANE) HAS A GREATER LAG THAN THE FIRST. AVIAT WILL NOT RESPOND TO PROBLEM. IT SHOULD BE NOTED THAT AVIAT MAKE	S THE TACH DRIVE ASSEMBLY WHICH HAS NEVER BEEN TESTED.		1	Q	7	1 	3O				A8SO 					 
1995092200589	19950922	00589	SO 	1995	9	22	95ZZZX5137 	2	19950831	G	8530	6291171	ROTOR 								CONT 	O520 	IO520* 	17032	SO 					EXHAUST VALVE	DEFECTIVE 	B			YCTR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11										EXHAUST VALVE ROTOR CAP WILL NOT ROTATE. THIS VALVE ROTOR WAS OUT OF A CYLINDER VALVE ASSEMBLY.											3	O			E5CE				 
1995092200590	19950922	00590	SO 	1995	9	22	95ZZZX5138 	2	19950820	G	7414	6220	MAGNETO 	SLICK 		CESSNA	210 	T210N 	2073456	CE 	CONT 	O520 	TSIO520R 	17040	SO 					ENGINE	BURNED 	D				K				NONE 				M			OVER TEMP 			NR	NOT REPORTED 	1			SW	15	37AA	348 			91030039	21062989	269610R			MAGNETO LOOKED LIKE NEW FROM OUTSIDE. WHEN REMOVED ALL COMPONENTS INSIDE WERE BURNED UP. NO ROTOR AND ONLY 3 TOWERS OF	 DISTRIBUTOR WERE LEFT. MAGNETO WAS BURNED UP VERY FAST AND VERY HOT. DESTROYED HALF OF THE HARNESS CONNECTION (PLATE)	.				1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995092900070	19950929	00070		1995	9	29	95ZZZX5139 	4	19950619	G	2210	HDSTD9860001	ACTUATOR 			BELL 	222 	222 	1182122	SW 										TRIM	CLUTCH SLIPS 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	100 			210	47520				TRIM ACTUATOR CLUTCH SLIDE WILL NOT HOLD. REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995092900071	19950929	00071	SW 	1995	9	29	95ZZZX5140 	1	19950615	G	7170	70031E072135	HOSE 			BELL 	222 	222 	1182122	SW 										EXHAUST DRAIN	SEPARATION 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	160 				47520				FITTING SEPARATION. NR 2 ENGINE EXHAUST DRAIN HOSE WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995092900072	19950929	00072	SW 	1995	9	29	95ZZZX5141 	1	19950724	G	3340	4501283	LIGHT 			BELL 	222 	222 	1182122	SW 										SEARCH	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	307 			68071	47520				LIGHT WOULD NOT EXTEND.						1	G	7	2 	3U				H9SW 					 
1995020300352	19950203	00352	CE 	1995	2	3	95ZZZX515 	1	19950112	G	3020	50389028	BOOT 			BEECH 	90 	E90 	1152914	CE 										LT ENG INLET	SHORTED 	D				A				UNSCHED LANDING 				M			OVER TEMP 			CR	CRUISE 	1			EA	03	232CL					LW232				ON DEPARTURE FROM AIRPORT, LEFT INLET BOOT (ELECTRIC) SHORTED AND BURNED, CIRCUIT BREAKER DID NOT TRIP. BOOT WAS TURNED	 OFF, LEFT ENGINE SHUT DOWN AND RETURNED TO AIRPORT.					1	L	7	2 	3T				3A20 					 
1995092900094	19950929	00094	EU 	1995	9	29	95ZZZX5163 	1	19950517	G	7931	6607A2114	SWITCH 			BOLKMS	105 	BO105LSA3 	5626020	EU 										OIL PRESS	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911SV				546319	2033				SWITCH UNRELIABLE, INOPERATIVE. REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU 					 
1995020300357	19950203	00357	EU 	1995	2	3	95ZZZX520 	1	19950112	G	3242	5000208	DISK 		9550504 	AMD 	FALC20	FALCON20C5 	2730107	EU 										BRAKE	FAILED 	B		A	ST1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19										OUT OF FOUR BRAKE ASSEMBLIES, THREE EACH STATIONARY DISKS WERE CRACKED. ONE EACH HAD BROKEN IN TWO AND HAD FALLEN OUT O	F BRAKE ASSEMBLY.					2	L	7	2 	4F			RT	A7EU 					 
1995092900344	19950929	00344		1995	9	29	95ZZZX5204 	4	19950810	G	3421	1113034	GYRO 			BELL 	212 	212 	1181420	SW 										COCKPIT ADI	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2FOR	54 			24445	31151				GYRO TUMBLES FOR 30-40 MINUTES.						1	G	7	1 	4U				H4SW 					 
1995092900345	19950929	00345		1995	9	29	95ZZZX5205 	4	19950806	G	2200	4020936903	GYRO 			BELL 	412 	412 	1182202	SW 										COCKPIT TARSYN	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2FOR	586 			94021247	36013				INOPERATIVE TARSYN GYRO. REMOVED AND REPLACED.						1	G	7	2 	4U				H4SW 					 
1995092900346	19950929	00346		1995	9	29	95ZZZX5206 	4	19950817	G	2312	4000103000	RECEIVER 		RT450 															VHF	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05					260					TRANSMIT RELAY STICKS. UNIT STILL INOPERATIVE. ZERO HOURS SINCE BENCH CHECK.																			 
1995092900348	19950929	00348	CE 	1995	9	29	95ZZZX5208 	1	19950901	G	3213	NAS50200	SNAP RING 			BEECH 	35 	J35 	1151522	CE 										RT MLG	FAILED 	D				D				RETURN TO BLOCK 				O			OTHER 			TX	TAXI/GRND HDL 	1			SO	03	3033C	3856 				D5688				DURING TAXI AFTER REFUELING, OPERATOR HEARD LOUD BANG & TAXIED TO HANGAR. MX FND HOLE IN TOP OF RT WING (APPROX 2 INCHE	S IN DIA), DIRECTLY ABOVE TOP OF RT MLG. FURTHER INVEST REVEALED RT MLG BARREL END PLUG HAD LEFT STRUT DUE TO FAILURE O	F RETAINING RING. UNABLE TO LOCATE FAILED RING. LOG RESEARCH REVEALED RT STRUT RESEALED APPROX 300 HRS PREV. FURTHER 	LOG RSRCH REVEALED NO DOCUMENTED LANDING GEAR DISASSY/INSP PER MFG 2,000 HR REQUIREMENT SINCE PLANE MFG IN 9/58. WITH T	HESE FACTS, LOGICAL SURMISE WOULD BE RETAINING RING FAILED DUE TO CORROSION & FATIGUE HAVING BEEN IN SERVICE SINCE 1958.	 IF JUST 1 OF MANY OPERATORS IN LAST 37 YRS HAD COMPLIED WITH MX REQUIREMENT, DAMAGE COULD HAVE BEEN AVOIDED.	1	L	7	1 	3O				3A15 					 
1995092900350	19950929	00350	SO 	1995	9	29	95ZZZX5210 	2	19950830	G	8530	63966011	INTAKE HOSE 			CESSNA	320 	320B 	2074508	CE 	CONT 	O470 	TSIO470C 	17026	SO 					LT ENGINE	LEAKING 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			SW	15	986J					320B0020	1080393C			LEFT ENGINE SPUTTERED AND BEGAN RUNNING ROUGH. MANIFOLD PRESSURE TRIED TO CLIMB TO AMBIENT PRESSURE AT IDLE. RIGHT FOR	WARD INTAKE HOSE WAS LEAKING DUE TO CLAMPS (PN 539487) BEING LOOSE WHERE BALANCE TUBE (PN 629937) ATTACHES. REPOSITIONE	D HOSE AND CLAMPS AND SECURED BY TIGHTENING CLAMPS.				1	L	7	2 	3O	3	O		3A25 	3E3				 
1995092900351	19950929	00351	CE 	1995	9	29	95ZZZX5211 	1	19950908	G	5220		WINDOW 			BEECH 	35 	S35 	1151532	CE 										EMERG ESCAPE	SEALED SHUT 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25		5039 								ANNUAL INSPECTION FOUND BOTH LT AND RT EMERGENCY ESCAPE WINDOWS HAD BEEN SILICONED SHUT BY PERSONS UNKNOWN, APPARENTLY I	N AN ATTEMPT TO SEAL THE WINDOW AGAINST THE WEATHER. THE SILICONE WAS SO HEAVILY APPLIED THAT ONLY BY PRYING FROM THE O	UTSIDE WITH A GASKET SCRAPER WAS EITHER WINDOW FINALLY OPENED. WHAT WAS MORE AMAZING WAS THAT DUE TO THE APPARENT AGE O	F THE SILICONE, THIS AIRCRAFT HAD UNDERGONE AT LEAST TWO ANNUAL INSPECTIONS PRIOR TO THIS WITHOUT THIS CONDITION BEING D	ISCOVERED. OBVIOUSLY, THE CONSEQUENCES IN AN ACCIDENT COULD BE DISASTEROUS.		1	L	7	1 	3O				3A15 					 
1995092900352	19950929	00352	SO 	1995	9	29	95ZZZX5212 	1	19950801	G	5711		SPAR CAP 			PIPER 	PA28 	PA28180 	7102808	SO 										LT WING	CORRODED 	H	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	5235L					284529				MINOR CORROSION FOUND ON CENTER SECTION OF THE FORWARD FLANGE OF THE UPPER SPAR CAP ON THE LT WING. A FUEL TANK MOUNTS 	FORWARD OF THE SPAR WHERE THE CORROSION WAS FOUND. THE CORROSION IS VERY MINOR. THE CORROSION HAS BEEN COMPLETELY REMO	VED AND IT IS BELIEVED THAT NO STRUCTURAL REPAIR OF THE AREA IS NECESSARY.				1	L	7	1 	3O				2A13 					 
1995092900353	19950929	00353	GL 	1995	9	29	95ZZZX5213 	2	19950808	G	7250	A6871505	BEARING 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					TURB NR 5	MAKING METAL 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	105NC	95 				790				BEARING WAS PURCHASED AS PMA PART FROM SUPERIOR TURBINE. AN INFORMATION LETTER FROM SUPERIOR DATED MAY 1, 1995, RECOMME	NDED INSPECTION OF BEARING AND FILTER FOR METAL FLAKES. THIRTEEN PIECES FOUND IN FILTER, ONE WAS 'TRIANGULAR 2 X 4MM', 	SINCE TWO SB HAVE BEEN ISSUED FROM SUPERIOR, ONE FOR NR 5 AND ONE FOR NR 8 BEARINGS.				1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995092900354	19950929	00354	CE 	1995	9	29	95ZZZX5214 	1	19950614	G	7603	5038901229	THROTTLE CABLE 			BEECH 	58 	58 	1152740	CE 										RT THROTTLE	LOOSE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	17915					TH78				RIGHT THROTTLE CABLE SLEEVE AT ENGINE END OF CONTROL WAS FOUND LOOSE, SWAGED PORTION BROKEN WHERE IT ATTACHES AT THE THR	EADED END OF CABLE. THIS WAS FOUND AT 100-HOUR INSPECTION WHEN COMPLYING WITH TCM SB 95-2.					1	L	7	2 	3O			 	3A16 					 
1995092900355	19950929	00355	CE 	1995	9	29	95ZZZX5215 	1	19950227	G	3246		RETAIN ARM 			CESSNA	185 	185 	2072802	CE 										LT SKI	FAILED 	H				O				OTHER 				O			OTHER 			LD	LANDING 	1			GL	15		400 								LEFT SKI RETAINING ARM BROKE DURING LANDINGS ALLOWING SKI TO ROTATE AND DIG INTO SNOW. AIRCRAFT SWERVED LEFT COMING TO 	REST ON NOSE CAUSING DAMAGE TO RIGHT WING AND PROPELLER.					1	H	7	1 	3O			NC	3A24 					 
1995092900356	19950929	00356	CE 	1995	9	29	95ZZZX5216 	1	19950511	G	2434	DOFF10300B	ALTERNATOR 	FORD 		CESSNA	150 	152 	2071835	CE 										DC SYSTEM	FAILED 	D				A				UNSCHED LANDING 				H			ELECT. POWER LOSS-50 PC 			CR	CRUISE 	1			GL	17	6598B				2574	15283957				ALTERNATOR FAILED IN-FLIGHT. ACFT LANDED AND REPLACED THE ALTERNATOR. NO OBVIOUS DAMAGE.						1	H	7	1 	3O			NT	3A19 					 
1995092900357	19950929	00357	CE 	1995	9	29	95ZZZX5217 	1	19950607	G	7602	5038901223	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										RT MIXTURE	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	17915					TH78				RIGHT MIXTURE CONTROL CABLE THREADED SWAGED END BROKE OFF AT ENGINE SHUT-DOWN. NEW CABLE WAS INSTALLED 5-15-95. AIRCRA	FT HAS ONLY FLOWN 63.1 HOURS SINCE CABLE WAS REPLACED.					1	L	7	2 	3O			 	3A16 					 
1995092900358	19950929	00358	CE 	1995	9	29	95ZZZX5218 	1	19950531	G	7603	5038901215	CONTROL CABLE 			BEECH 	95 	95B55 	1152729	CE 										LT THROTTLE	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	96NL					TC721				LEFT THROTTLE CABLE SLEEVE ON ENGINE END WAS FOUND LOOSE AND SLIDING FREELY. SWAGED PORTION WAS NOT ATTACHED TO THREADE	D END OF CABLE. SUBMITTER STATED NUMEROUS CABLES HAVE BEEN FOUND WITH THIS PROBLEM. CAN CAUSE CABLE TO JAM AND HAVE LO	SS OF CONTROL MOVEMENT. FOUND DURING 100-HOUR INSPECTION.				1	L	7	2 	3O			RT	3A16 					 
1995020300359	19950203	00359	SO 	1995	2	3	95ZZZX522 	1	19950113	G	2435	12041720001	DUCT 			EMB 	120 	EMB120RT 		SO 										START/GEN FLANGE	CRACKED 	B			D2TR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25										THE STARTER/GENERATOR DUCT CRACKS ON THE SIDES BY THE FLANGE, AND ON THE FLANGE. THERE IS A LARGE AMOUNT OF VIBRATION, 	AND THE DUCT IS CONNECTED TO A RUBBER HOSE THAT VIBRATES, A RIGID CONNECTION TO THE STARTER/GENERATOR. SUBMITTER STATED	 THIS IS A REPEATED REPAIR. A FLEXIBLE GASKET MAY HELP.				2	L	7	2 	4T			RT	A31SO 					 
1995092900360	19950929	00360	CE 	1995	9	29	95ZZZX5220 	1	19950523	G	7603	5038901215	CONTROL CABLE 			BEECH 	95 	95B55 	1152729	CE 										LT THROTTLE	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	246L					TC502				THE THROTTLE CABLE SLEEVE, SWAGED AT THE THREADED END AT ENGINE ATTACH POINT, SEPARATED AND CAUSED PARTIAL BINDING DURIN	G 100-HOUR INSPECTION AND GROUND RUN. FOUND DURING COMPLIANCE WITH TCM SB 95-2.					1	L	7	2 	3O			RT	3A16 					 
1995092900361	19950929	00361	SO 	1995	9	29	95ZZZX5221 	2	19950905	G	8530	653426A4	CYLINDER 			CESSNA	175 	175A 	2072504	CE 	CONT 	O300 	GO300C 	17022	SO 					NR 4	GUIDE WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	6821E	84 				56321	14017			VALVE GUIDE WORN EXCESSIVELY. WOULD NOT PASS COMPRESSION CHECK. OWNER STATED HE WAS NOT USING AUTO FUEL. VALVE GUIDE 	WAS REPLACED.					1	H	7	1 	3O	3	O		3A17 	E298				 
1995092900362	19950929	00362	SO 	1995	9	29	95ZZZX5222 	1	19950527	G	3230	6390170	HOSE ASSY 		9686000 	PIPER 	PA34 	PA34200T 	7103406	SO 										NLG DRAG LINK	INTERFERES 	G		A		O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			NM	05	41941	442 				347570176				THE PILOT NOTIFED DURING A LANDING SEQUENCE WHEN THE GEAR LEVER WAS SELECTED DOWN, THERE WAS AN INDICATION OF AN UNSAFE 	NOSE GEAR. THE NOSE GEAR COLLAPSED UPON LANDING. INVESTIGATION OF THE INCIDENT REVEALED THE NOSE GEAR ACTUATOR RETRACT	ION PORT HOSE ASSY INTERFERRED WITH THE NOSE GEAR EXTENSION AND PREVENTED THE GEAR FROM FULLY EXTENDING TO THE DOWN AND 	LOCKED POSITION. THE HOSE ENGAGED THE UPPER DRAG LINK TRUNNION BOLT. SUBMITTER SUGGESTS CHANGING THE ACTUATOR FITTINGS	 TO RE-DIRECT THE HOSES AWAY FROM THE DRAG LINK ASSY AS DONE ON LATER MODELS OF THIS AIRCRAFT.		1	L	7	2 	3O				A7SO 					 
1995092900363	19950929	00363	CE 	1995	9	29	95ZZZX5223 	1	19950906	G	2810	082340064	BULKHEAD 			CESSNA	402 	402B 	207590P	CE 										RT TIP TANK	CRACKED 	D		A		K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	07	3131K	6450 				402B0248				DURING A ROUTINE INSPECTION, NOTICED THE RIGHT MAIN WING TIP FUEL TANK WAS LEAKING. FURTHER INVESTIGATION REVEALED THE 	AFT BULKHEAD AND AFT WING ATTACH BULKHEAD WERE CRACKED. SUBMITTER STATED IF CONDITION WOULD HAVE GONE UNNOTICED, IT WOU	LD POSSIBLY RESULT IN WING TIP FUEL TANK DEPARTING THE AIRCRAFT. SUBMITTER SUSPECTS CAUSE AS FATIGUE, VIBRATION. SUBMI	TTER SUGGESTS PREVENTION - INSPECT AREA CLOSE DURING INSPECTION INTERVALS AND IMMEDIATELY IF FUEL STAINS NOTICED.			1	L	7	2 	3O				A7CE 					 
1995092900364	19950929	00364	CE 	1995	9	29	95ZZZX5224 	1	19950912	G	2810	082340063	BULKHEAD 			CESSNA	310 	310R 	2074245	CE 										LT TIP TANK	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	310MB	6500 				310R0943				INSPECTED LEFT TIP TANK BULKHEAD (REAR) AND FOUND BULKHEAD BROKEN HALF WAY ACROSS. PREVIOUS SHOP INSPECTOR STATED THEY 	DID NOT REMOVE THE TIP FAIRING UNLESS FUEL LEAKS WERE EVIDENT. REPAIRED WITH LIKE THICKNESS DOUBLER.					1	L	7	2 	3O				3A10 					 
1995092900365	19950929	00365	EA 	1995	9	29	95ZZZX5225 	2	19950801	G	8540		BOLT 								LYC 	O540 	IO540K1G5 	41532	EA 					CRANK GEAR	NOT MARKED 	B			H5LR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	05							L1640348P			ORDER NEW CRANKSHAFT AND GEAR/CAMSHAFT ATTACHING BOLT. BOLT INSPECTED AND NO HEAD ID MARKINGS IAW AD 91-14-22 TITLED TO	 PREVENT LOOSENING OR FAILURE AT CRANKSHAFT GEAR RETAINING BOLT.										3	O			1E4				 
1995092900366	19950929	00366	CE 	1995	9	29	95ZZZX5226 	1	19950809	G	3260	1CH16	SWITCH 			CESSNA	404 	404CESSNA 	2075901	CE 										LT MLG	FAILED 	B			BWRR	O				OTHER 				N			FALSE WARNING 			AP	APPROACH 	1			CE	07	27SA					4040038				AIRCRAFT CAME IN WITH NO GEAR DOWN INDICATION ON THE LEFT SIDE. AIRCRAFT LANDED WITHOUT INCIDENT. FOUND LEFT GEAR DOWN	 SWITCHES HAD FAILED. INSTALLED NEW SWITCH.					1	L	7	2 	3O				A25CE 					 
1995092900367	19950929	00367	SO 	1995	9	29	95ZZZX5227 	2	19950824	G	8520		CRANKCASE 			CESSNA	340 	340A 	2076405	CE 	CONT 	O520 	TSIO520NB 	17040	SO 					NR 4 CYL PAD	CRACKED 	B			NT2R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CE	07	340P	803 				340A0507	276960R			FOUND CRANKCASE CRACKED AT NR 4 CYLINDER PAD. CRACK IS CLEAR THROUGH CYLINDER PAD BOSS AND PROTRUDES DOWNWARDS ABOUT 5 	INCHES TOWARD THE OIL FILLER MOUNTING HOLE. LEAKS OIL. ENGINE REPLACED.					1	L	7	2 	3O	3	O		3A25 	E8CE				 
1995092900368	19950929	00368	GL 	1995	9	29	95ZZZX5228 	3	19950831	G	6114		HUB 			PIPER 	PA28 	PA28181 	7102807	SO 						MCAULY	1A170	1A170* 	GL 	BOLT HOLE	CRACKED 	B			FQ6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09										PROPELLER TOTAL TIME IN SERVICE, 2,000.3 HOURS SINCE NEW, MAY OF 1991. HUB CRACKED STRAIGHT ACROSS AND THROUGH ONE BOLT	 HOLE. ZYGLO AND EDDY CURRENT CRACK SHOWS UP. REJECTED AND NOTIFIED FAA ABOUT FINDINGS.					1	L	7	1 	3O				2A13 		5	N	P857	 
1995092900369	19950929	00369	CE 	1995	9	29	95ZZZX5229 	1	19950517	G	7602	12503172	BRACKET 			CESSNA	210 	210M 	2073450	CE 										THROTTLE	BROKEN 	B	S		NT2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	9036M	1455 				21062053				INSPECTION FOUND BRACKET FOR THROTTLE AND MIXTURE CONTROL MOUNT BROKEN.						1	H	7	1 	3O				3A21 					 
1995020300360	19950203	00360	CE 	1995	2	3	95ZZZX523 	1	19950109	G	2750	262504510	SWITCH 			LEAR 	55 	55LEAR 	5170702	CE 										FLAP LIMIT	FAILED 	B		A	EZ1R	O				OTHER 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			EA	11	8010X	48 			4381	096				FLAPS FAILED IN FULL DOWN POSITION. TROUBLESHOOTING FOUND POWER AT BOTH UP AND DOWN PINS OF FLAP CONTROL VALVE. FOUND 	RT FLAP (19 DEGREES/21 DEGREES) LIMIT MICROSWITCH MAINTAINED CONTINUITY IN ALL SWITCH LINKAGE POSITIONS. REPLACED SWITC	H AND SYSTEM OPERATED NORMALLY. AIRCRAFT RETURNED TO SERVICE. NOTE: LEFT LIMIT SWITCH PREVIOUSLY REPLACED WHEN FLAPS 	FAILED AT 8 DEGREES. BOTH SWITCHES WERE INSTALLED IN DECEMBER, 1994. LEFT SWITCH TT 35 HOURS/RT SWITCH TT 48 HOURS.			2	L	7	2 	4F				A10CE 					 
1995092900370	19950929	00370	SO 	1995	9	29	95ZZZX5230 	2	19950828	G	7414	4370	MAGNETO 	SLICK 		BBAVIA	7 	7KCAB 	21101P3	CE 	CONT 	O360 	IO360E 	17025	SO 					ENGINE	FAILED 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			SW	01	57678				94010167	41774	L512755A			ENGINE INTERMITTENTLY RUNNING ROUGH. MAGNETOS BOTH HAD 1,786 HOURS SINCE INSTALLATION. SABOTAGE PAINT APPLIED BY MANUF	ACTURER WAS NOT DISTURBED INDICATING NO 500-HOUR INSPECTIONS HAD BEEN PERFORMED. INSPECTION SHOWED TRACES OF 'CROSS-FIR	ING' IN DISTRIBUTOR AREAS OF BOTH MAGNETOS. SUBMITTER RECOMMENDS INSPECTIONS WHEN DUE WILL FIND SMALL PROBLEMS PREVENTI	NG PREMATURE REPLACEMENT.			1	H	7	1 	3O	3	O		A759 	E1CE				 
1995092900371	19950929	00371	SO 	1995	9	29	95ZZZX5231 	2	19950828	G	7414	4371	MAGNETO 	SLICK 		BBAVIA	7 	7KCAB 	21101P3	CE 	CONT 	O360 	IO360E 	17025	SO 					ENGINE	FAILED 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			SW	01	57678				94090555	41774	L512755A			ENGINE INTERMITTENTLY RUNNING ROUGH. MAGNETOS BOTH HAD 1,786 HOURS SINCE INSTALLATION. SABOTAGE PAINT APPLIED BY MANUF	ACTURER WAS NOT DISTURBED INDICATING NO 500-HOUR INSPECTIONS HAD BEEN PERFORMED. INSPECTION SHOWED TRACES OF 'CROSS-FIR	ING' IN DISTRIBUTOR AREAS OF BOTH MAGNETOS. SUBMITTER RECOMMENDS INSPECTIONS WHEN DUE WILL FIND SMALL PROBLEMS PREVENTI	NG PREMATURE REPLACEMENT.			1	H	7	1 	3O	3	O		A759 	E1CE				 
1995092900372	19950929	00372	CE 	1995	9	29	95ZZZX5232 	1	19950915	G	3231	S217840095	HOSE 			CESSNA	210 	T210M 	2073451	CE 										NLG DOOR	FAILED 	B			NT2R	O				OTHER 				O			OTHER 			AP	APPROACH 	1			CE	07	6597B	1314 				21062792				NOSE GEAR DOOR OPEN HOSE PARTED FROM FITTING AFTER GEAR DOWN MODE WAS SELECTED. MAIN LANDING GEAR WOULD NOT LOCK DOWN. 	 HYDRAULIC HOSE AS LISTED LOST ALL HYDRAULIC FLUID SO THE MAIN GEAR WOULD NOT HAVE PRESSURE TO LOCK INTO DOWN POSITION. 	 EMERGENCY LANDING WAS MADE WITH NOSE GEAR LOCKED DOWN AND MAIN GEAR SWINGING LOOSE.				1	H	7	1 	3O				3A21 					 
1995092900373	19950929	00373	SO 	1995	9	29	95ZZZX5233 	1	19950830	G	3221	028672	FITTING 			PIPER 	PA32 	PA32RT300 	7103215	SO 										NLG ATTACH	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	222PP	544 				32R7985013				FITTING INSTALLED TO C/W AD 93-05-10 AND PIPER SB 955 WHICH CALL OUT KIT 766-253. P/N 02867-2 IS PART OF KIT AND IT CRA	CKED AT FORWARD OUTBOARD CORNER OF WELD. OUTSIDE OF CORNER WELDED ONLY. SUBMITTER STATED INSIDE SHOULD BE WELDED.					1	L	7	1 	3O				A3SO 					 
1995092900374	19950929	00374	CE 	1995	9	29	95ZZZX5234 	2	19950906	G	8530	646678	GUIDE SEAL 			MOONEY	M20 	M20K 	5870220	SW 	CONT 	O360 	TSIO360MB 	17025	CE 					NR 5-6 CYLS	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	52RJ	6 				251070	317071			AFTER COMPLAINCE WITH TELEDYNE CONTINENTAL SB CSB-95-4 REGARDING IMPROPERLY INSTALLED INTAKE VALVE GUIDE SEALS, FOUND 2 	OF 6 DEFECTIVE SEALS ON ENGINE NOTED. TWO FWD CYLINDERS NR 5 AND NR 6 HAD BROKEN SEALS. REMOVED AND REPLACED ALL INTAK	E VALVE GUIDE SEALS ON THIS ENGINE IAW TELEDYNE CONTINENTAL SB CSB-95-4. SUBMITTER RECOMMENDS ALL SEALS IN QUESTION INS	PECTED IAW THIS SB, BE REPLACED FOR ASSURANCE.			1	L	7	1 	3O	3	O		2A3 	E9CE				 
1995092900375	19950929	00375	EA 	1995	9	29	95ZZZX5235 	2	19950811	G	7261	3004116	SPACER COVER 								PWA 	PT6 	PT6* 	52043	EA 					SCAVENGE PUMP	SCORED 	B			MASR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01					PWC95M666					THE SCAVENGE PUMP SPACER COVER WAS SENT TO PW & C FOR OVERHAUL. PART WAS RETURNED TO D.T.S. AFTER THEY OVERHAULED AND I	NSPECTED PART. THE RETURNED PART HAS DEEP SCORING ON THE GEAR SURFACE AREA AND HAS NOT BEEN RECOATED PROPERLY. PART WI	LL BE RETURNED TO OVERHAUL FACILITY FOR REPAIR.									3	T			E2NE				 
1995092900377	19950929	00377	CE 	1995	9	29	95ZZZX5238 	1	19950626	G	2842	991424211	PROBE 			CESSNA	650 	650 	2076802	CE 										LT WING NR 7	LUG SHORTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	84G	5747 				6500045				PILOT REPORTED ERRATIC FUEL QUANTITY INDICATION DURING FLIGHT. PROBLEM COULD NOT BE DUPLICATED ON THE GROUND. INVESTIG	ATION REVEALED THE LOA-Z WIRE LUG AT FUEL QUANTITY PROBE NR 7 WAS VERY CLOSE TO THE FORWARD FUEL VENT LINE AND WAS APPAR	ENTLY, THROUGH TEMPERATURE CHANGE OR WING MOVEMENT, RUBBING ON LINE EFFECTIVELY GROUNDING THE LO-Z LUG. INSTALLATION MA	KES IT DIFFICULT TO ALLOW SUFFICIENT MOVEMENT OF EITHER LINE OR TRANSMITTER TO ALLEVIATE CONTACT. LINE WAS REPOSITIONED	 AS FAR AS POSSIBLE AND A TEFLON STRAP WAS INSTALLED AS AN INSULATOR. THIS APPEARS TO BE MORE A DESIGN FLAW THAN AN INS	TALLATION ERROR AND MAY BE RECTIFIED PERHAPS BY SB USING A SIMILAR METHOD AS ABOVE.	2	L	7	2 	4F				A9NM 					 
1995092900378	19950929	00378	CE 	1995	9	29	95ZZZX5239 	1	19950626	G	5280	6227001106	BRACKET 		6227001110 	CESSNA	650 	650 	2076802	CE 										RT MLG DOOR	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	84G	5747 				6500045				DURING A SCHEDULED INSPECTION, DISCOVERED THE RT MLG DOOR CRADLE BRACKET CRACKED APPROXIMATELY THREE-FOURTHS OF THE WAY 	THROUGH AT THE BEND WHERE IT ATTACHES TO THE FORWARD SIDE OF MAIN GEAR DOOR. NOTICED THE NEW BRACKET RECEIVED FROM CESS	NA WAS MADE OF STAINLESS AND THE CRACKED BRACKET WAS MADE OF ALUMINUM OR MAGNESIUM. INSTALLED NEW BRACKET, ADJUSTED, AN	D CYCLED GEAR TO CHECK FAIR. SUGGEST THIS AREA GET CLOSE SCRUTINY DURING PRE-FLIGHT INSPECTIONS UNTIL NEWER BRACKETS AR	E INSTALLED.		2	L	7	2 	4F				A9NM 					 
1995092900379	19950929	00379	CE 	1995	9	29	95ZZZX5240 	1	19950626	G	3610	3021096	DUCT 			CESSNA	500 	500CESSNA 	2076602	CE 										INNER BYPASS	CRACKED 	C		A		O				OTHER 				N			FALSE WARNING 			CR	CRUISE 	1			EA	23	27SF					5000064				AT CRUISE, PILOT NOTED ITT ON LEFT ENGINE FLUCTUATING AND THEN DROPPING TO ZERO. ALL OTHER ENGINE INSTRUMENTS READ NORM	AL. AIRCRAFT LANDED WITHOUT INCIDENT. INITIAL INVESTIGATION SHOWED PROBLEM TO BE ISOLATED TO THE LEFT ENGINE ITT HARNE	SS. AIRCRAFT WAS FERRIED TO A P & W ENGINE REPAIR FACILITY WHERE IT WAS DISCOVERED THE AFT INNER BYPASS DUCT WAS CRACKE	D AND BROKEN AND HAD RUBBED THROUGH THE ITT HARNESS. HARNESS WAS REPLACED, DUCT WAS REPAIRED, AND RE-INSTALLED. SUBMIT	TER SUGGESTS THE OUTER BYPASS DUCT BE REMOVED AT PERIODIC ENGINE INSPECTIONS TO INSPECT THIS AREA FOR POSSIBLE CRACKS.		1	L	7	2 	4F				A22CE 					 
1995092900380	19950929	00380	CE 	1995	9	29	95ZZZX5241 	1	19950720	G	2430		ELECTRICAL SYS 			BEECH 	60 	60 	1153602	CE 										DC SYSTEM	FAULTY 	B			NVIR	A	O			UNSCHED LANDING 	OTHER 			H			ELECT. POWER LOSS-50 PC 			CR	CRUISE 	1			SW	05	44EL					036				AIRCRAFT EXPERIENCED ELECTRICAL FAILURE IN-FLIGHT. BOTH GENERATORS DROPPED OFF LINE. SWITCHED TO EMERGENCY BUS AND LAN	DED WITHOUT FURTHER PROBLEMS. TROUBLESHOT SYSTEM AND WAS UNABLE TO DETERMINE EXACT PROBLEM. INSTALLED NEW GENERATORS S	AME PN 6058003-1 LEFT AND RIGHT AND REPAIRED GCU'S SAME P/N GCSG505-16B. PARALLELED GENERATORS AND OPERATIONAL CHECKS W	ERE GOOD. LEARJET TUCSON RECOMMENDED REPLACEMENT OF ALL 4 COMPONENTS. TSN AIRCRAFT AND COMPONENTS, 305.9 HOURS S/N'S 	OFF, START/GEN 1307 AND 1274. GCU'S, 1090B AND 1085B.		1	L	7	2 	3O				A12CE 					 
1995092900381	19950929	00381	CE 	1995	9	29	95ZZZX5242 	1	19950901	G	3610	1299103391	DUCT 			BEECH 	1900 	1900D 	1154162	CE 										LT ENG BLEED	BROKEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	166K	2267 				UE63				A THIRTY DEGREE SPLIT IN ITT WAS REPORTED WITH LEFT ENGINE RUNNING HIGHER THAN RIGHT. A POWER ASSURANCE RUN VERIFIED A 	PROBLEM WITH THE LEFT BLEED AIR CONTROL SYSTEM. FUNCTIONAL CHECKS OF THE LEFT BLEED SYSTEM WERE UNRELIABLE AND DID NOT 	AGREE WITH TROUBLESHOOTING NARRATIVES IN THE BEECH 1900D MM. A VISUAL INSPECTION REVEALED THE LEFT BLEED AIR DUCT WAS B	ROKEN AT THE TEMPERATURE CONTROL BOSS. THE DUCT WAS REPLACED WITH A NEW UNIT.			2	L	7	2 	4T			RT	A24CE 					 
1995092900382	19950929	00382	EU 	1995	9	29	95ZZZX5243 	2	19950707	G	7250	9514M71P04	SHAFT 								CFMINT	CFM56 	CFM563B2 	13802	EU 					HPT ROTOR	FAILED 	B			R3AR	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	05		15859			D21448		725345			ENGINE WAS REMOVED FROM SERVICE DUE TO VIBRATION. DISASSEMBLY OF THE ENGINE REVEALED A SECTION OF THE HPT REAR SHAFT HA	D LIBERATED CAUSING EXTENSIVE DAMAGE WITHIN THE HPT AND LPT MAJOR MODULES. FAILURE INVESTIGATION IS BEING CONDUCTED.										4	F			E21EU				 
1995092900383	19950929	00383	EA 	1995	9	29	95ZZZX5244 	1	19950822	G	3244	256K433	TIRE TREAD 	GOODYEARAERO		CNDAIR	CL601 	CL6013A 	8070802	EA 										NR 3	SEPARATED 	D				O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			EA	25	399SW	463 			42130724	5009				NR 3 TIRE TREAD SEPARATED CAUSING DAMAGE TO WOW HARNESS RIGHT GEAR. REPLACED WHEEL ASSY AND WOW HARNESS ASSY. TIRE HAD	 171 LANDINGS. GEAR RETRACTION CHECK C/W.					2	L	7	2 	4F			RT	A21EA 					 
1995092900384	19950929	00384	EA 	1995	9	29	95ZZZX5245 	2	19950817	G	7310	230317502	SOLENOID 			CNDAIR	CL600 	CL6001A11 	1900302	EA 	LYC 	ALF502	ALF502* 	41580	EA 					FUEL SOV	FAULTY 	B			JO1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	91UC	1445 			1504	1051	LF03101			WHILE PERFORMING AN OVERSPEED SHUT-DOWN CHECK ON THE RIGHT ENGINE, THE ENGINE FAILED TO SHUT DOWN WHEN THE OVERSPEED TES	T SWITCH WAS THROWN. UPON INITIAL INVESTIGATION, FOUND THE RIGHT ENGINE OVERSPEED ANNUNCIATOR WAS ON, BUT WOULD NOT RES	ET UNTIL THE SHUT-OFF VALVE WAS TAPPED. THE SHUT-OFF VALVE WAS REPLACED, BUT DID NOT CURE THE ORIGINAL PROBLEM. (THAT 	WAS TRACED TO THE CONTROLLER).			2	L	7	2 	4F	4	F	RT	A21EA 	E6NE				 
1995092900385	19950929	00385	NE 	1995	9	29	95ZZZX5246 	2	19950817	G	7323	230305204	CONTROLLER 			CNDAIR	CL600 	CL6001A11 	1900302	EA 	LYC 	ALF502	ALF502L 	41580	NE 					ENGINE OVERSPEED	FAILED 	B			JO1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	91UC	1445 			3009	1051	LF03101			WHILE PERFORMING AN OVERSPEED SHUT-DOWN CHECK ON RIGHT ENGINE, THE ENGINE FAILED TO SHUT DOWN WHEN OVERSPEED TEST SWITCH	 WAS THROWN. THE PROBLEM WAS TRACED TO THE OVERSPEED CONTROLLER. THE UNIT WAS REPLACED AND OPS CHECKED NORMAL.					2	L	7	2 	4F	4	F	RT	A21EA 	E6NE				 
1995092900386	19950929	00386	NE 	1995	9	29	95ZZZX5247 	2	19950817	G	7261	230328701	OIL LINE 			CNDAIR	CL600 	CL6001A11 	1900302	EA 	LYC 	ALF502	ALF502L 	41580	NE 					LT ENG PYLON	CHAFED 	B			JO1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	25	90UC	4397 				1023	LF03059			DURING A 100-HOUR PYLON INSPECTION, THE OIL FILTER TO NR 12 STRUT OIL LINE ASSEMBLY WAS FOUND CHAFING AGAINST THE 4 BOLT	 HEADS THAT SECURE THE APRON FRAME SUPPORT TO THE ENGINE. ONE CHAFE HAD BEGUN TO SEEP. THE OIL LINE IS FLATTENED OUT I	N THIS AREA TO PROVIDE CLEARANCE. THE NEW LINE, WHEN INSTALLED, FIT WITH PLENTY OF CLEARANCE.				2	L	7	2 	4F	4	F	RT	A21EA 	E6NE				 
1995092900387	19950929	00387	CE 	1995	9	29	95ZZZX5248 	1	19950818	G	3246	50300010133	WHEEL 	BFGOODRICH 		BEECH 	90 	E90 	1152914	CE 										LT MLG	BEARING FAILED 	D				O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			SW	03	676J					LW179				LEFT MAIN WHEEL CAME OFF ON TAKEOFF. INSPECTION REVEALED OUTSIDE BEARING FAILURE. DISINTEGRATION OF BEARING, RACE, CUP	 AND HOUSING ALLOWED WHEEL TO EXIT OVER AXLE NUT. SUBMITTER STATED POSSIBLE DEFECT DURING MANUFACTURE. CLOSE INSPECTIO	N OF BEARINGS AT EACH RECOMMENDED PERIOD SUGGESTED. BEARING IS A TIMKEN, P/N 07100.				1	L	7	2 	3T				3A20 					 
1995092900388	19950929	00388	SW 	1995	9	29	95ZZZX5249 	1	19950711	G	2720		CONTROL CABLE 			GULSTM	690TP 	690B 	7630516	SW 										RUDDER	FRAYED 	B		A	FB2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	999FG	279 				11535				DURING C/W TWIN COMMANDER SB NR 195B, FOUND BOTH AFT RUDDER CABLES TO HAVE NUMEROUS STRANDS BROKEN. INSTRUCTIONS IN THE	 SB DO NOT ADDRESS THE REMOVAL AND INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14. THIS I	S THE ONLY WAY TO PROPERLY INSPECT CABLES. SUBMITTER STATED HAVE FOUND MANY, MANY AIRCRAFT WITH CABLE STRANDS BROKEN BE	YOND THE LIMITS IN THE SB WHILE INSPECTING IN THIS MANNER. SUGGEST OWNERS C/W SI-199, WHICH INSTALLS LARGER PULLEYS AT 	THIS LOCATION.		1	H	7	2 	3T			 	2A4 					 
1995092900389	19950929	00389	SW 	1995	9	29	95ZZZX5250 	1	19950831	G	5751		SKIN 			GULSTM	690TP 	690C 	7630517	SW 										LT AILERON LE	CRACKED 	B		A	FB2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	47TT	2890 				11600				DURING THE COURSE OF A 100-HOUR INSPECTION, FOUND THE LT AILERON LEADING EDGE SKIN CRACKED AT THE INBOARD MOST BALANCE W	EIGHT ATTACHMENT SCREWS. THE CRACKS RANGED FROM .75 INCH TO 1.75 INCH IN LENGTH AND TOTALED 7 IN NUMBER. THERE WAS NO 	REPAIR FOR THIS DAMAGE, HAD TO FABRICATE AND INSTALL A NEW LEADING EDGE SKIN ASSEMBLY. NO DAMAGE FOUND IN THE RT AILERO	N.			1	H	7	2 	3T				2A4 					 
1995092900390	19950929	00390	CE 	1995	9	29	95ZZZX5251 	1	19950626	G	2910	6000100201	TUBE 			BEECH 	60 	60 	1153602	CE 										HYD SYSTEM	FAILED 	B			GIKR	A				UNSCHED LANDING 				K			FLUID LOSS 			NR	NOT REPORTED 	1			NM	01	228N	494 				031				HYDRAULIC TUBE LOCATED BETWEEN HYD RESERVOIR AND EXTERNAL SERVICE RETURN FITTING RUPTURED IN-FLIGHT. ACFT LANDED WITHOU	T DAMAGE EXCEPT FOR A BLOWN NR 4 TIRE WHEN EMERG BRAKING APPLIED. SUBMITTER SUSPECTS THIS LINE WAS WEAKENED BY REPEATED	 THERMAL EXPANSION OF HYD FLUID TRAPPED BETWEEN CHECK VALVE AND EXTERNAL FITTING. THIS LINE COULD NOT THEN HANDLE THE E	XCESS PRESSURE WHEN THE RT ENG DRIVEN HYD PUMP FAILED TO SELF-REGULATE AND CAUSED AN OVER PRESSURE CONDITION. LEARJET A	LERT SB A60-29-2 IN WORK. MAIL OUT DUE MID-OCTOBER, 1995.		1	L	7	2 	3O				A12CE 					 
1995092900391	19950929	00391	CE 	1995	9	29	95ZZZX5253 	1	19950907	G	2820	79326	CLAMP 		W99116DE 	LEAR 	55 	55C 	5170706	CE 										FUEL FILTER	DEFECTIVE 	G		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	40CR	1399 				144				INSPECTION FOUND FUEL FILTER CLAMP FAULTY. THIS IS FOLLOW-UP ON PREVIOUSLY SUBMITTED REPORT. SUBMITTER RECOMMENDED THA	T CLAMPS UTILIZED IN AREAS SUBJECT TO VIBRATION BE SAFTIED WITH WIRE TO PREVENT INADVERTENT OPENING.					2	L	7	2 	4F			RT	A10CE 					 
1995092900392	19950929	00392	WP 	1995	9	29	95ZZZX5254 	2	19950824	G	7313	8687432	SHROUD 			BEECH 	100 	B100 	1152919	CE 	GARRTT	TPE331	TPE3316 	01514	WP 					LT ENGINE	MISINSTALLED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	21	524BA					BE99	P27206			THE LEFT ENGINE WAS VERY SLOW TO START. INVESTIGATION REVEALED THE FUEL NOZZLE SHROUD WAS INSTALLED 180 DEGREES FROM CO	RRECT POSITION WHICH BLOCKED FUEL FLOW THROUGH THE NOZZLE CAUSING SLOW STARTS. THE FUEL NOZZLES HAD BEEN REPLACED 291.1	 HOURS PREVIOUSLY. REPLACED ALL NOZZLES TO CORRECT THE PROBLEM.				1	L	7	2 	4T	4	T		A14CE 	E4WE				 
1995092900393	19950929	00393	CE 	1995	9	29	95ZZZX5255 	1	19950906	G	3246	5030010133	WHEEL 			BEECH 	90 	E90 	1152914	CE 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	379VM					LW27				CRACKS WERE FOUND IN THE BOLT HOLES OF THE WHEEL HALF CAUSING THE TIRE TO DEFLATE MORE THAN THE ALOTTED AMOUNT.						1	L	7	2 	3T				3A20 					 
1995092900395	19950929	00395	GL 	1995	9	29	95ZZZX5257 	3	19950906	G	6111	C130195	BLADE CLAMP 			DHAV 	DHC6 	DHC6300 		EA 						HARTZL	HCB3T	HCB3TN5 	GL 	DOWEL PIN	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17		17940			CC4821			BU7022		BLADE CLAMP IS CRACKED WHERE THE HOLE IS DRILLED FOR COUNTERWEIGHT DOWEL PIN.						1	H	7	2 	3T				A9EA 		6	C	P15EA	 
1995092900396	19950929	00396	CE 	1995	9	29	95ZZZX5258 	1	19950901	G	2820	25160283	TUBE ASSY 			LEAR 	35 	31A 	5170531	CE 										TAILCONE	CHAFED 	B		A	TJ4R	K				NONE 				B	K		SMOKE/FUMES/ODORS/SPARKS 	FLUID LOSS 		IN	INSP/MAINT 	1			GL	11	741E	1194 				070				FUEL ODOR NOTICED INSIDE TAILCONE DURING ROUTINE 1,200-HOUR INSPECTION. TRACED TO LT ENGINE MAIN FUEL TUBE ASSY WHERE I	T PASSES NEXT TO CABIN AIR DISTRIBUTION DUCT COUPLING. THE COUPLING LOCK TAB HAD CHAFED THROUGH THE TUBE. WITH FUEL PR	ESSURE UP, THE FUEL WOULD SPRAY INTO THE TAILCONE IN A MIST. REPLACED TUBE. RE-POSITIONED COUPLING FOR PROPER CLEARANC	E. SUBMITTER STATES CLOSE PROXIMITY OF FUEL AND HYD LINES IN THE TAILCONE WITH STRUCTURE AND OTHER COMPONENTS CONTINUES	 TO BE A PROBLEM WITH LEARJETS.		2	L	7	2 	4F			RT	A10CE 					 
1995092900503	19950929	00503	NE 	1995	9	29	95ZZZX5259 	2	19950121	G	7250	430144801	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	117MA	109 			0791973	7107	LE45155E			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900504	19950929	00504	NE 	1995	9	29	95ZZZX5260 	2	19950121	G	7230	430135702	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	117MA	109 			019	7107	LE45155E			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900505	19950929	00505	NE 	1995	9	29	95ZZZX5261 	2	19950121	G	7261	430101501	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					GOV/FCU/STARTER	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	117MA	109 				7107	LE45155E			ACCESSORY DRIVE SEALS LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900506	19950929	00506	NE 	1995	9	29	95ZZZX5262 	2	19950121	G	7261	430101201	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ALTERNATOR	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	117MA	109 				7107	LE45155E			ALTERNATOR FORWARD SEAL LEAKING BEYOND SERVICEABLE LIMITS REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900507	19950929	00507	NE 	1995	9	29	95ZZZX5263 	2	19950121	G	7261	230307203	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					CSD	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	117MA	109 				7107	LE45155E			CSD LIP SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900508	19950929	00508	NE 	1995	9	29	95ZZZX5264 	2	19950121	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					FIRST TURBINE	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117MA	274 				7107	LE45155E			FIRST TURBINE SHROUD SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900509	19950929	00509	SW 	1995	9	29	95ZZZX5265 	1	19950413	G	6330	222331617101	ISOLATION MOUNT 	LORD 		BELL 	222 	222 	1182122	SW 										M/R XMSN	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	30SV	458 			BW385A	47044				LATERAL ISO MOUNT ELASTOMERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WTIH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H9SW 					 
1995092900510	19950929	00510	NE 	1995	9	29	95ZZZX5266 	2	19950228	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	420MB	880 				7077	LE45282E			FIRST TURBINE SEALS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW 2 EACH UNITS(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900511	19950929	00511	NE 	1995	9	29	95ZZZX5267 	2	19950518	G	7210	430125301	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					RED GEARBOX	ROUGH 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	420MB	938 				7077	LE45382E			ANNULAR BALL BEARING ROUGH. REPLACED WITH 4 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900512	19950929	00512	NE 	1995	9	29	95ZZZX5268 	2	19950518	G	7261	430101501	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					GOV FCU STARTER	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	420MB	475 				7077	LE45382E			ACCESSORY DRIVE SEALS LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH 3 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900513	19950929	00513	NE 	1995	9	29	95ZZZX5269 	2	19950518	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	420MB	677 				7077	LE45382E			FIRST TURBINE SHROUD SEAL RING WORN BEYOND SERVICEABLE LIMITS.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900514	19950929	00514	NE 	1995	9	29	95ZZZX5270 	2	19950519	G	7250	430144801	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	424MB	62 			0492445	7082	LE45078			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900515	19950929	00515	NE 	1995	9	29	95ZZZX5271 	2	19950519	G	7230	430135703	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	424MB	62 			320	7082	LE45078			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900521	19950929	00521	NE 	1995	9	29	95ZZZX5277 	2	19950420	G	7261	230307203	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					CSD LIP	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	527SF	350 				7111	LE45306E			CSD DRIVE LIP SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900522	19950929	00522	NE 	1995	9	29	95ZZZX5278 	2	19950420	G	7261	430101201	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ALTERNATOR FWD	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	527SF	371 				7111	LE45306E			ALTERNATOR FORWARD SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WTIH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900523	19950929	00523	NE 	1995	9	29	95ZZZX5279 	2	19950420	G	7261	430101301	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ALTERNATOR AFT	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	527SF	371 				7111	LE45306E			ALTERNATOR AFT SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WTH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900524	19950929	00524	NE 	1995	9	29	95ZZZX5280 	2	19950420	G	7230	430135703	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	527SF	371 			513	7111	LE45306E			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900525	19950929	00525	NE 	1995	9	29	95ZZZX5281 	2	19950420	G	7250	430144801	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	527SF	371 			0591540	7111	LE45306E			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900526	19950929	00526	EU 	1995	9	29	95ZZZX5282 	1	19950504	G	7714	56337078012	TACHOMETER 			SNIAS 	350 	AS350B2 	8680813	EU 										ENGINE NG	FAILS 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	92LG	78 	261 		261	2575				NG TACK INDICATOR, UNIT PEAKS OR GOES TO ZERO INTERMITTENTLY. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995092900527	19950929	00527	EU 	1995	9	29	95ZZZX5283 	1	19950427	G	6420	1053170018	FITTED BOLT 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117MA	375 				7107				FITTED BOLT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900528	19950929	00528	EU 	1995	9	29	95ZZZX5284 	1	19950420	G	7810	1176506401	BRACKET 			BOLKMS	117 	BK117A3 	5626015	EU 										EJECTOR BOTTOM	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117MA	565 				7107				BRACKET CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900529	19950929	00529	EU 	1995	9	29	95ZZZX5285 	1	19950601	G	7810	1176506401	BRACKET 			BOLKMS	117 	BK117A3 	5626015	EU 										EJECTOR BOTTOM	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117MA	73 				7107				BRACKET CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900530	19950929	00530	EU 	1995	9	29	95ZZZX5286 	1	19950530	G	6420	ABWT82008	BEARING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117CW	198 				7125				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900533	19950929	00533	NE 	1995	9	29	95ZZZX5289 	2	19950518	G	7230	430135702	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	420MB	938 			729	7077	LE45382E			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900534	19950929	00534	NE 	1995	9	29	95ZZZX5290 	2	19950518	G	7250	430144801	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	420MB	677 			05920417	7077	LE45382E			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900535	19950929	00535	WP 	1995	9	29	95ZZZX5291 	2	19950303	G	7310	39423041	SOLENOID VALVE 			MTSBSI	MU2 	MU2B60 	5780460	CE 	GARRTT	TPE331	TPE33110 	01514	WP 					FUEL SOV	FAILED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	454MA				6589	1535SA	P36357C			SOLENOID VALVE NO RESPONSE WHEN POWERED. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	H	7	2 	3T	4	T	RT	A10SW 	E4WE				 
1995092900536	19950929	00536	NE 	1995	9	29	95ZZZX5292 	2	19950712	G	7230	430135702	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	428MB	508 			256	7088	LE45154			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WTIH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900537	19950929	00537	EU 	1995	9	29	95ZZZX5293 	1	19950323	G	3340	2LA00162500	LIGHT 			BOLKMS	117 	BK117A3 	5626015	EU 										TAIL	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	428MB					7088				TAIL LIGHT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900538	19950929	00538	EU 	1995	9	29	95ZZZX5294 	1	19950323	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	428MB					7088				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900539	19950929	00539	EU 	1995	9	29	95ZZZX5295 	1	19950611	G	7712	G555674	TRANSDUCER 			BOLKMS	117 	BK117B1 	5626012	EU 										ENG TORQUE	FAILED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5194C	843 			796	7169				TRANSDUCER FAILED. CONTINUOUS ROTATING INDICATION. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900540	19950929	00540	NE 	1995	9	29	95ZZZX5296 	2	19950328	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					FIRST TURBINE	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5194C	304 				7169	LE45522E			FIRST TURBINE SHROUD SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900541	19950929	00541	NE 	1995	9	29	95ZZZX5297 	2	19950328	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	5194C	304 			782	7169	LE45522E			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900542	19950929	00542	NE 	1995	9	29	95ZZZX5298 	2	19950328	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	5194C	304 			04920455	7169	LE45522E			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900543	19950929	00543	EU 	1995	9	29	95ZZZX5299 	1	19950301	G	6420	AWT82008	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	527SF	69 				7111				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900544	19950929	00544	NE 	1995	9	29	95ZZZX5300 	2	19950509	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	528SF	609 				7104	LE45295E			FIRST TURBINE SHROUD SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900545	19950929	00545	EU 	1995	9	29	95ZZZX5301 	1	19950415	G	6230	1051011305	BELLOWS 			BOLKMS	117 	BK117A3 	5626015	EU 										SWASHPLATE	TORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	528SF	432 				7104				BELLOWS IS TORN AROUND CLAMP AND FOLD AREAS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900546	19950929	00546	EU 	1995	9	29	95ZZZX5302 	1	19950522	G	6730	AC67246	SERVO 	DUNLOP 		SNIAS 	350 	AS350B 	8680801	EU 										M/R	FEEDBACK 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	58045	24 			QN018	1602				FORE AND AFT SERVO FEEDBACK. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995092900547	19950929	00547	NE 	1995	9	29	95ZZZX5303 	2	19950317	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	7060G	290 			434	7173	LE45988			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900548	19950929	00548	NE 	1995	9	29	95ZZZX5304 	2	19950317	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	7060G	290 			05920411	7173	LE45988			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900549	19950929	00549	EU 	1995	9	29	95ZZZX5305 	1	19950524	G	6320	IPT20RT1100080G	TRANSMITTER 			BOLKMS	117 	BK117B1 	5626012	EU 										XMSN OIL PRESS	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	205 			42043136	7173				TRANSMITTER UNIT CAUSES PRESSURE GAUGE TO READ LOW AND FLUCTUATE. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900550	19950929	00550	EU 	1995	9	29	95ZZZX5306 	1	19950314	G	6320	IPT20RT1100080G	TRANSMITTER 			BOLKMS	117 	BK117B1 	5626012	EU 										XMSN PRESS	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	385 			44613173	7173				TRANSMITTER FAULTY. ERRATIC INDICATOR READINGS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995092900551	19950929	00551	NE 	1995	9	29	95ZZZX5307 	2	19950425	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	71703	561 			751	7227	LE45755E			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900552	19950929	00552	NE 	1995	9	29	95ZZZX5308 	2	19950425	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	71703	561 			84940454	7227	LE45755E			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900553	19950929	00553	EU 	1995	9	29	95ZZZX5309 	1	19950515	G	7930	DK040	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										OIL PRESS	INOPERATIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	722MB	571 			7078	S754				TRANSMITTER UNIT INOPERATIVE. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H3EU 					 
1995092900554	19950929	00554	NE 	1995	9	29	95ZZZX5310 	2	19950324	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	911VU	591 			723	7141	LE45540E			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900555	19950929	00555	NE 	1995	9	29	95ZZZX5311 	2	19950324	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	911VU	591 			35783	7141	LE45540E			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995092900556	19950929	00556		1995	9	29	95ZZZX5312 	4	19950315	G	3120	B1894522282A	CLOCK 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT PANEL	FAULTY 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	1246 			704466	2654				CLOCK WILL NOT RESET. KNOB WAS TIGHT, BUT LOOSENED TO REMOVE FROM PANEL. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995092900558	19950929	00558	NE 	1995	9	29	95ZZZX5314 	2	19950828	G	7250	569551	GUIDE VANE 			RKWELL	NA265 	NA26560 	7630106	CE 	PWA 	JT12 	JT12A8 	52042	NE 					1ST STAGE	BURNED 	B	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	8NR	1227 				306141	P638049NB			ENGINE RECEIVED FOR CORR & HOT SECT INSP PER SB 1508. ENG OPERATED TO 1,227 HRS TIME SINCE LAST HOT SECT INSP. ENG SUF	FERED LOSS OF 3 EA NOZZLE GUIDE VANES COMPLETELY BURNED IN HALF ALLOWING INNER SHROUD HALVES TO ENTER GAS PATH & DAMAGE 	TURB. FAILURE RESULTED IN DOMESTIC OBJECT DAMAGE OF ALL 92 EA 1ST STAGE & 46 EA 2ND STAGE TURB BLADES. P & W SB 1508, 	REV NR 16, OUTLINES RECOMMENDED 1,500 HR HOT SECT INSP INTERVAL. FAILURE IS PARTICULAR TO JT12A-8 ENG PARTICULAR TO NA2	6540 (DASH 8 CONFIGURED) & ALL 60 MDL ACFT. SUBMITTER STATES HAVE EXPERIENCED 30-40 ENG OVER LAST 6 YRS THAT SUFFERED N	OZZLE GUIDE VANE FAILURES & SUBSEQUENT TURB BLADE IMPACT DAMAGE FROM NOZZLE GUIDE VANE MATL RELEASED INTO TURB GAS PATH.	2	L	7	2 	4J	4	J	RT	A2WE 	1E9				 
1995100600010	19951006	00010	NE 	1995	10	6	95ZZZX5366 	2	19950509	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					LT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	528SF	1807 	1089 		SC04224	7104	LE45295E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 15, MINUS 0.009 INCH. REPLACED WITH NEW UNITS(S) CORRECTED P	ROBLEM. PART TOTAL CYCLES, 4296.4.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600011	19951006	00011	NE 	1995	10	6	95ZZZX5367 	2	19950712	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					LT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	428MB	1597 	508 		SC20597	7088	LE45154			FAILED SB LT5101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 4, MINUS 0.011 INCH. REPLACED WITH NEW UNIT(S) CORRECTED PR	OBLEM. PART TOTAL CYCLES 3925.7.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600012	19951006	00012	NE 	1995	10	6	95ZZZX5368 	2	19950621	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	420MB	786 	218 		SC13879	7077	LE45244E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 5, MINUS 0.017 INCH, NR 8, MINUS 0.011 INCH, NR 9, MINUS 0.00	9 INCH, NR 12, MINUS 0.010 INCH. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM. PART TOTAL CYCLES, 2920.6.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600013	19951006	00013	NE 	1995	10	6	95ZZZX5369 	2	19950606	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	625MB	1036 	253 		SC20475	7108	LE45247E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 11, MINUS 0.011 INCH. REPLACED WITH NEW UNIT(S) CORRECTED PR	OBLEM. PART TOTAL CYCLES, 3314.5.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600014	19951006	00014	NE 	1995	10	6	95ZZZX5370 	2	19950724	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A4 	5626017	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					LT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117CW	1474 			SC20562	7125	LE45344E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 10, MINUS 0.0105 INCH, NR 14, MINUS 0.0105 INCH. PART TOTAL 	CYCLES, 3533.5.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600015	19951006	00015	NE 	1995	10	6	95ZZZX5371 	2	19950613	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117MA	1377 	367 		SC12226	7107	LE45132			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 16, MINUS 0.010 INCH, NR 22, MINUS 0.010 INCH. PART TOTAL CY	CLES, 2230.5.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600016	19951006	00016	NE 	1995	10	6	95ZZZX5372 	2	19950829	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5188B	709 			SC47941	7163	LE45757E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 1, PLUS 0.010 INCH, NR 26, PLUS 0.012 INCH. REPLACED WITH US	ED UNIT, CORRECTED PROBLEM. PART TOTAL CYCLES, 1136.9					1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600018	19951006	00018	NE 	1995	10	6	95ZZZX5374 	2	19950420	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					LT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	527SF	1457 	371 		SC12211	7111	LE45306E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 15, PLUS 0.013 INCH. REPLACED WITH NEW UNIT(S) CORRECTED PRO	BLEM. PART TOTAL CYCLES, 3477.8.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600019	19951006	00019	NE 	1995	10	6	95ZZZX5375 	2	19950425	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	71703	561 			SC12095	7227	LE45755E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 11, PLUS 0.014 INCH. PART TOTAL CYCLES 1304.9.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600020	19951006	00020	NE 	1995	10	6	95ZZZX5376 	2	19950228	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	420MB	1752 	880 		SC17237	7077	LE45282			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 7, PLUS 0.011 INCH, NR 12, PLUS 0.018 INCH, NR 17, PLUS 0.010	 INCH, NR 18, PLUS 0.010 INCH. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM. PART TOTAL CYCLES, 5811.3.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600021	19951006	00021	NE 	1995	10	6	95ZZZX5377 	2	19950518	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					LT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	420MB	2111 	938 		SC12532	7077	LE45382E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 5, PLUS 0.012 INCH, NR 26, PLUS 0.009 INCH. REPLACED WITH NE	W UNIT(S) CORRECTED PROBLEM. PART TOTAL CYCLES, 5788.1.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600022	19951006	00022	NE 	1995	10	6	95ZZZX5378 	2	19950312	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					LT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	424MB	2226 	1194 		SC12045	7082	LE45313			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 7, PLUS 0.008 INCH, NR 10, PLUS 0.008 INCH. REPLACED WITH USE	D UNIT, CORRECTED PROBLEM. PART TOTAL CYCLES 4406.5.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600023	19951006	00023	NE 	1995	10	6	95ZZZX5379 	2	19950518	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	428MB	1294 	745 		SC12068	7088	LE45033E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 8, PLUS 0.016 INCH. REPLACED WITH USED UNIT, CORRECTED PROBL	EM. PART TOTAL CYCLES 2967.6.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600024	19951006	00024	NE 	1995	10	6	95ZZZX5380 	2	19950811	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	527SF	374 	164 		SC20438	7111	LE45132E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT. REPLACED WITH USED UNIT, CORRECTED PROBLEM. PART TOTAL CYCLES	, 540.1.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600025	19951006	00025	NE 	1995	10	6	95ZZZX5381 	2	19950817	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					LT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	424MB	940 	162 		SC20410	7082	LE45306E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT. REPLACED WITH USED UNIT, CORRECTED PROBLEM. PART TOTAL CYCLES	, 3788.0.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600026	19951006	00026	NE 	1995	10	6	95ZZZX5382 	2	19950622	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					LT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7059N	1273 			SC04098	7154	LE45987E			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 22, MINUS 0.018 INCH, NR 20, MINUS 0.010 INCH. PART TOTAL CY	CLES, 2747.2.					1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600027	19951006	00027	NE 	1995	10	6	95ZZZX5383 	2	19950717	G	7250	414129001	ROTOR ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					RT ENG TURB	BLADE SHIFT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7059N	2356 			SC12802	7154	LE45754			FAILED SB LT101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT NR 12, PLUS 0.012 INCH. REPLACED WITH REPAIRED UNIT, CORRECTED 	PROBLEM. PART TOTAL CYCLES, 5344.3.					1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600286	19951006	00286	EU 	1995	10	6	95ZZZX5456 	1	19950822	G	6410	10531754	BLADE 		15031754 	BOLKMS	105 	BO105S 	5626006	EU 										CAMBER SIDE	SEPARATION 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	107AL	2804 				S772				DAILY INSPECTION FOUND BLADE SEPARATED 9 INCHES FROM TIP AND 2 INCHES FROM LEADING EDGE ON CAMBER SIDE OF BLADE. SEPARA	TED AT FACE PLATE TRANSITION AREA. SEPARATION BEYOND LIMITS.					1	G	7	2 	3U				H3EU 					 
1995100600289	19951006	00289	SW 	1995	10	6	95ZZZX5459 	1	19950830	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1084Y		358 			45433				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 357.7.				1	G	7	1 	3U				H2SW 					 
1995100600290	19951006	00290	SW 	1995	10	6	95ZZZX5460 	1	19950830	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1084Y		358 			45433				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 357.7.				1	G	7	1 	3U				H2SW 					 
1995100600291	19951006	00291	SW 	1995	10	6	95ZZZX5461 	1	19950830	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	174AL		585 			52067				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 585.2.				1	G	7	1 	3U			NC	H2SW 					 
1995100600292	19951006	00292	SW 	1995	10	6	95ZZZX5462 	1	19950830	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	174AL		585 			52067				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 585.2.				1	G	7	1 	3U			NC	H2SW 					 
1995100600293	19951006	00293	NE 	1995	10	6	95ZZZX5463 	1	19950901	G	6320	S163520211	TOP CASE 			SKRSKY	S58T 	S58ET 	8141803	NE 										M/R GRBOX	CRACKED 	A		A	NYBA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	26567	8176 	1281 		1804	581514				MAIN GEARBOX TOP CASE CRACKED AT FORWARD SUPPORT TUBE ATTACHMENT POINT. REPLACED MAIN GEARBOX TOP CASE PN S1635-20211 W	ITH NEW.					2	G	7	2 	4U				1H11 					 
1995100600294	19951006	00294	SW 	1995	10	6	95ZZZX5464 	1	19950830	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206B3 	1181506	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2155Z		493 			3476				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 492.7.				1	G	7	1 	3U				H2SW 					 
1995100600295	19951006	00295	SW 	1995	10	6	95ZZZX5465 	1	19950830	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206B3 	1181506	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2155Z		493 			3476				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 492.7.				1	G	7	1 	3U				H2SW 					 
1995100600296	19951006	00296	SW 	1995	10	6	95ZZZX5466 	1	19950830	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3186P		414 			45776				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 413.8.				1	G	7	1 	3U				H2SW 					 
1995100600297	19951006	00297	SW 	1995	10	6	95ZZZX5467 	1	19950830	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3186P		414 			45776				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 413.8.				1	G	7	1 	3U				H2SW 					 
1995100600298	19951006	00298	SW 	1995	10	6	95ZZZX5468 	1	19950811	G	6310	206040272101	BOOT 		206040015015	BELL 	206 	206L1 	1182107	SW 										INPUT DRIVESHAFT	TORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A	1136 				45256				ON DAILY INSPECTION FOUND BOOT TORN DUE TO DETERIORATION CAUSED BY CHEMICAL CONTAMINATION.						1	G	7	1 	3U				H2SW 					 
1995100600299	19951006	00299	SW 	1995	10	6	95ZZZX5469 	1	19950830	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350AL		271 			51429				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 271.1.				1	G	7	1 	3U				H2SW 					 
1995100600300	19951006	00300	SW 	1995	10	6	95ZZZX5470 	1	19950830	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350AL		271 			51429				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 271.1.				1	G	7	1 	3U				H2SW 					 
1995100600301	19951006	00301	SW 	1995	10	6	95ZZZX5471 	1	19950817	G	2435	02560005	FRICTION DISC 		23081018 	BELL 	206 	206L3 	1182108	SW 										CLUTCH	MISSING 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	355AL					51444				OVERHAUL FOUND FRICTION DISC WAS MISSING FROM CLUTCH ALLOWING DRIVESHAFT TO BECOME LOOSE WHEN GENERATOR CAME TO ELECTRIC	 SHOP.					1	G	7	1 	3U				H2SW 					 
1995100600302	19951006	00302	SW 	1995	10	6	95ZZZX5472 	1	19950817	G	6410	206016201127	BLADE 		206011810125	BELL 	206 	206L3 	1182108	SW 										T/R	PAINT PEEL 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL	840 			CS6670	51460				NORMAL MAINTENANCE FOUND PAINT PEELING ON TIP OF T/R BLADE FROM LEADING EDGE.						1	G	7	1 	3U				H2SW 					 
1995100600304	19951006	00304	SW 	1995	10	6	95ZZZX5474 	1	19950830	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	366AL		412 			51470				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 412.4.				1	G	7	1 	3U				H2SW 					 
1995100600305	19951006	00305	SW 	1995	10	6	95ZZZX5475 	1	19950830	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	366AL		412 			51470				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH, 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. WORN PARTS TT, 412.4.				1	G	7	1 	3U				H2SW 					 
1995100600306	19951006	00306	NE 	1995	10	6	95ZZZX5476 	1	19950809	G	6322	10E933	SHAFT 		763080790210	SKRSKY	S76 	S76A 	8143006	NE 										SPLINES	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	709AL	4113 	651 			760278				REMOVED AT ENGINE CHANGE. OIL COOLER BLOWER SHAFT SPLINES WORN EXCESSIVELY.						1	G	7	2 	3U				H1NE 					 
1995100600309	19951006	00309	NE 	1995	10	6	95ZZZX5479 	2	19950121	G	7250	411104055	SEAL ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					LABYRINTH	GROOVED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117MA	439 				7107	LE45155E			LABYRINTH SEAL IS EXCESSIVELY GROOVED FROM GP DISC KNIFE EDGES. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600310	19951006	00310	NE 	1995	10	6	95ZZZX5480 	2	19950121	G	7250	411100720	SHROUD 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					GP BLADE	TIP RUB 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117MA	109 			1A29	7107	LE45155E			GAS PRODUCER SHROUD HAS EXCESSIVE GP BLADE TIP RUB. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600311	19951006	00311	EU 	1995	10	6	95ZZZX5481 	1	19950313	G	7714	430106201	SPEED PICKUP 			BOLKMS	117 	BK117A3 	5626015	EU 										ENGINE	ERRATIC 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	127HH	32 			9N0067	7060				SPEED PICK-UP ERRATIC. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600312	19951006	00312	EU 	1995	10	6	95ZZZX5482 	1	19950529	G	6420	ABWT82008	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	17SJ	337 				7230				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600313	19951006	00313		1995	10	6	95ZZZX5483 	4	19950413	G	3425	071105200	TRANSMITTER 	BENDIX 	KMT112 	BOLKMS	117 	BK117A3 	5626015	EU 										RMI/HSI	FAILED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	158BK	35 			46129	7058				TRANSMITTER DEFECTIVE. SPINS RMI/HSI. CARDS IN SLAVE MODE. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600314	19951006	00314	EU 	1995	10	6	95ZZZX5484 	1	19950223	G	6220	1051418103	FLANGE BUSHING 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R	SCORED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	158BK	5 				7058				FLANGE BUSHING HAS EXCESSIVE SCORING. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600316	19951006	00316	EU 	1995	10	6	95ZZZX5486 	1	19950519	G	6410	134616P	BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5194C	627 				7169				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW 2 EACH UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600317	19951006	00317	EU 	1995	10	6	95ZZZX5487 	1	19950519	G	6410	134617P	BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5194C	627 				7169				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600318	19951006	00318	EU 	1995	10	6	95ZZZX5488 	1	19950519	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5194C	719 				7169				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600319	19951006	00319	NE 	1995	10	6	95ZZZX5489 	2	19950509	G	7250	430144801	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	528SF	354 			0492483	7104	LE45295E			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600320	19951006	00320	NE 	1995	10	6	95ZZZX5490 	2	19950509	G	7230	430135703	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	528SF	354 			386	7104	LE45295E			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600321	19951006	00321	EU 	1995	10	6	95ZZZX5491 	1	19950504	G	6220	10513103505	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	387 			181203	7173				BOLT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600322	19951006	00322	EU 	1995	10	6	95ZZZX5492 	1	19950504	G	6220	10513103505	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	387 			181258	7173				BOLT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600323	19951006	00323	EU 	1995	10	6	95ZZZX5493 	1	19950525	G	6510	551253	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R DRIVE	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	71703	270 				7227				METAL DUST COMING FROM T/R DRIVE BEARINGS. REPLACED WITH NEW 4 EACH UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600324	19951006	00324	EU 	1995	10	6	95ZZZX5494 	1	19950325	G	6420	1053170023	BEARING 			BOLKMS	105 	BO105S 	5626006	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	722MB	156 				S754				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H3EU 					 
1995100600325	19951006	00325	GL 	1995	10	6	95ZZZX5495 	2	19950512	G	7250	6898764	SEAL 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					OIL BELLOWS	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	911BH	110 				685	CAT37299			OIL BELLOW SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995100600326	19951006	00326	GL 	1995	10	6	95ZZZX5496 	2	19950310	G	7250	A23007202	BEARING 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					NR 6 MAIN	SPALLED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911BH	53 			123	685	CAT24854			NR 6 MAIN BEARING SPALLING. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995100600327	19951006	00327	NE 	1995	10	6	95ZZZX5497 	2	19950324	G	7250	414144001	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					ENGINE	PITTED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911VU	831 			K575	7141	LE45540E			BEARING OUTER RACE HAS EXCESSIVE PITTING. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600328	19951006	00328	NE 	1995	10	6	95ZZZX5498 	2	19950324	G	7250	430136201	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911VU	831 			3482	7141	LE45540E			NR 3 BEARING, EXCESSIVE ROLLER WEAR. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600329	19951006	00329	NE 	1995	10	6	95ZZZX5499 	2	19950705	G	7250	0292507660	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1D 		NE 					SCAVENGE LINE	LEAKS 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	94LG	262 	1 		541	2728	9334			REAR BEARING LEAKS AT THE SCAVENGE LINE BOSS. REPLACED BRONZE CRUSH SEAL TWICE WITH NO SUCCESS. IT WAS FOUND THE REAR 	BEARING HAD A SMALL NICK WHICH PREVENTED THE CRUSH SEAL FROM SEATING PROPERLY. SUSPECT SOMEONE NICKED THE REAR BEARING 	WHILE CLEANING COKE FROM MODULE 4. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.				1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995100600330	19951006	00330	EU 	1995	10	6	95ZZZX5500 	1	19950811	G	2612	B332M	FIRE DETECTOR 			BOLKMS	105 	BO105S 	5626006	EU 										NR 2 ENG COMPT	FAILED 	B			ALGR	A				UNSCHED LANDING 				N			FALSE WARNING 			HO	HOVERING 	1			SW	03	4572V	5007 	34 			S665				DURING HOVER OUT, NR 2 FIRE LIGHT ILLUMINATED. CHECKED FOR SMOKE. NO SMOKE VISIBLE. FIRE LIGHT WENT OUT. WHILE HOVER	ING BACK TO THE PAD, FIRE LIGHT ILLUMINATED AGAIN. AGAIN, NO SMOKE VISIBLE. LANDED AIRCRAFT. CONTACTED MAINTENANCE. D	URING TROUBLESHOOTING, FOUND CENTER UPPER FIRE DETECTOR ON NR 2 ENGINE BAD. REPLACED FIRE DETECTOR WITH SERVICEABLE DET	ECTOR.			1	G	7	2 	3U				H3EU 					 
1995100600331	19951006	00331		1995	10	6	95ZZZX5501 	4	19950104	G	3422	109290	GYRO 	LEARSIEGLER 		BOLKMS	117 	BK117A3 	5626015	EU 										YAW CSAS	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	420MB	442 			0477	7077				GYRO UNIT REMOVED BECAUSE OF YAW CSAS KICK. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600332	19951006	00332	CE 	1995	10	6	95ZZZX5502 	1	19950829	G	7931	99103101	TRANSDUCER 	EDCLIFF 		CESSNA	441 	441 	2076020	CE 										OIL PRESSURE	ERRATIC 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	441RC	374 			28107	4410076				ERRATIC INDICATOR OPERATION. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	L	7	2 	3T			RT	A28CE 					 
1995100600333	19951006	00333	CE 	1995	10	6	95ZZZX5503 	1	19950822	G	7722	8974768	RESISTOR 			MTSBSI	MU2 	MU2B60 	5780460	CE 										ENGINE TEMP	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	479MA	7 			94130971293	15535A				ERRATIC TEMP INDICATIONS AT HIGH POWER SETTINGS. WORKS FINE UPON INITIAL START-UP. REPLACED WTH NEW UNIT(S) CORRECTED 	PROBLEM.					1	H	7	2 	3T			RT	A10SW 					 
1995100600334	19951006	00334	EU 	1995	10	6	95ZZZX5504 	1	19950629	G	6410	704A33633171	HINGE 			AEROSP	AS355 	AS355F1 	8680810	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5787M	130 				5067				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	2 	3U				H11EU 					 
1995100600335	19951006	00335	EU 	1995	10	6	95ZZZX5505 	1	19950301	G	6410	704A33633116	BEARING 			AEROSP	AS355 	AS355F1 	8680810	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5787M	275 				5067				LAMINATED BEARING ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 4 EACH NEW UNITS FROM KIT 355A09-1036-00, 	CORRECTED PROBLEM.					1	G	7	2 	3U				H11EU 					 
1995100600336	19951006	00336	EU 	1995	10	6	95ZZZX5506 	1	19950802	G	7400	355A72302300	TRANSDUCER 			AEROSP	AS355 	AS355F1 	8680810	EU 										IGNITION SYS	INOPERATIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5787M	344 			1002	5067				IGNITION TRANSDUCER UNIT INOPERATIVE. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H11EU 					 
1995100600337	19951006	00337	EU 	1995	10	6	95ZZZX5507 	1	19950627	G	6330	355A38004005	REAR BAR 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R XMSN	BEARING DEFECT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5787M	194 			M2414	5067				LOWER SPHERICAL BEARING PULLED. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H11EU 					 
1995100600338	19951006	00338	EU 	1995	10	6	95ZZZX5508 	1	19950824	G	6720	3160S88100454	CONTROL CABLE 			AEROSP	SA316 	SA316B 	8680207	EU 										T/R DRUM	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	67081					2184				EXCESSIVE DISCOLORATION AND CRACKING OF CABLE COATING AROUND T/R DRUM AREA. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM	.					1	G	7	1 	4U			 	H1IN 					 
1995100600339	19951006	00339	EU 	1995	10	6	95ZZZX5509 	1	19950419	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911LR	189 				2404				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600340	19951006	00340	EU 	1995	10	6	95ZZZX5510 	1	19950613	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911LR	93 				2404				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600341	19951006	00341	EU 	1995	10	6	95ZZZX5511 	1	19950323	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	92LG	146 				2575A				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00.						1	G	7	1 	3U				H9EU 					 
1995100600342	19951006	00342	EU 	1995	10	6	95ZZZX5512 	1	19950328	G	6410	704A33633116	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	183 				2654				LAMINATED BEARING ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS FROM KIT 355A09-1036-00, CORRECT	ED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600343	19951006	00343	EU 	1995	10	6	95ZZZX5513 	1	19950327	G	5210	350A25109521	JETTISON ROD 			SNIAS 	350 	AS350B2 	8680813	EU 										DOOR	WEAK 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	1264 				2654				DOOR JETTISON ROD WEAK. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600344	19951006	00344	EU 	1995	10	6	95ZZZX5514 	1	19950328	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	49 				2654				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW 2 EACH UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600345	19951006	00345	EU 	1995	10	6	95ZZZX5515 	1	19950729	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	214 				2654				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600346	19951006	00346	EU 	1995	10	6	95ZZZX5516 	1	19950405	G	5210	350A25109521	JETTISON ROD 			SNIAS 	350 	AS350B2 	8680813	EU 										DOOR	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	94LG	767 				2728				DOOR JETTISON ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600347	19951006	00347	EU 	1995	10	6	95ZZZX5517 	1	19950405	G	6330	704A33633151	LAMINATED MEMBER			SNIAS 	350 	AS350B2 	8680813	EU 										M/R XMSN	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	94LG	767 				2728				LAMINATED MEMBER ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WTIH 4 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600348	19951006	00348	EU 	1995	10	6	95ZZZX5518 	1	19950405	G	6330	704A33633153	LAMINATED MEMBER			SNIAS 	350 	AS350B2 	8680813	EU 										M/R XMSN	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	94LG	767 				2728				LAMINATED MEMBER ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600349	19951006	00349	EU 	1995	10	6	95ZZZX5519 	1	19950412	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	94LG	298 				2728				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600503	19951006	00503	CE 	1995	10	6	95ZZZX5521 	1	19950913	G	2822	2017002	PUMP 	TRW 		RKWELL	NA265 	NA26540 	6402608	CE 										LT FUEL BOOST	FAILED 	B				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	312NT		50 		100853D	282032				PUMP REMOVED FROM AIRCRAFT WITH 49.7 HOURS T.I.S. SINCE OVERHAUL DUE TO INTERNAL FAILURE, CAUSING BOOST PUMP CIRCUIT BRE	AKER TO TRIP. PILOT STATED THE BREAKER WOULD NOT RESET. THESE PUMPS HAVE A 2,000 HOUR SERVICE LIFE, BUT HAVE EXPERIENC	ED MANY PREMATURE FAILURES IN FLEET OF 17 AIRCRAFT. PUMP WAS OVERHAULED BY REPAIR STATION NR HAXR577E, W.O. L3202.				2	L	7	2 	4J				A2WE 					 
1995100600504	19951006	00504	CE 	1995	10	6	95ZZZX5522 	1	19950718	G	2760	20544470	FITTING 			CESSNA	650 	650 	2076802	CE 										SPOILER FILTER	FAILED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	39WP	5194 				6500039				DURING MAINTENANCE INSPECTION, OPERATION 10, ITEM CARD 27-20, INSPECTION REVEALED SPOILER SHUTTLE VALVE FILTER SEPARATED	 FROM MOUNTING FLANGE IN THE END OF ELBOW FITTING PERMITTING IT TO SLIDE BACK AND FORTH WITHIN THE FITTING. THIS NEGATE	D FILTERING CAPABILITIES. REPLACED ELBOW FILTER FITTING. SUBMITTER SUGGESTS EITHER POOR DESIGN OR POOR MANUFACTURING S	TANDARD CONTRIBUTED TO THIS DEFECT.			2	L	7	2 	4F				A9NM 					 
1995100600505	19951006	00505	CE 	1995	10	6	95ZZZX5523 	1	19950908	G	3230	53130441	CHANNEL 			CESSNA	402 	402C 	207590R	CE 										NLG UPLOCK ACT	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	402SA	6092 				402C0623				DURING INSPECTION, FOUND CHANNELS CRACKED. REMOVED AND REPLACED WITH NEW. SUSPECT CAUSE - HILOK'S BECAME LOOSE ON CHAN	NELS CAUSING BEND RADIUS TO CRACK.					1	L	7	2 	3O				A7CE 					 
1995100600506	19951006	00506	CE 	1995	10	6	95ZZZX5524 	1	19950908	G	3230	58130441	CHANNEL 			CESSNA	402 	402C 	207590R	CE 										NLG UPLOCK ACT	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	2711X	6863 				402C0116				DURING INSPECTION, FOUND CHANNELS CRACKED. REMOVED AND REPLACED WITH NEW. SUSPECT CAUSE - HILOK'S BECAME LOOSE ON CHAN	NELS CAUSING BEND RADIUS TO CRACK.					1	L	7	2 	3O				A7CE 					 
1995100600507	19951006	00507	EA 	1995	10	6	95ZZZX5525 	2	19950908	G	8530	71973	GASKET 			BEECH 	60 	B60 	1153605	CE 	LYC 	O541 	TIO541E1C4 	41536	EA 					INTAKE	FAILED 	B			FC6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	234RD	10 				P566				INTAKE TO CYLINDER GASKET FAILED NEAR BOLT HOLE AFTER 10 HOURS FLIGHT. SURFACE PLATE TEST REVEALED NO ABNORMALITIES IN 	SEALING SURFACE. GASKET SHOWED DEFINITE IMPRESSION FROM INTAKE TUBE - SEATED 360 DEGREES. GASKET SUPPLIER SUGGESTS A S	OFT SPOT ON THE GASKET WHICH FAILED.				1	L	7	2 	3O	3	O		A12CE 	E10EA				 
1995100600508	19951006	00508	GL 	1995	10	6	95ZZZX5526 	1	19950810	G	7120	2071000100	MOUNT 			DIAMON	DA20A1	DA20A1 	05626UX	GL 										ENGINE	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	605F	226 				10018				FOUND CRACKED RT REAR MOTOR MOUNT. RADIAL CRACKS EMANATING FROM SHOCK MOUNT BUSHING BRACKET. (BUSHING P/N 785-000).						1	L	7	1 	3O			NT	TA4CH 					 
1995100600509	19951006	00509		1995	10	6	95ZZZX5527 	2	19950823	G	7414	M3525	COIL 	SLICK 																MAGNETO	FAILED 	B			NILG	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25										THIS SLICK COIL IS ORANGE COLORED AND IS VERY PRONE TO FAILURE. SUBMITTER STATES HAVE CHANGED ABOUT 15 FAILED COILS SIN	CE 1985. HAVE SEEN ONLY ONE FAILURE OF A BENDIX COIL NAMED IN THE CURRENT BENDIX COIL A.D. SUBMITTER STRONGLY RECOMMEN	DS AN AIRWORTHY DIRECTIVE REQUIRING REPLACMEENT OF THIS COIL, BEFORE SOMEONE GETS HURT.																	 
1995100600510	19951006	00510	EA 	1995	10	6	95ZZZX5528 	2	19950912	G	8530	LW12416	CYLINDER 			CESSNA	172 	172P 	2072436	CE 	LYC 	O320 	O320D2J 	41508	EA 					HEAD ATTACH	BARREL CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	55404	718 				17275175	RL1533239A			CYLINDER BARREL CRACKED AT BASE OF THE 4TH COOLING FIN AWAY FROM CYLINDER HEAD ATTACH AREA. THIS IS SECOND CYLINDER TO 	FAIL IN THIS MANNER ON THIS SAME ENGINE SINCE OVERHAUL WITH NEW LYCOMING CYLINDERS.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995100600511	19951006	00511	GL 	1995	10	6	95ZZZX5529 	1	19950914	G	3230	HM6	ROD END 			AMTR 	300 	SX300 	05675EK	GL 										MLG ACTUATOR	FAILED 	G				O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			EA	01	83JH					83				PILOT COULD NOT GET RIGHT MAIN GEAR UP AND LOCKED, OR DOWN AND LOCKED. UPON LANDING, RIGHT GEAR COLLAPSED AND AIRCRAFT 	SKIDDED OFF RUNWAY. APPEARS HYDRAULIC ACTUATOR ROD END HAD PREVIOUSLY BEGUN TO CRACK AND FINALLY BROKE UPON TAKEOFF. R	ECOMMEND CLOSER INSPECTION OF ACTUATOR ROD ENDS DURING INSPECTIONS (FOR CRACKS).				1	L	7	1 	3O			RT	EXPA1L71					 
1995100600512	19951006	00512	EA 	1995	10	6	95ZZZX5530 	1	19950915	G	3213	9D255441	STRUT 	WIPLINEINC 	8000AMPHIB 	DHAV 	DHC3 	DHC3 	2800202	EA 										LT FWD FLOAT	BROKE 	C		A		O				OTHER 				O			OTHER 			LD	LANDING 	1			AL	05	472PM	512 				419				UPON LANDING WITH BOAT SWELLS IN THE AREA, LT FWD FLOAT STRUT, PN 9D2-5544-1, BROKE ALMOST IN HALF CAUSING ACFT TO LIST 	SOMEWHAT TO THE LEFT. NO SIGNS OF PREVIOUS WEAR OR CRACKS/BREAKS.					1	H	7	1 	3R				A815 					 
1995100600515	19951006	00515	WP 	1995	10	6	95ZZZX5533 	2	19950825	G	7250	30747553	BLADE 			CESSNA	650 	650 	2076802	CE 	GARRTT	TFE731	TFE731* 	01518	WP 					NR 3 LPT	SHROUD MISSING 	B			GMCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	5112	1526 				6507012	102125			ONE BLADE TIP SHROUD FOUND MISSING DURING POST-FLIGHT ON NR 3 LOW PRESSURE TURBINE.						2	L	7	2 	4F	4	F		A9NM 	E6WE				 
1995100600516	19951006	00516	SW 	1995	10	6	95ZZZX5534 	1	19950821	G	6310	476206165	SPRING 		476206165 	BELL 	47 	47G5 	1181032	SW 										FREEWHEEL	LOW TENSION 	B			OUGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	6288N	50 			A1239	7888				AIRCRAFT EXPERIENCED SLOW ROTOR ENGAGEMENT AT START-UP. TENSION DIMENSIONS AND FINISH OF FREEWHEEL SPRINGS VARY GREATLY	. SUBMITTER SUGGESTS BELL NEEDS TO IMPROVE QUALITY OF SPRINGS.					1	G	7	1 	3O				2H3 					 
1995100600517	19951006	00517	EA 	1995	10	6	95ZZZX5535 	2	19950904	G	7414	10382585	CONTACT POINTS 	BENDIX 	D4LN2021 	ENSTRM	F28 	F28C 	3300407	GL 	LYC 	O360 	IO360E1A 	41514	EA 					DUAL MAG	WORN FOLLOWER 	D				O				OTHER 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			SW	05	503H	338 				304	L152851A			ENGINE FAILED DUE TO BOTH SETS OF POINTS FAILING TO OPEN CAUSED BY EXCESSIVE WEAR OF PLASTIC CAM FOLLOWERS. SUSPECT LAC	K OF LUBRICATION AS NO OIL FOUND ON CAM OR IN FELT WIPER PADS. SUBMITTER SUGGESTS CHECK AND LUBE ON 100-HOUR INSPECTION	.				1	G	7	1 	3O	3	O		H1CE 	1E10				 
1995100600518	19951006	00518	WP 	1995	10	6	95ZZZX5536 	1	19950901	G	6410	55045	PLATES 			HILLER	UH12 	UH12E 	4360122	WP 										TENSION TORSION	FAILED 	G		A		A				UNSCHED LANDING 				D			INFLIGHT SEPARATION 			AG	AGRICULTURE 	1			WP	17	4027D	3711 			1388	5072				PILOT LOST TAIL ROTOR AUTHORITY WHILE SPRAYING TOMATOES. HELICOPTER MADE HARD LANDING WITH SUBSTANTIAL DAMAGE. ONE TAI	L ROTOR BLADE DEPARTED HELICOPTER PRIOR TO LANDING. INVESTIGATION REVEALED TENSION. TORSION PLATES (11) FAILED ALLOWIN	G BLADE TO DEPART.				1	G	7	1 	3O				4H11 					 
1995100600519	19951006	00519		1995	10	6	95ZZZX5537 	4	19950912	G	3416	59341A91	ALTIMETER 	UNITEDINST 		BELL 	206 	206B 	1181511	SW 										COCKPIT	HANG-UP 	D				K				NONE 				O			OTHER 			CR	CRUISE 	1			SO	17	223AJ				R7602	1734				PILOT REPORTED ALTIMETER HANG-UP AT 5,000 FEET. TESTED IN SHOP, UNIT STOPPED AT 12,000 FEET ON DESCENT. IT WOULD START	 AT 10,500 FEET. UPON DISASSEMBLY, INSPECTED INSHAKE ON ALL PIVOTS. THERE WAS NO INSHAKE AT ALL. THIS UNIT WAS MFG IN	 1979 AND WAS NEVER OVERHAULED SINCE.				1	G	7	1 	3U				H2SW 					 
1995100600520	19951006	00520	NE 	1995	10	6	95ZZZX5538 	2	19950822	G	7250	0292377110	SWIRL PLATE 			SKRSKY	S76 	S76C 	8143008	NE 	TMECA 	ARRIEL	ARRIEL1S 	60030	NE 					RT ENGINE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	399KK	424 			4739B	760421	15059			DURING 150-HOUR ENGINE INSPECTION, BORESCOPING RT ENGINE REVEALED CRACK ON SWIRL PLATE AND PIECES MISSING. DAMAGE BEYON	D LIMITS. REMOVED ENGINE, INSTALLED LOANER ENGINE. INSPECTION AT TEAR DOWN REVEALED NO OTHER DAMAGE. NEW TYPE SWIRL P	LATE TO BE INSTALLED AT MANUFACTURER OF ENGINE.				1	G	7	2 	3U	3	U	NC	H1NE 	E19EU				 
1995100600521	19951006	00521	GL 	1995	10	6	95ZZZX5539 	2	19950814	G	7321	23056935	FUEL CONTROL 	BENDIX 		HILLER	UH12 	UH12E 	4360122	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	MALFUNCTION 	B			PN5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	603RA		170 		335937	1527	831594			FUEL CONTROL WILL NOT RESPOND PROPERLY TO ADJUSTMENTS FOR START TEMPS. START TEMPS GO EITHER HOT OR COLD IN AN ERRATIC 	MANNER. RETURNED CONTROL FOR BENCH CHECK.					1	G	7	1 	3O	3	U		4H11 	E4CE				 
1995100600522	19951006	00522	GL 	1995	10	6	95ZZZX5540 	2	19950824	G	7323	23007501	GOVERNOR 	BENDIX 		HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE N2	FAILED 	G				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			SW	99	8639F		1762 		25869	1280431D	CAE832846			WHILE IN CRUISE FLIGHT, THE PILOT NOTICED A DECREASE IN MAIN ROTOR RPM AND THE NOSE OF THE HELICOPTER NOTICEABLY YAWED. 	 THE PILOT DECREASED COLLECTIVE PITCH, BUT THE ENGINE POWER AND ROTOR RPM CONTINUED TO DECREASE. THE ENGINE DID NOT FAI	L COMPLETELY. DURING THE TOUCH DOWN, THE HELICOPTER HIT THE GROUND HARD AND CUT OFF THE TAIL BOOM BY THE MAIN ROTORS. T	HE N2 GOVERNOR WAS REMOVED AS A SUSPECTED CONTRIBUTING FACTOR.			1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995100600523	19951006	00523	GL 	1995	10	6	95ZZZX5541 	2	19950824	G	7321	23057344	FUEL CONTROL 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE N1	FAULTY 	G				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			SW	99	8639F		405 		331134	128043D	CAE832846			WHILE IN CRUISE FLIGHT, THE PILOT NOTICED A DECREASE IN MAIN ROTOR RPM AND THE NOSE OF THE HELICOPTER NOTICEABLY YAWED. 	 THE PILOT DECREASED COLLECTIVE PITCH, BUT THE ENGINE POWER AND ROTOR RPM CONTINUED TO DECREASE. THE ENGINE DID NOT FAI	L COMPLETELY. DURING THE TOUCH DOWN, THE HELICOPTER HIT THE GROUND HARD AND CUT OFF THE TAIL BOOM BY THE MAIN ROTORS. T	HE N1 FUEL CONTROL WAS REMOVED AS A SUSPECTED CONTRIBUTING FACTOR.			1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995100600524	19951006	00524	EU 	1995	10	6	95ZZZX5542 	1	19950808	G	6220	350A31190700	STARFLEX 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R YELLOW STAR	BROKEN 	C			JLFL	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			WP	21	813CE	2178 			M2060	5010				AIRCRAFT SUFFERED SEVERE VIBRATION ON APPLICATION OF POWER AFTER START. AIRCRAFT HAD NOT TAKEN OFF. UPON EXAMINATION, 	THE YELLOW EAR OF THE STARFLEX WAS FOUND BROKEN OFF AND THE TAIL BOOM WAS BENT DOWNWARDS. CAUSE IS UNDER INVESTIGATION.					1	G	7	2 	3U				H11EU 					 
1995100600525	19951006	00525	SW 	1995	10	6	95ZZZX5543 	1	19950905	G	6710	206001344001	CYCLIC STICK 			BELL 	206 	206B 	1181511	SW 										LOWER END	BROKE 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	05	101PN					774				DURING THE POST-FLIGHT INSPECTION, THE PILOT EXERCISED THE CYCLIC CONTROL WITH THE HYDRAULIC POWER OFF. DURING THIS PRO	CEDURE, THE CYCLIC STICK BROKE COMPLETELY OFF WHERE IT CONNECTS TO THE CYCLIC PIVOT LEVER. CYCLIC STICK BROKE IN THE SA	ME MANNER AS DESCRIBED IN AD85-25-01 AND BELL ASB-206-85-29. LAST INSPECTION WAS JANUARY, 1995. AIRCRAFT TT, 11,220 HO	URS.			1	G	7	1 	3U				H2SW 					 
1995100600526	19951006	00526	CE 	1995	10	6	95ZZZX5544 	1	19950918	G	7920	701010K0122	LINE 			BEECH 	90 	E90 	1152914	CE 										OIL COOLER	SPLIT 	D				E				ENGINE SHUTDOWN 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	15	22TL					LW334				LEFT ENGINE OIL COOLER LINE SPLIT CAUSING LOSS OF OIL. LEFT ENGINE SHUT DOWN. OIL LINE WAS REPLACED, APRIL, 1995, AT 5	-YEAR INSPECTION.					1	L	7	2 	3T				3A20 					 
1995100600527	19951006	00527	CE 	1995	10	6	95ZZZX5545 	1	19950914	G	2822	2017002	PUMP 	TRW 		RKWELL	NA265 	NA26540 	6402608	CE 										FUEL BOOST	FAILURE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	311NT		6 		10015700D	282019				PUMP WAS REMOVED FROM AIRCRAFT WITH 5.6 HOURS TIME IN SERVICE SINCE OVERHAUL DUE TO PUMP CAUSED CIRCUIT BREAKER TO TRIP 	AND WOULD NOT RESET. UNIT WAS OVERHAULED BY REPAIR STATION NR HAXR577E UNDER WORK ORDER NR L3201 ON 7-17-95. THIS IS T	HE THIRD LOW-TIME FAILURE OF A FUEL BOOST PUMP IN FLEET OF 17 AIRCRAFT IN THE LAST 3 DAYS. AIRCRAFT TOTAL TIME: 13,140	.0 HOURS. LANDINGS: 13,403.			2	L	7	2 	4J				A2WE 					 
1995100600528	19951006	00528	CE 	1995	10	6	95ZZZX5546 	1	19950913	G	2822	2017002	PUMP 	TRW 		RKWELL	NA265 	NA26540 	6402608	CE 										FUEL BOOST	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	311NT		52 		1002108D	282019				PUMP WAS REMOVED FROM AIRCRAFT WITH 52.0 HOURS TIME IN SERVICE SINCE OVERHAUL DUE TO INTERNAL FAILURE CAUSING BOOST PUMP	 CIRCUIT BREAKER TO TRIP AND WOULD NOT RESET. PUMP WAS OVERHAULED BY REPAIR STATION NR NAXR577E ON 7-12-95 UNDER WORK O	RDER NR L3211. SUBMITTER STATES THESE PUMPS ARE 2,000 HOUR TIME-CHANGE ITEMS, BUT LOW-TIME FAILURES SUCH AS THIS ARE CO	MMON IN FLEET OF 17 AIRCRAFT. AIRCRAFT TOTAL TIME: 13,134.4 HOURS. LANDINGS: 13,400.			2	L	7	2 	4J				A2WE 					 
1995100600529	19951006	00529	CE 	1995	10	6	95ZZZX5547 	1	19950913	G	7830	2020002124	STANG 	ROHR 	2250012511 	BEECH 	MU300 	400BEECH 		CE 										LT THRUST REV	DEPARTED 	D		A		O				OTHER 				D			INFLIGHT SEPARATION 			NR	NOT REPORTED 	1			NM	01	440DS	1188 				RK8				LEFT OUTBOARD STANG DEPARTED THE AIRCRAFT IN-FLIGHT. NO DAMAGE TO THE AIRCRAFT WAS FOUND, FLIGHT CREW FELT NOTHING IN-F	LIGHT. ROHR SB BS 400 78-4 ADDRESSES THIS PROBLEM AND HAS KITS OUT TO FIX THE PROBLEM. SUBMITTER SUGGESTS THIS SHOULD 	BE AN AD.				2	H	7	2 	4F			RT	A16SW 					 
1995100600530	19951006	00530	CE 	1995	10	6	95ZZZX5548 	1	19950914	G	2150	1155550409	COMPRESSOR 			BEECH 	200 	200BEECH 	1152920	CE 										RT ENG AIR COND	CLUTCH FAILED 	B			UG1R	F				ACTIVATE FIRE EXT. 				B			SMOKE/FUMES/ODORS/SPARKS 			AP	APPROACH 	1			SW	03	999DT					BB138				IN-FLIGHT OCCURRENCE. SMOKE SEEN COMING FROM RIGHT ENGINE COWLING ON DOWNWIND LEG PRIOR TO LANDING. ENGINE COWLING OPE	NED UPON LANDING AND FIRE EXTINGUISHED BY USE OF ONBOARD EXTINGUISHER. CAUSE OF FIRE WAS FAILED CLUTCH ASSEMBLY ON AIR 	CONDITIONER COMPRESSOR. NO OTHER DAMAGE FOUND IN ENGINE COMPARTMENT.				1	L	7	2 	4T				A24CE 					 
1995100600532	19951006	00532	NE 	1995	10	6	95ZZZX5549 	2	19950713	G	7260	430101201	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					ALTERNATOR FWD	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	10UM	116 				7231	LE45807E			ALTERNATOR FORWARD SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600533	19951006	00533	NE 	1995	10	6	95ZZZX5550 	2	19950713	G	7260	230307203	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					CSD LIP	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	10UM	116 				7231	LE45807E			CSD LIP SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600534	19951006	00534	NE 	1995	10	6	95ZZZX5551 	2	19950713	G	7260	430124102	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					FCU GOV START	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	10UM	116 				7231	LE45807E			ACCESSORY SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600535	19951006	00535	NE 	1995	10	6	95ZZZX5552 	2	19950121	G	7230	411100212	NUT 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					COMPRESSOR	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	117MA	109 				7107	LE45155E			NUT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600536	19951006	00536	EU 	1995	10	6	95ZZZX5553 	1	19950603	G	6410	704A33633116	BEARING 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	151AC	823 				1173				LAMINATED BEARING ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 4 EACH NEW UNITS FROM KIT 355A09-1036-00, 	CORRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600537	19951006	00537	EU 	1995	10	6	95ZZZX5554 	1	19950703	G	6730	AC67246	SERVO 	DUNLOP 		SNIAS 	350 	AS350B 	8680801	EU 										PILOT VALVE	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	151AC	170 	8 		QN025	1173				SERVO LEAKING FROM PILOT VALVE AREA. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600538	19951006	00538	EU 	1995	10	6	95ZZZX5555 	1	19950622	G	6730	AC67246	SERVO 	DUNLOP 		SNIAS 	350 	AS350B 	8680801	EU 										FORE/AFT CYCLIC	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	151AC	994 			QC041	1173				FORE AND AFT CYCLIC MOVEMENT IS STIFF. REPLACED WITH UNIT K-BALLED FROM NEW B2, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600539	19951006	00539	CE 	1995	10	6	95ZZZX5556 	1	19950816	G	7712	99103313	TRANSDUCER 			CESSNA	441 	441 	2076020	CE 										ENG TORQUE	FAULTY 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	185GA	191 			4814238	4410066				ERRATIC TORQUE INDICATION. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	L	7	2 	3T			RT	A28CE 					 
1995100600540	19951006	00540	EU 	1995	10	6	95ZZZX5557 	1	19950417	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	3593X	289 			3594	1081				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600541	19951006	00541	EU 	1995	10	6	95ZZZX5558 	1	19950417	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	3593X	289 			3592	1081				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600542	19951006	00542	EU 	1995	10	6	95ZZZX5559 	1	19950417	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	3593X	289 			3593	1081				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WTIH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600543	19951006	00543	EU 	1995	10	6	95ZZZX5560 	1	19950621	G	6410	704A33633116	BEARING 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	3593X	402 				1081				LAMINATED BEARING ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 4 EACH NEW UNITS FROM KIT 355A09-1036-00, 	CORRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600544	19951006	00544	NE 	1995	10	6	95ZZZX5561 	2	19950312	G	7250	411105064	ROTARY ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					GAS PRODUCER	DISC DAMAGE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	424MB	814 			4395	7082	LE45313			DISC HAS EXCESSIVE DAMAGE (WARPED CAUSING LOOSE BLADES) RESULTING FROM LAB SEAL ELEMENT RUBBING INTO DISC KNIFE EDGES. T	HIS LAB SEAL HAS FEWER WELD POINTS AS COMPARED TO THE MORE RECENT SEAL DESIGN. THE LAB SEAL WAS INSTALLED NEW AS A PART	 OF SB 126 UPGRADE. HERE ARE THE VIBRATION RESULTS OF THE ENGINE TEST CELL RUN AT THE TIME THE ROTOR WAS INSTALLED NEW.	 DYNR = 0.16, GB-R = 0.21, AD-A = 0.26, PT-R = 0.15. PART TOTAL CYCLES, 1299.4.			1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995100600545	19951006	00545	EU 	1995	10	6	95ZZZX5562 	1	19950607	G	6220	1051410110	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R MAIN	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5188B	549 				7163				MAIN BOLT HAS WORN THREADS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600546	19951006	00546	EU 	1995	10	6	95ZZZX5563 	1	19950310	G	6210	1051585403	BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5188B	614 				7163				BUSHING ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WTH 8 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600547	19951006	00547	EU 	1995	10	6	95ZZZX5564 	1	19950517	G	6230	1051011305	BELLOWS 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R MAST	TORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5194C	566 				7169				MAST BELLOWS IS TORN AROUND CLAMP AND FOLD AREAS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600548	19951006	00548	EU 	1995	10	6	95ZZZX5565 	1	19950526	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5771C	447 				1369				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600549	19951006	00549	EU 	1995	10	6	95ZZZX5566 	1	19950818	G	6220	117775P	BALL JOINT 			SNIAS 	350 	AS350B 	8680801	EU 										STARFLEX	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5771C	356 				1369				STARFLEX BALL JOINT TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 3 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600550	19951006	00550	EU 	1995	10	6	95ZZZX5567 	1	19950215	G	6410	704A33633116	BEARING 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	58045	253 				1602				LAMINATED BEARING ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 4 EACH NEW UNITS FROM KIT 355A09-1036-00, 	CORRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600551	19951006	00551	EU 	1995	10	6	95ZZZX5568 	1	19950419	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	586BH	206 				7129				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600552	19951006	00552	EU 	1995	10	6	95ZZZX5569 	1	19950824	G	6420	3160S333005400	BEARING STACK 			AEROSP	SA316 	SA316B 	8680207	EU 										T/R	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	67081	227 			A31175	2184				BEARING STACK KNOTCHED AROUND INNER RACE. PILOT REPORT PEDAL STICKS DURING FLIGHT. REPLACED WITH NEW UNIT(S) CORRECTED	 PROBLEM.					1	G	7	1 	4U				H1IN 					 
1995100600553	19951006	00553	EU 	1995	10	6	95ZZZX5570 	1	19950824	G	6420	3160S333005400	BEARING STACK 			AEROSP	SA316 	SA316B 	8680207	EU 										T/R	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	67081	227 			A31165	2184				BEARING STACK KNOTCHED AROUND INNER RACE. PILOT REPORT PEDAL STICKS DURING FLIGHT. REPLACED WITH NEW UNIT(S) CORRECTED	 PROBLEM.					1	G	7	1 	4U				H1IN 					 
1995100600554	19951006	00554	EU 	1995	10	6	95ZZZX5571 	1	19950824	G	6420	3160S333005400	BEARING STACK 			AEROSP	SA316 	SA316B 	8680207	EU 										T/R	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	67081	227 			A31098	2184				BEARING STACK KNOTCHED AROUND INNER RACE. PILOT REPORT PEDAL STICKS DURING FLIGHT. REPLACED WITH NEW UNIT(S) CORRECTED	 PROBLEM.					1	G	7	1 	4U				H1IN 					 
1995100600555	19951006	00555	NE 	1995	10	6	95ZZZX5572 	2	19950622	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	7059N	250 			RE8I940626	7154	LE45987E			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600556	19951006	00556	NE 	1995	10	6	95ZZZX5573 	2	19950622	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	7059N	250 			781	7154	LE45987E			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600557	19951006	00557	NE 	1995	10	6	95ZZZX5574 	2	19950622	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7059N	250 				7154	LE45987E			SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600558	19951006	00558	EU 	1995	10	6	95ZZZX5575 	1	19950401	G	6220	10513103505	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7059N	440 			181281	7154				BOLT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600559	19951006	00559	NE 	1995	10	6	95ZZZX5576 	2	19950516	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	7060G	544 			05920414	7173	LE45583			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM T05K KIT CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600560	19951006	00560	NE 	1995	10	6	95ZZZX5577 	2	19950516	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	7060G	544 			144	7173	LE45583			NR 2 BEARING SEAL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600561	19951006	00561	NE 	1995	10	6	95ZZZX5578 	2	19950516	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	544 				7173	LE45583			SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995100600562	19951006	00562	EU 	1995	10	6	95ZZZX5579 	1	19950224	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	779LF	180 				1621				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600563	19951006	00563	EU 	1995	10	6	95ZZZX5580 	1	19950329	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	779LF	460 			3773	1621				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600564	19951006	00564	EU 	1995	10	6	95ZZZX5581 	1	19950329	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	779LF	460 			3780	1621				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600565	19951006	00565	EU 	1995	10	6	95ZZZX5582 	1	19950329	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	779LF	460 			3784	1621				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600566	19951006	00566	EU 	1995	10	6	95ZZZX5583 	1	19950418	G	7110	1176506401	BRACKET 			BOLKMS	117 	BK117B1 	5626012	EU 										COWL	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	90260	363 				7140				BRACKET CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600567	19951006	00567	EU 	1995	10	6	95ZZZX5584 	1	19950320	G	5240	117232371	GOOSE NECK 			BOLKMS	117 	BK117B1 	5626012	EU 										TRANSMISSION	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911VU	238 				7141				GOOSE NECK CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WTIH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600568	19951006	00568	EU 	1995	10	6	95ZZZX5585 	1	19950509	G	6420	ABWT82008	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911VU	678 				7141				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995100600569	19951006	00569	EU 	1995	10	6	95ZZZX5586 	1	19950210	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	92LG	417 			0194	2575				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600570	19951006	00570	EU 	1995	10	6	95ZZZX5587 	1	19950210	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	92LG	417 			0198	2575				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600571	19951006	00571	EU 	1995	10	6	95ZZZX5588 	1	19950210	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	92LG	417 			0192	2575				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WIT NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600572	19951006	00572	EU 	1995	10	6	95ZZZX5589 	1	19950221	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	134 				2654				LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CO	RRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600573	19951006	00573	EU 	1995	10	6	95ZZZX5590 	1	19950803	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	482 			3877	2654				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600574	19951006	00574	EU 	1995	10	6	95ZZZX5591 	1	19950803	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	482 			3864	2654				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600575	19951006	00575	EU 	1995	10	6	95ZZZX5592 	1	19950803	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	482 			3865	2654				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995100600576	19951006	00576	EU 	1995	10	6	95ZZZX5593 	1	19950728	G	6410	704A33633116	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LG	214 				2654				LAMINATED BEARING ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 4 EACH NEW UNITS FROM KIT 355A09-1036-00, 	CORRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995100600577	19951006	00577	EU 	1995	10	6	95ZZZX5594 	1	19950531	G	6730	AC67246	SERVO 	DUNLOP 		SNIAS 	350 	AS350B2 	8680813	EU 										PILOT VALVE	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	94LG	1522 	610 		DA165	2728				SERVO LEAKING AT PILOT VALVE. REPLACED WITH OVERHAULED UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995101300172	19951013	00172	CE 	1995	10	13	95ZZZX5595 	1	19950826	G	2612		WIRE 			BEECH 	99 	99 	1154002	CE 										RT ENG DET SYS	CHAFED 	B			APCR	O				OTHER 				N			FALSE WARNING 			NR	NOT REPORTED 	1			NM	01	2880A					U109				ON 8-26-95, PILOT EXPERIENCED FIRE WARNING LIGHT ON RIGHT ENGINE. CAUSE DETERMINED TO BE FAULTY (CHAFED) WIRING IN DETE	CTOR SYSTEM. ERRONEOUS INDICATION, NO ACTUAL FIRE.					1	L	7	2 	3T			 	A14CE 					 
1995101300173	19951013	00173	CE 	1995	10	13	95ZZZX5596 	1	19950822	G	2436		REGULATOR 			BEECH 	99 	99 	1154002	CE 										LT VOLTAGE	FAILED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	2880A					U109				EXACT FAILURE SEQUENCE UNKNOWN. AFTER TOTAL ELECTRICAL FAILURE, MAINTENANCE FACILITY FOUND LEFT VOLTAGE REGULATOR AND R	EVERSE-CURRENT RELAY RUINED INTERNALLY. SUBITTER SUSPECTS VOLTAGE FLUCTUATIONS CAUSED RIGHT SYSTEM TO DROP OFF-LINE. T	ROUBLESHOOTING STILL IN PROGRESS AT THIS TIME.				1	L	7	2 	3T				A14CE 					 
1995101300174	19951013	00174	SW 	1995	10	13	95ZZZX5597 	1	19950712	G	3610	88027685	TUBE 			GULSTM	690TP 	690A 	0141722	SW 										TAIL SECT	FAILED 	B			DJFR	O				OTHER 				H			ELECT. POWER LOSS-50 PC 			NR	NOT REPORTED 	1			EA	23	333CA	3882 				11136				PILOT REPORTED LOSS OF ALL PRIMARY ELECTRICAL FLIGHT INSTRUMENTS AS WELL AS ALL AVIONICS. TROUBLESHOT AND FOUND TUBE FA	IILED AT AFT FLARE. COMPLIED WITH ROCKWELL SL 327 TO CORRECT PROBLEM. NOTE: TUBING PRE SL 327 WAS ALUMINUM, POST SL 3	27 WAS STAINLESS STEEL.				1	H	7	2 	3T				2A4 					 
1995101300175	19951013	00175	SO 	1995	10	13	95ZZZX5598 	2	19950816	G	8520	642360	CRANKCASE 			CESSNA	210 	T210M 	2073451	CE 	CONT 	O520 	TSIO520R 	17040	SO 					NR 5 CYLINDER	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	6994B	3034 	461 			21062868	512941			CRACK IN THE CRANKCASE ON THE FORWARD LOWER PORTION OF NR 5 CYLINDER, RUNNING THROUGH THE LOWER FORWARD CYLINDER MOUNTIN	G STUD.					1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995101300177	19951013	00177	CE 	1995	10	13	95ZZZX5600 	1	19950830	G	7112	U842705H	CLAMP 			CESSNA	340 	340A 	2076405	CE 										CYL INTERCOOLER	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	68707	3000 				340A1515				THE CLAMPS ON THE FLEX DUCT THAT CONNECTS THE INTERCOOLER TO THE NR 1 AND NR 2 CYLINDERS ARE TOO LARGE AND BOTTOM OUT BE	FORE THEY REACH THE REQUIRED TORQUE OF 30-35 PSI. THE PARTS CATALOG CALLS OUT FOR A U84-270SH CLAMP OF THE CYLINDER AND	 A U84-260SH CLAMP AT THE INTERCOOLER. IT WOULD BE BETTER IF BOTH WERE A U84-260-SH. THIS DUCT BLEW OFF AT THE CYLINDE	R IN A FULL POWER TEST RUN OF NR 2 CYLINDER.			1	L	7	2 	3O				3A25 					 
1995101300178	19951013	00178	SO 	1995	10	13	95ZZZX5601 	1	19950912	G	7810	78011	STACK 			PIPER 	PA31 	PA31P 	7103120	SO 										NR 6 EXHAUST	BROKEN 	B			EKIR	E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			O			OTHER 			CL	CLIMB 	1			WP	07	18MC					31P7300143				NR 6 EXHAUST STACK BROKEN AT FLANGE. LEAKING EXHAUST GASSES DAMAGED WIRING AND COWL NEXT TO STACK. PROBLEM OCCURRED DU	RING CLIMB-OUT, ENGINE WAS SECURED AND AIRCRAFT LANDED WITHOUT INCIDENT. TIME ON STACK UNKNOWN. BREAK APPEARED TO HAVE	 OCCURRED OVER A SHORT PERIOD OF TIME AS INDICATED BY EXHAUST GAS STAIN ON BROKEN PIECES. VISUAL INSPECTION OF EXHAUST 	PARTS MAY NOT BE ENOUGH AS THE CONSTANT HEAT CYCLING FATIGUES THE PARTS.			1	L	7	2 	3O				A8EA 					 
1995101300179	19951013	00179	NM 	1995	10	13	95ZZZX5602 	1	19950830	G	3213	491951	AIR VALVE 		45050001 	PIPER 	PA60 	PA60601P 	7106012	NM 										NLG	LOOSE 	D				O				OTHER 				O			OTHER 			CL	CLIMB 	1			NE	03	3635A	2300 				61P077480633				AFTER TAKEOFF, STRUT OLEO DID NOT FULLY EXTEND WHICH ALLOWED NOSE WHEEL TO TURN TO THE LEFT AND JAM FORWARD GEAR DOORS O	N RETRACTION. AFTER NOSE WHEEL ALIGNMENT CONFIRMED CORRECT, AND UNEVENTFUL LANDING WAS MADE. AIR VALVE AT BASE OF NOSE	 GEAR STRUT FOUND NOT FULLY TIGHT, ALLOWING THE STRUT NITROGEN TO LEAK OUT. STRUT RESERVICED AND CHECKED OK. FORWARD N	LG DOOR SHEER PIN REPLACED.			1	M	7	2 	3O			RT	A17WE 					 
1995101300180	19951013	00180	EA 	1995	10	13	95ZZZX5603 	2	19950906	G	7414	ES10682014	DISTRIBUTOR GEAR		LW385124115 	CESSNA	172 	172 	2072402	CE 	LYC 	O320 	O320H2AD 	41508	EA 					DUAL MAG RT	TEETH FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	6583D		157 		5030663	17272876	L29976T			FOUND RIGHT DISTRIBUTOR GEAR WITH 21 OF 53 TEETH MISSING. HELICAL SPRING MISSING FROM NR 1 TOWER (RIGHT SIDE) OF THE DI	STRIBUTOR BLOCK. EVIDENCE OF HEAVY ARCING INSIDE NR 1 TOWER BECAUSE OF MISSING SPRING. THIS DUAL MAGNETO IS AN ELECTRO	 SYSTEM, INC., OVERHAUL.				1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995101300181	19951013	00181	SO 	1995	10	13	95ZZZX5604 	1	19950901	G	5313		LONGERON 			PIPER 	PA12 	PA12 	7101202	SO 										FUSELAGE RT	CORRODED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	7682H	2262 				12571				INSPECTION FOUND A LOWER LONGERON CLUSTER ON THE RIGHT SIDE OF THE FUSELAGE, JUST BENEATH THE BATTERY COMPARTMENT, HAS B	EEN BADLY DAMAGED BY CORROSION. SUSPECT CAUSE WOULD BE FROM BATTERY ACID DRIPPING IN THIS AREA FOR SOME TIME.					1	H	7	1 	3O				A780 					 
1995101300182	19951013	00182	EA 	1995	10	13	95ZZZX5605 	2	19950925	G	8530	LW12039	VALVE 			BEECH 	23 	A2324 	1151226	CE 	LYC 	O360 	IO360A2B 	41514	EA 					NR 4 CYL EXH	DEFECTIVE 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	232W	825 				MA7	L211951A			DURING ANNUAL INSPECTION, FOUND LOW COMPRESSION IN NR 4 CYLINDER, INSPECTED INSIDE CYLINDER WITH BORESCOPE AND FOUND EXH	AUST VALVE WITH PIECES MISSING. VALVE SEAT WAS UNDAMAGED, NO OTHER DEFECTS IN CYLINDER WERE FOUND.					1	L	7	1 	3O	3	O		A1CE 	1E10				 
1995101300183	19951013	00183	GL 	1995	10	13	95ZZZX5606 	3	19950907	G	6111	L160BT	BLADE 			GROB 	109 	G109B 	1660205	EU 						HOFMAN	HOV62	HOV62R 	GL 	LEADING EDGE	DEFECTIVE 	C	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	791G		92 		7739A	6357		A1225		TRIANGULAR PIECE OF WOOD/COMPOSITE MATERIAL APPROXIMATELY .2187 INCH LONG BY .1250 INCH DEEP, SEPARATED FROM LEADING EDG	E OF PROPELLER BLADE AT THE BEVELED JOINT BETWEEN THE WOOD/COMPOSITE AND THE METAL LEADING EDGE. DEFECT LOCATED APPROXI	MATELY 15.8750 INCHES FROM THE CENTER OF THE PROPELLER HUB AND APPROXIMATELY 15.8750 INCHES FROM THE TIP OF THE PROPELLE	R BLADE. PROPELLER BLADE WAS INSTALLED ON PROPELLER HUB 12-21-93 BY LAS VEGAS PROPELLER SERVICE W/O NR 6659.			1	K	7	1 	3O			NC	G43EU 		5	N	P7EU	 
1995101300184	19951013	00184	CE 	1995	10	13	95ZZZX5607 	1	19950919	G	5511	053200198	SPAR 			CESSNA	172 	172M 	2072418	CE 										HORIZ STAB	CRACKED 	G	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	1261U	3801 				17266956				DURING AN ANNUAL INSPECTION, FOUND THE CENTER SECTION OF THE HORIZONTAL STABILIZER WAS DEFORMED AND CRACKED. IT IS POSS	IBLE THAT MISHANDLING DURING GROUND HANDLING IS THE CAUSE. CESSNA HAS A HEAVY DUTY CENTER SECTION SPAR AND SKIN REPLACE	MENT.				1	H	7	1 	3O			NT	3A12 					 
1995101300185	19951013	00185	CE 	1995	10	13	95ZZZX5608 	1	19950919	G	5512	053200132	SKIN 			CESSNA	172 	172M 	2072418	CE 										H STAB CENTER	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	1261U	3801 				17266956				DURING AN ANNUAL INSPECTION, FOUND THE CENTER SECTION OF THE HORIZONTAL STABILIZER WAS DEFORMED AND CRACKED. IT IS POSS	IBLE THAT MISHANDLING DURING GROUND HANDLING IS THE CAUSE. CESSNA HAS A HEAVY DUTY CENTER SECTION SPAR AND SKIN REPLACE	MENT.				1	H	7	1 	3O			NT	3A12 					 
1995101300186	19951013	00186	CE 	1995	10	13	95ZZZX5609 	1	19950911	G	2750	040010746	CONTROL CABLE 			CESSNA	150 	152 	2071835	CE 										FLAP	FRAYED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	47126	7653 				15283176				FLAP EXTENSION CABLE IN THE LEFT WING, THE CABLE HAS APPROXIMATELY 80 PERCENT OF THE STRANDS BROKEN. THE BROKEN WIRES W	ERE OVER THE HEADLINER AND WERE NOT VISIBLE UNTIL THE HEADLINER OPENED. DISCOVERED THE BROKEN CABLE WHILE REMOVING THE 	WINGS FROM THE AIRCRAFT.				1	H	7	1 	3O			NT	3A19 					 
1995101300187	19951013	00187	CE 	1995	10	13	95ZZZX5610 	1	19950919	G	3211	08227203	SUPPORT 			CESSNA	402 	402A 	207590M	CE 										LT MLG	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	710WT					402A0094				BOLTS SECURING SUPPORT TO AIRFRAME WERE DISCOVERED LOOSE AND PART WAS WORKING. UPON REMOVAL, PART WAS FOUND CRACKED. A	IRCRAFT MUST BE ON JACKS TO SEE LOOSENESS. AIRCRAFT TOTAL TIME IS IN EXCESS OF 25,000 HOURS. RECOMMEND INSPECTION AT A	NNUAL, AT LEAST.				1	L	7	2 	3O				A7CE 					 
1995101300188	19951013	00188	CE 	1995	10	13	95ZZZX5611 	1	19950919	G	2750		PULLEY 			CESSNA	402 	402CESSNA 	207590K	CE 										LT WING ROOT	SEIZED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	99AX	5665 				4020051				FLAP PULLEY WAS FOUND CHIPPED. UPON REMOVAL, FOUND BEARING HAD RUSTED AND WAS IMMOBILE. PULLEY HAD BEEN TURNING ON BOL	T WHICH WAS ALSO DAMAGED. BEARING CANNOT BE SEEN DURING NORMAL INSPECTION. PULLEY WAS TURNING. IT WAS LOCATED TOP OF 	A PAIR IN LEFT WING ROOT AREA.				1	L	7	2 	3O				A7CE 					 
1995101300189	19951013	00189	SO 	1995	10	13	95ZZZX5612 	1	19950719	G	3242	16423	DISC 	PARKERHANFIN		PIPER 	PA32 	PA32300 	7103212	SO 										MLG BRAKE	CORRODED 	G	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	15667	3445 				327340056				DURING AN ANNUAL INSPECTION, FOUND THE RIGHT BRAKE DISC WAS COMPLETELY SEPARATED FROM THE ATTACHMENT COLLAR DUE TO SEVER	E CORROSION.					1	L	7	1 	3O				A3SO 					 
1995101300190	19951013	00190	EU 	1995	10	13	95ZZZX5613 	1	19950525	G	6320	1171261001	BEARING 			BOLKMS	117 	BK117B2 	5626013	EU 										M/R GEARBOX	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07		3577 								GEARBOX WAS DISASSEMBLED FOR OVERHAUL, BEARING, PN 117-12610-01, INNER RACE FOUND CRACKED. NO OTHER DAMAGE FOUND.						1	G	7	2 	3U			NC	H13EU 					 
1995101300191	19951013	00191	EA 	1995	10	13	95ZZZX5614 	2	19950911	G	7261	3201104	JUNCTION BOX 			SKRSKY	S76 	S76B 	8143007	NE 	PWA 	PT6 	PT6B36 	52043	EA 					NR 2 CHIP DET	DEFECTIVE 	D				K				NONE 				N			FALSE WARNING 			NR	NOT REPORTED 	1			EA	17	22CP					760425	PCE36041			NR 2 ENGINE 'CHIP' LIGHT ILLUMINATED, WOULD NOT CLEAR BY CYCLING NR 2 CHIP CIRCUIT BREAKER. INSPECTED BOTH AGB AND RGB 	CHIP PLUGS FOR METAL PARTICLES - BOTH WERE CLEAN (NO METAL PARTICLES ATTACHED). REINSTALLED CHIP PLUGS, LIGHT STILL ILL	UMINATED. REMOVED AND REPLACED POWER MODULE JUNCTION BOX (ZAPPER BOX). SYSTEM FUNCTIONED NORMALLY.				1	G	7	2 	4U	4	U		H1NE 	E4EA				 
1995101300192	19951013	00192	NE 	1995	10	13	95ZZZX5615 	2	19950830	G	7230	3032145	IMPELLER VANE 			CESSNA	501 	501 	2076603	CE 	PWA 	JT15 	JT15D1 	52060	NE 					ENGINE	CRACKED 	B			OG5R	O				OTHER 				R			PARTIAL RPM/PWR LOSS 			TO	TAKEOFF 	1			GL	21	83ND	4733 	1285 			5010178	77202			DURING TAKEOFF ROLL, ENGINE MADE WHAT PILOT DESCRIBED AS COMPRESSOR STALLS. ENGINE DISASSEMBLED BY P & W. INVESTIGATIO	N FOUND A LARGE PORTION OF ONE VANE (APPROXIMATELY 1.75 SQUARE INCH) WAS FRACTURED FROM THE INDUCER AREA OF THE IMPELLER	. NO OTHER EVIDENCE OF FOD DAMAGE FOUND ON OTHER BLADES. ENGINE SUSTAINED HEAVY DAMAGE TO GAS GENERATOR, HIGH TURBINE,	 SEGMENTS, LOW TURBINE, ETC. (ENGINE TO BE OVERHAULED).			1	L	7	2 	4F	4	F		A27CE 	E1NE				 
1995101300193	19951013	00193	WP 	1995	10	13	95ZZZX5616 	2	19950901	G	7210	8968051	GEAR 			MTSBSI	MU2 	MU2B20 	5780407	SW 	GARRTT	TPE331	TPE3311 	01514	WP 					FWD GEARBOX	FAILED 	G				O				OTHER 				O			OTHER 			CL	CLIMB 	1			SW	15	500PS	5747 				224	P92297			ENGINE FAILED AFTER TAKEOFF. TEAR DOWN REVEALED SPUR GEAR IN FORWARD GEARBOX HAD FAILED CAUSING SECONDARY DAMAGE TO OTH	ER GEARS. GEAR SENT TO ALLIED SIGNAL FOR EVALUATION.					1	H	7	2 	3T	3	T		A2PC 	E3WE				 
1995101300194	19951013	00194	CE 	1995	10	13	95ZZZX5617 	1	19950811	G	7160	BA4101	GASKET 		BA4106 	CESSNA	150 	152 	2071835	CE 										BRACKET	FAULTY 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	23										DURING COMPLIANCE WITH AD 95-03-02, IT WAS NOTED THAT FACTORY FURNISHED HOLES IN THE GASKET CAUSE MISALIGNMENT OF SEALIN	G/GLUING SURFACE AND LACK OF CONTACT AREA WHICH COULD LEAD TO GASKET INGESTION. (TOPIC OF AD 95-0302).					1	H	7	1 	3O			NT	3A19 					 
1995101300195	19951013	00195	SO 	1995	10	13	95ZZZX5618 	2	19950831	G	8530	6291171	ROTOR CAP 								CONT 	O520 	IO520* 	17032	SO 					EXHAUST VALVE	DEFECTIVE 	B			YCTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11										EXHAUST VALVE ROTOR CAP WILL NOT ROTATE. THIS VALVE ROTOR WAS OUT OF CYLINDER VALVE ASSEMBLY.											3	O			E5CE				 
1995101300196	19951013	00196		1995	10	13	95ZZZX5619 	4	19950920	G	3420	A1S24035	SWITCH 	AVIONINST 		BEECH 	33 	F33A 	1151425	CE 										COCKPIT	FAILED 	B			FCPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	224AB	3 			166	CE1680				REMOTE SWITCH UNIT USED FOR GPS/NAV TRANSFER INTERNAL RELAY BANKS, FAILED. INTERNAL K2, K3, AND K4 RELAY BANKS FAILED I	N THE CLOSED POSITION AND K5 BANK FAILED IN NEUTRAL POSITION. THIS FAILURE CAUSES THE NAV 1 HSI INDICATOR TO DISPLAY ER	RONEOUS INFORMATION.				1	L	7	1 	3O				3A15 					 
1995101300197	19951013	00197	SO 	1995	10	13	95ZZZX5620 	1	19950819	G	7920	MILH6000	HOSE 	AEROQUIP 		PIPER 	PA28 	PA28180 	7102808	SO 										OIL COOLER	RUPTURED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	7046W					28802				LOWER OIL COOLER HOSE RUPTURED APPROXIMATELY 12 INCHES FROM OIL COOLER AT LOWEST PART. SUBMITTER SUGGESTS ENGINE WAS US	ING SYNTHETIC OIL WHICH MAY HAVE HAD AN ADVERSE EFFECT ON HOSE. HOSE WAS SOFT. HOSE WAS MADE 1-84.					1	L	7	1 	3O				2A13 					 
1995101300198	19951013	00198	SO 	1995	10	13	95ZZZX5621 	1	19950818	G	2710		BELLCRANK 			PIPER 	PA44 	PA44180 	7104402	SO 										AILERON CONTROL	NUT CRACKED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	39608					447995015				THE RIGHT AILERON CONTROL BOLT AT THE BELLCRANK HAD A MISSING NUT. THE NUT WAS LOCATED IN THE WING AND WAS CRACKED IN T	HREE PLACES. ONE CRACK WAS ACTUALLY SEPARATED AND ALLOWED THE NUT TO FALL OFF. ALL HARDWARE WAS REPLACED WITH CORRECT	 HARDWARE.				1	L	7	2 	3O				A19S0 					 
1995101300199	19951013	00199	SO 	1995	10	13	95ZZZX5622 	1	19950914	G	2821	3571503	GASCOLATOR 			PIPER 	PA28 	PA28161 	7102803	SO 										BOWL SEAL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	05	83207					288116123				FUEL LEAKING FROM GASCOLATOR ASSY. FOUND FUEL LEAKING FROM BOWL SEAL AREA. THE COVER OF THE GASCOLATOR HAS BECOME ELON	GATED FROM THE CLAMP THAT SECURES THE BOWL ASSY TO THE COVER. REPLACEMENT OF COVER ASSY WITH NEW REPLACEMENT COVER, PN 	874-77-002 (PIPER).				1	L	7	1 	3O				2A13 					 
1995101300200	19951013	00200	NM 	1995	10	13	95ZZZX5623 	1	19950801	G	2822	AF6415	VALVE BODY 		AC9051 	UNIVAR	415 	415C 	0420302	NM 										PUMP	CRACKED 	D				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			SO	09	93781	2080 				1104				PUMP FAILED TO PUMP FUEL FROM WING TANK OF FUSELAGE TANK DUE TO A CRACK IN THE VALVE BODY UPPER TO LOWER CHAMBER CAUSING	 LOSS OF PRIME. THE CRACK WAS CAUSED BY SEVERE INTERGRANULAR CORROSION. THE ENGINE QUIT DUE TO FUEL STARVATION. PILOT	 WAS FORCED TO LAND THE AIRCRAFT IN A ROADWAY. SUBMITTER STATED THIS PUMP HAD NOT BEEN INSPECTED PROPERLY IN SEVERAL YE	ARS. PROPER MAINTENANCE PROCEDURES IAW MANUFACTURER'S SERVICE INSTRUCTIONS WOULD HAVE FOUND AND CORRECTED THIS PROBLEM.			1	L	7	1 	3O				A718 					 
1995101300201	19951013	00201	SW 	1995	10	13	95ZZZX5624 	1	19950913	G	7810	30501507HS	EXHAuST SYSTEM 	ROCKETRESRCH		MOONEY	M20 	M20K 	5870220	SW 										ENGINE	CRACKED 	B			NT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	252YD	585 				251075				DURING PRE-BUY AND ROCKET MSB 95-305-01 INSPECTION: FOUND TAIL PIPES, HEADERS, TRANSITION PIPES CRACKED AT WELDS AND WH	ERE BAFFLING RUBS. EXHAUST SYSTEM IS HARD MOUNTED, PLACING STRAIN ON ALL COMPONENTS, SYSTEM ASSEMBLY INSTALLATION REQUI	RES FORCE TO PUT IN PLACE. ENGINE TO LORD MOUNT BOLTS - UNTHREADED BOLT SHANK TOO LONG; THUS, ALLOWING ENGINE TO FURTHE	R VIBRATE. BAFFLING CRACKED AND BROKEN. ENGINE EXHAUST STAINS THROUGHOUT COMPARTMENT. STC SA5891NM.			1	L	7	1 	3O				2A3 					 
1995101300202	19951013	00202	SW 	1995	10	13	95ZZZX5625 	1	19950913	G	7810	30501507HS	EXHAUST SYSTEM 	ROCKETRESRCH		MOONEY	M20 	M20K 	5870220	SW 										ENGINE	CRACKED 	B			NT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	2FOR	241 				250037				DURING ANNUAL AND ROCKET MSB 95-305-01 INSPECTION: FOUND TAIL PIPES, HEADERS, TRANSITION PIPES CRACKED AT WELDS AND WHE	RE BAFFLING RUBS. EXHAUST SYSTEM IS HARD MOUNTED, PLACING STRAIN ON ALL COMPONENTS. SYSTEM ASSEMBLY INSTALLATION REQUI	RES FORCE TO PUT IN PLACE. ENGINE TO LORD MOUNT BOLTS - UNTHREADED BOLT SHANK TOO LONG; THUS, ALLOWING ENGINE TO FURTHE	R VIBRATE. BAFFLING CRACKED AND BROKEN. ENGINE EXHAUST STAINS THROUGHOUT COMPARTMENT. STC SA5891NM (SEA).			1	L	7	1 	3O				2A3 					 
1995101300203	19951013	00203	SO 	1995	10	13	95ZZZX5626 	1	19950801	G	3211	9564306	BRACKET ASSY 			PIPER 	PA34 	PA34200 	7103405	SO 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	15412	6680 				347350060				REFER TO DOCKET NR (93-C3-61-AD). THIS PART IS THE MLG SWIVEL PIN ASSY. PART WAS DISASSEMBLED TO SEE IF IT COULD BE TI	GHTENED UP. AFTER DISASSEMBLY AND CLEANING, CORROSION WAS NOTICED ON PIN SHANK AND RADIUS. SMALL CRACKS WERE FOUND WIT	H 10X MAGNIFYING GLASS. DYE-CHECK BOLT RT AND LT TO VERIFY THE CRACKS. ONE CRACK, .75 INCH AND THE OTHER CRACK, .50 IN	CH THE WAY AROUND (CRACKED). BOTH ASSYS WERE REPLACED. RECOMMEND TO DISASSEMBLE AND INSPECT EVERY 1,500 TO 2,000 HOURS	.		1	L	7	2 	3O				A7SO 					 
1995101300204	19951013	00204	SO 	1995	10	13	95ZZZX5627 	1	19950801	G	3211	9564307	BRACKET ASSY 			PIPER 	PA34 	PA34200 	7103405	SO 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	15412	6680 				347350060				REFER TO DOCKET NR (93-C3-61-AD). THIS PART IS THE MLG SWIVEL PIN ASSY. PART WAS DISASSEMBLED TO SEE IF IT COULD BE TI	GHTENED UP. AFTER DISASSEMBLY AND CLEANING, CORROSION WAS NOTICED ON PIN SHANK AND RADIUS. SMALL CRACKS WERE FOUND WIT	H 10X MAGNIFYING GLASS. DYE-CHECK BOLT RT AND LT TO VERIFY THE CRACKS. ONE CRACK, .75 INCH AND THE OTHER CRACK, .50 IN	CH THE WAY AROUND (CRACKED). BOTH ASSYS WERE REPLACED. RECOMMEND TO DISASSEMBLE AND INSPECT EVERY 1,500 TO 2,000 HOURS	.		1	L	7	2 	3O				A7SO 					 
1995101300205	19951013	00205	CE 	1995	10	13	95ZZZX5628 	1	19950825	G	3230	504501019	TORQUE TUBE 			CESSNA	402 	402B 	207590P	CE 										LT MLG	CRACKED 	D				A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			NM	09	5198J	9716 				402B0885				AFTER TAKEOFF, TOWER TOLD THE PILOT THE RT MLG DID NOT RETRACT. AFTER LANDING, MAINTENANCE FOUND RT MLG TORQUE TUBE CRA	CKED 6 INCHES IN A SPIRALING DIRECTION. THE LT MLG WAS ALSO IINSPECTED AND A ONE-INCH CRACK WAS FOUND ON IT. THESE CRA	CKS START IN THE AREA OF THE FORK BOLT. A 200-HOUR MLG INSPECTION HAD BEEN C/W 120 HOURS EARLIER.				1	L	7	2 	3O				A7CE 					 
1995101300206	19951013	00206	CE 	1995	10	13	95ZZZX5629 	1	19950825	G	3230	50450102	TORQUE TUBE 			CESSNA	402 	402B 	207590P	CE 										RT MLG	CRACKED 	D				A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			NM	09	5198J	9716 				402B0885				AFTER TAKEOFF, TOWER TOLD THE PILOT THE RT MLG DID NOT RETRACT. AFTER LANDING, MAINTENANCE FOUND RT MLG TORQUE TUBE CRA	CKED 6 INCHES IN A SPIRALING DIRECTION. THE LT MLG WAS ALSO IINSPECTED AND A ONE-INCH CRACK WAS FOUND ON IT. THESE CRA	CKS START IN THE AREA OF THE FORK BOLT. A 200-HOUR MLG INSPECTION HAD BEEN C/W 120 HOURS EARLIER.				1	L	7	2 	3O				A7CE 					 
1995101300207	19951013	00207	EA 	1995	10	13	95ZZZX5630 	2	19950910	G	8530	61247	ROCKER COVER 			BEECH 	77 	77 	1153007	CE 	LYC 	O235 	O235L2C 	41505	EA 					ENGINE CYLS	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	6754W	1286 				WA99	L2082115			WHILE PERFORMING AN ANNUAL INSPECTION THE ROCKER COVERS WERE FOUND EXTREMELY RUSTY ON THE INSIDE. OWNER ADVISED HE HAD	 LEFT THE ENGINE HEATER PLUGGED IN ALL WINTER. SUBMITTER SUSPECTS CONDENSATION FORMED ON COVERS DUE TO COOL TEMPS OUTSI	DE ENGINE AND THAT COUPLED WITH LACK OF WINTER FLYING KEPT OIL FILM TO A MINIMUM. SUGGEST ENGINE HEATERS ONLY BE USED P	RIOR TO A FLIGHT TO WARM ENGINE AND NEVER LEAVE THEM PLUGGED IN FOR EXTENDED TIME. TWENTY-THREE HOURS SINCE LAST 12-MON	TH INSPECTION.		1	L	7	1 	3O	3	O		A30CE 	E223				 
1995101300208	19951013	00208	SO 	1995	10	13	95ZZZX5631 	1	19950907	G	2410	LW18129	BELT 	PRESTOLITE 	ALU8403 	PIPER 	PA31 	PA31350 	7103110	SO 										ALTERNATOR	FAILED 	E	L			K				NONE 				W			INADEQUATE Q C 			NR	NOT REPORTED 	1			EA	07	107GA	2 			1M000102	31705446				RIGHT ENGINE ALTERNATOR AND A/C BELTS REPLACED DUE TO AGE AND CRACKING AT 25.5 HOURS P.T.T. AIRCRAFT FLEW THROUGH HEAVY	 RAIN AND ALTERNATOR BELT FAILED BY LOSS OF DRIVE COGS (TEETH). NEW BELT INSTALLED, AIRCRAFT FLEW 1.9 HRS (1ST TRIP), B	ELT FAILED AS ABOVE. ANOTHER NEW LW18129 BELT WAS INSTALLED, AIRCRAFT RETURNED HOME, 1.8 HRS BELT WAS FAILING (COGS MIS	SING). THE LAST TWO FLIGHTS HAD NO RAIN OR MOISTURE.			1	L	7	2 	3O				A20SO 					 
1995101300209	19951013	00209	CE 	1995	10	13	95ZZZX5632 	1	19950723	G	7110	0752609201	FLAP 			CESSNA	182 	182H 	2072718	CE 										LOWER RT COWL	DEPARTED 	D		A		O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			SO	13	8409S	1425 				18256509				RIGHT COWL FLAP DEPARTED AIRCRAFT IN-FLIGHT. SUSPECT CORROSION BETWEEN HINGE AND STEEL PIN. SUBMITTER RECOMMENDS IF AN	Y EXCESSIVE PLAY IS DETECTED IN HINGE AREA, REMOVE AND REPLACE HINGE, ESPECIALLY IF HINGE STILL LOOKS SERVICEABLE. THIS	 CORROSION IS HIDDEN BY STEEL PIN.				1	H	7	1 	3O			NT	3A13 					 
1995101300210	19951013	00210	SO 	1995	10	13	95ZZZX5633 	1	19950906	G	2842	686049	FUEL SENDER 			PIPER 	PA46 	PA46310P 	7104605	SO 										LT OTBD	ERRATIC 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	26033	1984 				468508108				REMOVED LEFT OUTBOARD FUEL SENDER DUE TO ERRATIC QUANTITY INDICATION. UPON REMOVAL, FOUND FOAM ON INNER SIDE OF PANEL D	ELAMINATING AND BREAKING LOOSE.					1	L	7	1 	3O				A25SO 					 
1995101300211	19951013	00211	CE 	1995	10	13	95ZZZX5634 	1	19950830	G	7921	641484	COOLER 			CESSNA	404 	404CESSNA 	2075901	CE 										ENGINE OIL	CRACKED 	B			APCR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	01	48SA	379 				440417				OIL COOLER CRACKED UNDER NORMAL CONDITIONS, LEAKING OIL. SUBMITTER SUGGESTS RE-DESIGN COOLER.						1	L	7	2 	3O				A25CE 					 
1995101300212	19951013	00212	CE 	1995	10	13	95ZZZX5635 	1	19950918	G	2410	5395473119	BELT 	FORD 	C6115050102 	CESSNA	210 	T210N 	2073456	CE 										ALTERNATOR	FAILED 	D				O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			WP	17	7067N	79 				21064005				DURING FLIGHT, THE LOW VOLTAGE ILLUMINATED. DURING INSPECTION ON THE GROUND, A BROKEN ALTERNATOR BELT WAS DISCOVERED. T	HE BELT APPEARED TO HAVE UNRAVELED FROM THE TOP DOWN. THE ALTERNATOR HAD BEEN REPLACED 14 HOURS EARLIER, THE PULLEYS WE	RE CHECKED FOR PROPER ALIGNMENT. SUBMITTER SUGGESTS FROM ALL INDICATIONS THE BELT WAS DEFECTIVE.				1	H	7	1 	3O				3A21 					 
1995101300213	19951013	00213	SO 	1995	10	13	95ZZZX5636 	2	19950908	G	8530	639702	CYLINDER 			CESSNA	150 	150L 	2071826	CE 	CONT 	O200 	O200A 	17020	SO 					NR 2 CYLINDER	ROCKER BROKE 	D				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			SW	11	19111				6116168Q3	15074176	21346671A			A LOSS OF 500 RPM IN-FLIGHT PROMPTED A NORMAL LANDING AT AIRPORT. FURTHER INVESTIGATION REVEALED NR 2 CYLINDER INOPERAT	IVE. CLOSER DISASSEMBLY REVEALED THE COMPLETE ROCKER ARM ASSY WAS BROKEN LOOSE. ROCKER ARM BOSSES WERE ALL BROKEN OFF 	HALF WAY UP THEIR HEIGHT. AD 94-04-05 C/W 235.2 HRS PRIOR AT 6-1-94.				1	H	7	1 	3O	3	O		3A19 	E252				 
1995101300214	19951013	00214	SO 	1995	10	13	95ZZZX5637 	1	19950913	G	2700		TORQUE TUBE 			PIPER 	PA18 	PA18150 	7101828	SO 										CONTROL STICK	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	89994					188510				INSPECTION FOUND STICK TORQUE TUBE FORWARD PIVOT CRACKED, ON LEFT SIDE.						1	H	7	1 	3O				1A2 					 
1995101300215	19951013	00215	CE 	1995	10	13	95ZZZX5638 	1	19950912	G	5712	082212571	RIB 			CESSNA	310 	310R 	2074245	CE 										WHEELWELL	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	310MB					310R0943				FOUND WING RIB CRACKED AT GEAR ACTUATOR OPENING BEHIND SIDE BRACE BRACKET ATTACH. TOP BOLTS OF SIDE BRACE BRACKET WERE 	SLOPPY, LOOSE, AND HAD BEEN FOR A LONG TIME. OTHER HARDWARE SHOWS SIGNS OF WORKING LOOSE AND WERE RETORQUED. BOTH WING	S SHOW SAME PROBLEM. SERVICE KIT ADDRESSES CRACK PROBLEM, BUT NOT LOOSE HARDWARE.				1	L	7	2 	3O				3A10 					 
1995101300216	19951013	00216	SO 	1995	10	13	95ZZZX5639 	2	19950821	G	8520	641931981	THROUGH-BOLT 								CONT 	O470 	IO470N 	17026	SO 					ENGINE	BROKE 	B	S		JZYR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09										NEW THROUGH-BOLT BROKE AFTER TORQUED TO 67 FEET/POUND. BROKE AT O-RING GROOVE IN CENTER OF BOLT. SUBMITTER SUSPECTS PO	SSIBLE HYDROGEN EMBRITTLEMENT FROM PLATING.										3	O			3E1				 
1995021000050	19950210	00050	EA 	1995	2	10	95ZZZX564 	2	19950117	G	8550	21932	PICK-UP TUBE 								LYC 	O320 	IO320E2B 	41508	EA 					INVERT OIL SYS	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	88065						L519655A			THE OIL PICK-UP TUBE, PN 2-1932, WHICH IS PART OF THE INVERTED OIL SYSTEM OF STC 3E7CE, IS CRACKED THROUGH THREE-FOURTHS	 OF ITS CIRCUMFERENCE ABOUT 1.50 INCHES FROM THE END TO WHICH THE SWINGING PICK-UP IS ATTACHED. CRACK WAS FOUND WHEN TH	E STC REQUIRED INSPECTION WAS PERFORMED (EVERY 400 HOURS). SUBMITTER HAD CHECKED THIS STC AT 525 HOURS TT AND 925 HOURS	 TT AND NO CRACKS WERE FOUND. NO OTHER PROBLEMS EXISTED ON THIS STC AT THAT TIME (1250 HOURS TT).								3	O			1E12				 
1995101300218	19951013	00218	CE 	1995	10	13	95ZZZX5641 	1	19950822	G	3246	16119A	WHEEL HALF 	PARKERHANFIN	4040A 	CESSNA	340 	340A 	2076405	CE 										RT MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	6827Z					340A1222				WHEEL HALF HAS 6 INCH CRACK IN BEAD AREA. NOTED UPON LANDING, DIFFICULT TO TAXI. SUBMITTER SUSPECTS HARD LANDING ALONG	 WITH AGE. SUBMITTER SUGGESTS NDT INSPECTION AT EACH TIRE CHANGE.					1	L	7	2 	3O				3A25 					 
1995101300219	19951013	00219	SO 	1995	10	13	95ZZZX5642 	2	19950616	G	8530	633821	TUBE 			CESSNA	319 	319 	2074402	SO 	CONT 	O470 	O470* 	17026	SO 					INTAKE	DISLOCATED 	D				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SW	99	36880					608	457115J			DURING WILDLIFE SURVEY, ENGINE BECAME ROUGH AND WAS SHUT DOWN. AIRCRAFT LANDED ON RIVER LEVEE. CARBURETOR TO MANIFOLD 	TUBE HAD BECOME DISLODGED. REPLACED TUBE, ENGINE FUNCTIONED NORMALLY. THIS AIRCRAFT FUEL SYSTEM IS GRAVITY FLOW AND IS	 PLACARDED TO TURN ON ELECTRIC FUEL PUMP FOR MANEUVERING. SUSPECT BACKFIRE DUE TO DISRUPTED FUEL FLOW CAUSED TUBE TO BE	COME DISLODGED.			1	H	7	1 	3O	3	O	NC		E273				 
1995101300220	19951013	00220	CE 	1995	10	13	95ZZZX5643 	1	19950918	G	3230	98820152	ACTUATOR 			CESSNA	172 	172RG 	2072438	CE 										MLG	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	6529V	6661 			7632	172RG0755				GEAR WAS REPORTED TO HAVE NOT RETRACTED ALL THE WAY. UPON INSPECTION, THE LEFT GEAR WOULD NOT FULLY RETRACT INTO THE WE	LL. INSPECTING THE GEAR ACTUATOR, A CRACK WAS DISCOVERED IN THE HOUSING. AFTER REMOVAL OF THE ACTUATOR, DISCOVERED THE	 SECTOR GEAR, PN 4882002-2, HAD BEEN DRIVEN PAST THE END OF THE PISTON GEAR, PN 9882004-1.				1	H	7	1 	3O				3A17 					 
1995101300222	19951013	00222	SO 	1995	10	13	95ZZZX5645 	1	19950918	G	3233	401270	BOLT 		3579702 	PIPER 	PA32 	PA32RT300 	7103215	SO 										NLG ACTUATOR	FRACTURED 	B		A	CSVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	3046H	2052 				32R7985046				UPON COMPLIANCE WITH PIPER SB 747, NLG ACTUATOR ATTACHMENT BOLT (REAR) WAS FOUND SEVERELY WORN, BENT, AND FRACTURED WITH	 FORWARD CLEVIS BOLT, PN 400-871 (AN23-19A) FOUND WORN AND BENT ALSO. SUBMITTER SUGGESTS SB 747 SHOULD BE MANDATORY.					1	L	7	1 	3O				A3SO 					 
1995101300225	19951013	00225	EA 	1995	10	13	95ZZZX5648 	2	19950729	G	8530		RING 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					NR 1-3 CYLS	BROKEN 	D				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			EA	25	8351W	1600 				288116176	L949439A			PILOT MADE EMERGENCY LANDING DUE TO POWER LOST. FOUND NR 1, NR 3 BOTTOM SPARK PLUGS OIL FOULED. REMOVED THE CYLINDERS 	AND FOUND BROKEN COMPRESSION RINGS. TSO NR 1 CYLINDER, 1600 HRS. TSO NR 3 CYLINDER, 777 HRS.					1	L	7	1 	3O	3	O		2A13 	E274				 
1995101300226	19951013	00226	EA 	1995	10	13	95ZZZX5649 	2	19950907	G	8530	72050	KEY 			CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					NR 3 CYL EXH	BROKEN 	B			BXSR	O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			EA	09	6814H		400 			17265594	L454527A			PILOT REPORTED THE ENGINE RUNS ROUGH AT LOW POWER SETTING ONLY. TROUBLESHOT AND FOUND ONE OF THE NR 3 CYLINDER EXHAUST 	VALVE KEYS BROKEN IN TWO AND THE VALVE STEM WAS DESTROYED IN THE KEY AREA.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995101300227	19951013	00227	CE 	1995	10	13	95ZZZX5650 	1	19950912	G	2731	12346281	TRIM TAB 			CESSNA	210 	210L 	2073448	CE 										ELEVATOR	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	2FOR	2911 				61120				ELEVATOR TRIM TAB CORRODED AT PUSH/PULL ROD ATTACHMENT. SAME CONDITION AS MENTIONED ON AC 43-16, ALERT NR 200, PAGE 6.						1	H	7	1 	3O				3A21 					 
1995101300228	19951013	00228	NE 	1995	10	13	95ZZZX5651 	2	19950922	G	8530	366249	CYLINDER 								PWA 	R1340 	R1340AN1 	52016	NE 					ROCKER	HOUSING FAILED 	H	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15										SUBMITTER REPORTS THAT ONE OPERATOR OF A PRATT & WHITNEY R-1340 ENGINE HAS HAD AT LEAST 4 CYLINDERS BREAK AT SAME LOCATI	ON. HE REPORTS THE EXHAUST ROCKER SHAFT HOUSING AREA OF THE CYLINDERS HAVE EITHER CRACKED OR BROKE IN TWO. TWO RADIAL 	ENGINE OVERHAUL FACILITIES STATE THAT THEY REJECT AT LEAST 3 PERCENT OF THE CYLINDERS FOR ROCKER FAILURE. THEY FEEL MAI	NTENANCE PERSONS IN THE FIELD ARE OVERTIGHTENING THE ROCKER SHAFT NUTS WHEN A SLIGHT SEEPAGE IS DETECTED. THEY ADVISE R	ECOMMENDED TORQUE NEVER SHOULD BE EXCEEDED. ONCE A SEEPAGE IS DETECTED, REPLACMENT OF OIL SEALS IS REQUIRED TO STOP THE	 LEAK.						3	R			5E2				 
1995101300229	19951013	00229	EA 	1995	10	13	95ZZZX5652 	1	19950912	G	3320	G345230	LIGHT ASSY 		G345230 	CNDAIR	CL600 	CL6002B19 		EA 										LAVATORY	WIRES BURNED 	H		A		O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			EA	11	5100X					7008				TWELVE TO FIFTEEN MINUTES FROM HOME BASE, THE FLIGHT ATTENDANT SMELLED AN ELECTRICAL BURNING ODOR FROM THE REAR LAV AREA	 OF THE AIRCRAFT. UPON INVESTIGATING, SHE FOUND NO VISIBLE INDICATIONS. ON LANDING, MAINTENANCE WAS INFORMED AND THEN 	FOUND THE 4 FLUORESCENT TUBE LIGHT ASSYS IN THE LAV ABOVE THE SINK SMOKING GIVING OFF BLUE SPARKS AND A SLIGHT ORANGE GL	OW. POWER WAS IMMEDIATELY REMOVED FROM THE LAV AREA AND THE FAULTY ASSY REMOVED FROM AIRCRAFT.			2	L	7	2 	4F			RT	A21EA 					 
1995101300230	19951013	00230	NE 	1995	10	13	95ZZZX5653 	2	19950915	G	7261	785543	PRESSURE TUBE 								PWA 	JT9 	JT9* 	52054	NE 					NR 4 BEARING	MISREPAIRED 	H		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	27										THREE DIAMETERS OF TUBE ASSY ARE PLASMA COATED. ASSY IN QUESTION WAS RETURNED AS UNREPAIRABLE DUE TO EXCESSIVE PLASMA C	OATING THICKNESS. REPAIR CAUSE FOR THE REMOVAL OF EXISTING PLASMA AND RE-APPLICATION. ORIGINAL OR REPAIRED AREAS WERE 	SHOWING AT LEAST TWICE THE ALLOWABLE THICKNESS. THIS CONDITION COULD CAUSE THE COATING TO BREAK AWAY FROM PARENT METAL 	AND CAUSE A PROBLEM.								4	F			E20EA				 
1995101300231	19951013	00231	NE 	1995	10	13	95ZZZX5654 	2	19950922	G	7250	786822A	TURBINE DISK 								PWA 	JT8 	JT8D17R 	52049	NE 					2ND STAGE	FIR TREE FAILURE	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03		18729			N92357		700823			DURING DEBLADING OF THE SECOND STAGE TURBINE DISK, 3 FIR TREES FELL OFF WHEN THE BLADES WERE REMOVED. OVERHAUL MANUAL P	ROCEDURES WERE FOLLOWED AND WERE NOT A CONTRIBUTING CAUSE TO THE DAMAGE. THE CRACKS ON THE FIR TREES APPEAR TO BE OLD D	UE TO SOOT DEPOSITS. THE OEM (PRATT & WHITNEY) NOTIFIED ON 9-21-95. GAS TURBINE COMPANY CONTROL ORDER IS 11730E.									4	F			E2EA				 
1995101300301	19951013	00301		1995	10	13	95ZZZX5655 	4	19950928	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					60337					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300302	19951013	00302		1995	10	13	95ZZZX5656 	4	19950928	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14901					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300303	19951013	00303		1995	10	13	95ZZZX5657 	4	19950928	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C16999					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300304	19951013	00304		1995	10	13	95ZZZX5658 	4	19950928	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14877					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300305	19951013	00305		1995	10	13	95ZZZX5659 	4	19950928	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C11681					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995021000052	19950210	00052	CE 	1995	2	10	95ZZZX566 	1	19950113	G	3240	C1630300103	BRAKE ASSY 			CESSNA	150 	150F 	2071814	CE 										ANCHOR BOLT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	6242R	3544 				15061542				DURING AN INSPECTION, BOTH WHEEL BRAKE ASSEMBLIES WERE FOUND CRACKED AT THE ANCHOR BOLT BOSSES. THE CAUSE OF THE CRACK 	IS THE ANCHOR BOLT (PN 69-4) GETS RUSTY/DIRTY AND WOULD NOT SLIDE FREELY IN THE TORQUE PLATE (PN 75-37). SUBMITTER SUGG	ESTS DURING INSPECTION, BE SURE THE ANCHOR BOLTS AND HOLES IN THE TORQUE PLATE ARE CLEANED OF ALL RUST AND DIRT.				1	H	7	1 	3O				3A19 					 
1995101300306	19951013	00306		1995	10	13	95ZZZX5660 	4	19950928	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14390					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300307	19951013	00307		1995	10	13	95ZZZX5661 	4	19950928	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					64475					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300308	19951013	00308		1995	10	13	95ZZZX5662 	4	19950928	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					20918					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300309	19951013	00309		1995	10	13	95ZZZX5663 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					28694					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300310	19951013	00310		1995	10	13	95ZZZX5664 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					77819					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300311	19951013	00311		1995	10	13	95ZZZX5665 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					75318					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300312	19951013	00312		1995	10	13	95ZZZX5666 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C18596					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300313	19951013	00313		1995	10	13	95ZZZX5667 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					52545					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300314	19951013	00314		1995	10	13	95ZZZX5668 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					71802					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300315	19951013	00315		1995	10	13	95ZZZX5669 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					72674					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995021000053	19950210	00053	CE 	1995	2	10	95ZZZX567 	1	19950108	G	5102		BURNER 			NATBAL	752 	858 	6113320	CE 										PILOT LIGHT	ORFICE PLUGGED 	G				A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			GL	15	7271K	398 				116				OPERATOR REPORTED LOSS OF PILOT LIGHT DURING STABLE FLIGHT, DURING ATTEMPTED LANDING -- AND EMERGENCY DEFLATION DUE TO A	PPROACHING POWER LINES. WIND BLEW BALLOON AGAINST POWER LINES. PILOT SUSPECTED THE LOSS OF PILOT LIGHT WAS DUE TO CARB	ON BUILD-UP ON ORIFICES ON PILOT LIGHT ASSEMBLY. WHEN HOLES WERE CLEANED WITH A .080 INCH BROACH, PILOT LIGHT OPERATED 	'BETTER THAN NEW'. THERE APPEARS TO BE NO ANNUAL REQUIREMENT TO CLEAN HOLES. OPERATOR RECOMMENDS MAKING THIS PROCEDURE	 PART OF THE ANNUAL INSPECTION.		1	B	0	0 					A33CE 					 
1995101300316	19951013	00316		1995	10	13	95ZZZX5670 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					61181					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300317	19951013	00317		1995	10	13	95ZZZX5671 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					62903					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300318	19951013	00318		1995	10	13	95ZZZX5672 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18409					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300319	19951013	00319		1995	10	13	95ZZZX5673 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18829					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300320	19951013	00320		1995	10	13	95ZZZX5674 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					428694					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300321	19951013	00321		1995	10	13	95ZZZX5675 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					78909					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300322	19951013	00322		1995	10	13	95ZZZX5676 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					96337					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300323	19951013	00323		1995	10	13	95ZZZX5677 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18798					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300324	19951013	00324		1995	10	13	95ZZZX5678 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18830					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300325	19951013	00325		1995	10	13	95ZZZX5679 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					99298					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995021000054	19950210	00054	CE 	1995	2	10	95ZZZX568 	1	19950113	G	7120	123901	MOUNT 	LORD 		CESSNA	310 	310J 	2074226	CE 										LT ENG FWD	DAMAGED 	B			FGQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	3192L	355 				310J0192				NEW OWNER BROUGHT AIRCRAFT IN FOR PITOT HEAT PROBLEM. NOTICED LT ENGINE WAS SAGGING RELATIVE TO THE COWLING. FURTHER I	NSPECTION REVEALED THE FORWARD MOUNTS TO HAVE UNSEATED AND DROPPED IN THE SUPPORT STRUCTURE. THE RT ENGINE WAS CHECKED 	AND FOUND TO HAVE THE SAME CONDITION. THIS AIRCRAFT HAS ONLY 355 HRS SINCE NEW MOUNTS AND REMANUFACTURED ENGINES INSTAL	LED. IT ALSO HAD ONLY ONE FLIGHT SINCE A 'FRESH ANNUAL' WAS SIGNED OFF ONLY FOUR DAYS EARLIER.			1	L	7	2 	3O				3A10 					 
1995101300326	19951013	00326		1995	10	13	95ZZZX5680 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					23044					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300327	19951013	00327		1995	10	13	95ZZZX5681 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					11221					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300328	19951013	00328		1995	10	13	95ZZZX5682 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					11814					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300329	19951013	00329		1995	10	13	95ZZZX5683 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					17063					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300330	19951013	00330		1995	10	13	95ZZZX5684 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					28425					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300331	19951013	00331		1995	10	13	95ZZZX5685 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18799					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300332	19951013	00332		1995	10	13	95ZZZX5686 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					99992					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300333	19951013	00333		1995	10	13	95ZZZX5687 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					10674					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300334	19951013	00334		1995	10	13	95ZZZX5688 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C12649					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300335	19951013	00335		1995	10	13	95ZZZX5689 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					21065					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300336	19951013	00336		1995	10	13	95ZZZX5690 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					40184					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300337	19951013	00337		1995	10	13	95ZZZX5691 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					22020					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300338	19951013	00338		1995	10	13	95ZZZX5692 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					23286					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300339	19951013	00339		1995	10	13	95ZZZX5693 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					24618					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300340	19951013	00340		1995	10	13	95ZZZX5694 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					99901					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300341	19951013	00341		1995	10	13	95ZZZX5695 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					20011					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300342	19951013	00342		1995	10	13	95ZZZX5696 	4	19950816	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	DEFECTIVE 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18869					UNIT WAS RETURNED FOR RE-CERTIFICATION TEST PER SB ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION TE	ST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB ELT-14, W	HICH WAS MANDATED APRIL 21, 1986.																	 
1995101300349	19951013	00349	CE 	1995	10	13	95ZZZX5704 	1	19950823	G	5510	380210417011	SUPPORT ASSY 		265210001322	RKWELL	NA265 	NA26580 	7630108	CE 										RT HORZ STAB	CRACKED 	B		A	JV2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	66ED	5805 			7L02	38032				DEFECTS WERE FOUND DURING ROUTINE MAINTENANCE INSPECTION PER CAMP CARD NR 27013, ATA 274006, LT, AND ATA 274007, RT. TH	E LT INBD HORIZ SUPPORT WAS FOUND BROKEN AT THE BEARING (PN BR4) AND THE RT INBD HORIZ SUPPORT WAS CRACKED AT THE BEARIN	G (PN BR4). THE BEARINGS WERE CORRODED AND FROZE UP CAUSING THEM TO BURN IN THE SUPPORT WHEN THE ELEVATORS WERE BEING O	PERATED. SUBMITTER RECOMMENDS A CLOSER INSPECTION OF THESE BEARINGS. THESE BEARINGS ARE SEALED BEARINGS.			2	L	7	2 	4F				A2WE 					 
1995101300350	19951013	00350	CE 	1995	10	13	95ZZZX5705 	1	19950823	G	5510	380210417011	SUPPORT ASSY 		265210001321	RKWELL	NA265 	NA26580 	7630108	CE 										LT HORZ STAB	CRACKED 	B			JV2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	66ED	5805 			7L13	38032				DEFECTS WERE FOUND DURING ROUTINE MAINTENANCE INSPECTION PER CAMP CARD NR 27013, ATA 274006, LT, AND ATA 274007, RT. TH	E LT INBD HORIZ SUPPORT WAS FOUND BROKEN AT THE BEARING (PN BR4) AND THE RT INBD HORIZ SUPPORT WAS CRACKED AT THE BEARIN	G (PN BR4). THE BEARINGS WERE CORRODED AND FROZE UP CAUSING THEM TO BURN IN THE SUPPORT WHEN THE ELEVATORS WERE BEING O	PERATED. SUBMITTER RECOMMENDS A CLOSER INSPECTION OF THESE BEARINGS. THESE BEARINGS ARE SEALED BEARINGS.			2	L	7	2 	4F				A2WE 					 
1995101300351	19951013	00351	GL 	1995	10	13	95ZZZX5706 	3	19950907	G	6114		HUB 			CESSNA	210 	T210M 	2073451	CE 						MCAULY	D3A34	D3A34C402 	GL 	PROPELLER	EXCESS CORROSION	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	761HS	1040 				21062275		776996		INSPECTION FOUND PROPELLER SLOW TO OPERATE. EXCESSIVE RUST, CORROSION, AND CONDENSATION FOUND INSIDE. OHC PROPELLER AT	 RECOMMENED TBO.					1	H	7	1 	3O				3A21 		5	C	P47GL	 
1995101300352	19951013	00352	SW 	1995	10	13	95ZZZX5707 	1	19950912	G	5523	440001501	TRIM TAB RIB 			GULSTM	500 	500S 	0141107	SW 										ELEVATOR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	9038N	3000 				3050				DURING C/W SB 198A, PART I, CRACKS WERE FOUND RT FWD SCREW HOLE IN LEFT AND RIGHT RIBS ON BOTH TRIM TABS. FOUND NO OTHE	R DAMAGE AND RIBS WERE REPAIRED/MODIFIED PER SB 198A, PART II.					1	H	7	2 	3O				6A1 					 
1995101300353	19951013	00353	GL 	1995	10	13	95ZZZX5708 	3	19950907	G	6111	C35A	CLAMP 			GULSTM	500 	500RKWELL 	0141102	SW 						HARTZL	HCA2V	HCA2VK2 	GL 	BLADE	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	2FOR		191 		JA4193			H1766		INSPECTION FOUND BLADE CLAMP BACK HALF CRACKED. SUSPECT POSSIBLE ENGINE VIBRATION.						1	H	7	2 	3O				6A1 		5	C	P24EA	 
1995101300354	19951013	00354	CE 	1995	10	13	95ZZZX5709 	1	19950915	G	3246	13889	BEARING 	TIMKEN 	1228100787 	BEECH 	2000 	2000 	1152000	CE 										LT MLG	FAILED 	B		A	PAI5	O				OTHER 				O			OTHER 			CL	CLIMB 	1			SO	05	8025L	137 			246	NC19				LT MAIN INBOARD WHEEL ASSY DEPARTED ACFT ON TAKEOFF ROLL. ACFT CONTINUED THE FLIGHT AND MADE A SUCCESSFUL LANDING ON RE	MAINING WHEEL. INVESTIGATION REVEALED THE WHEEL BEARINGS FAILED DUE TO CONTAMINATION OF THE BEARING LUBRICATION. TOTAL	 TIME SINCE MAIN WHEEL BEARING SEALING KIT NR 122-8001-1 WAS INSTALLED IS 137 HOURS. TOTAL TIME SINCE BEARING LUBRICATI	ON IS 86 HOURS. SUGGEST A MORE FREQUENT INSPECTION AND LUBRICATION SCHEDULE FOR THESE BEARINGS. LUBRICATION SCHEDULE I	S 100 HOURS OF OPERATION.		1	L	7	2 	4T			RT	A38ACE 					 
1995101300355	19951013	00355	CE 	1995	10	13	95ZZZX5710 	1	19950915	G	3246	1228100787	WHEEL 			BEECH 	2000 	2000 	1152000	CE 										LT MLG	DEPARTED 	B			PAI5	A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			SO	05	8025L	917 				NC19				LEFT MAIN INBOARD WHEEL DEPARTED AIRCRAFT ON TAKEOFF. AIRCRAFT MADE SUCCESSFUL LANDING ON REMAINING WHEEL. DETERMINED 	WHEEL BEARINGS FAILED DUE TO IMPROPER LUBRICATION CAUSING WHEEL TO DEPART. SUGGEST A MORE FREQUENT INSPECTION AND LUBRI	CATION SCHEDULE FOR THESE WHEEL BEARINGS.				1	L	7	2 	4T			RT	A38ACE 					 
1995101300356	19951013	00356	SW 	1995	10	13	95ZZZX5711 	1	19950906	G	2910	70061H000R180A	HOSE 			BELL 	206 	206B 	1181511	SW 										HYD PUMP	RUPTURED 	H				K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SO	16	67724					5195				AIRCRAFT HAD HYDRAULIC FAILURE. HOSE FROM HYDRAULIC PUMP TO FILTER RUPTURED.						1	G	7	1 	3U				H2SW 					 
1995101300357	19951013	00357	SW 	1995	10	13	95ZZZX5712 	1	19950918	G	6720		CONTROL TUBE 			BELL 	222 	222U 	1182140	SW 										T/R PITCH ACT	CHAFED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	911NM					47569				TAIL ROTOR PITCH ACTUATOR CONTROL TUBE HAS STARTED GETTING WEAR DOWN BELOW THE PAINT AS IT PASSES THROUGH THE BULKHEAD. 	 OPENED UP THE LIGHTNING HOLE TO ALLOW SUFFICIENT CONTROL TUBE CLEARANCE.					1	G	7	2 	3U				H9SW 					 
1995101300358	19951013	00358	WP 	1995	10	13	95ZZZX5713 	1	19950905	G	5610	SA269K07301	KIT 			HUGHES	269 	269C 	4470504	WP 										CANOPY	WRONG PARTS 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	17										KIT WAS FURNISHED FROM SCHWEIZER WITH MS20470A5 SOFT RIVETS INSTEAD OF MS20470AD5 RIVETS AS INDICATED ON PARTS LIST. TH	IS KIT IS THE 'ALUMINUM CANOPY SLAT-V BRACKET KIT'. THE 6 RIVETS AFFECTED ARE USED TO ATTACH THE 'V' BRACKET TO THE ALU	M SLAT.				1	G	7	1 	3O				4H12 					 
1995101300360	19951013	00360	SW 	1995	10	13	95ZZZX5715 	1	19950915	G	3211	20603010417	FITTING 			BELL 	206 	206L1 	1182107	SW 										GEAR ATTACH	CRACKED 	B	S	A	EHHR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	1071C	1893 				45346				FOUND NUTPLATE CRACKED IN HALF WHEN FITTING WAS REMOVED FOR ACCESS TO BELLY SKIN. FOUND INNER CAVITIES OF FITTING TO BE	 TRAPPING WATER, NOT SEALED, OTHER NUTPLATES CORRODED. MUST REMOVE FITTING FROM AIRCRAFT TO SEE NUTPLATE.					1	G	7	1 	3U				H2SW 					 
1995101300361	19951013	00361	GL 	1995	10	13	95ZZZX5716 	2	19950825	G	7200	23053301	ENGINE 			BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20 	03013	GL 					POWER SECTION	FLAME-OUT 	D		A		A				UNSCHED LANDING 				X	R		ENGINE FLAMEOUT 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			NM	09	34698	355 				4324	296031			HELICOPTER EXPERIENCED 3 ENGINE FLAME-OUTS WITHIN APPROXIMATELY 5 MINUTES. THE AUTO RE-IGNITION STARTED THE ENGINE IN-F	LIGHT EACH TIME. NORMAL LANDING WAS ACCOMPLISHED. A COMPLETE INSPECTION OF THE FUEL SYSTEMS, CONTROL SYSTEMS, FUEL FIL	TERS, AIR FILTERS, FUEL NOZZLE, FUEL CONTROL, GOVERNOR, FUEL PUMPS, FUEL VENTS. GROUND RAN AND TEST FLOWN FOR 4 HOURS W	ITH NO MALFUNCTIONS. COULD NOT FIND A CAUSE FOR THE FLAME-OUTS.			1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995101300452	19951013	00452	WP 	1995	10	13	95ZZZX5717 	1	19950915	G	6320	369D25100505	TRANSMISSION 			HUGHES	369 	369D 	4470706	WP 										MAIN GEARBOX	MAKING METAL 	B			EOOR	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			AL	03	4282X	2702 	2570 		1810	180253D				PILOT REPORTED A CHIP LIGHT AND UPON INSPECTION OF THE CHIP DETECTOR, A LARGE SHINING FLAKE AND NUMEROUS SMALLER FLAKES 	WERE FOUND. UNIT WAS SENT IN FOR OVERHAUL. (UNIT HAS 429.6 HOURS REMAINING TO OVERHAUL).					1	G	7	1 	3U				H3WE 					 
1995101300453	19951013	00453	EU 	1995	10	13	95ZZZX5718 	1	19950731	G	2150		DRIVE BELT 			SNIAS 	350 	AS350B 	8680801	EU 										AIR CONDITIONER	SLIPS 	B		A	DYRR	K				NONE 				B	W		SMOKE/FUMES/ODORS/SPARKS 	INADEQUATE Q C 		IN	INSP/MAINT 	1			NM	07	58045					1602				AIR CONDITIONER BELT SLIPPING, CAUSE, SMOKE IN COCKPIT. IT HAS BEEN NOTED THE BELTS OF THE SAME P/N OCCASIONALLY HAVE A	 SLIGHT SIZE VARIATION AND WILL NOT ALLOW ADJUSTMENT TO BE MADE FULLY. BETTER QUALITY CONTROL BY THE STC HOLDER, TO PRE	CLUDE RECURRENCE.				1	G	7	1 	3U				H9EU 					 
1995101300454	19951013	00454	EU 	1995	10	13	95ZZZX5719 	1	19950522	G	6330	350A21129200	SUPPORT 			AEROSP	AS355 	AS355F1 	8680810	EU 										RT MAIN GEARBOX	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	30LG	7847 				5065				DURING ROUTINE INSPECTION, FOUND MAIN GEARBOX SUPPORT RIVETS WORKING. FOUND FLANGE BROKEN OFF SPAR AT STA 108.3 INCHES.	 SUBMITTER SUSPECTS OVERTORQUE OR HARD LANDING AS CAUSE.					1	G	7	2 	3U				H11EU 					 
1995101300455	19951013	00455	EU 	1995	10	13	95ZZZX5720 	1	19950522	G	6330	355A21210020	SPAR 			AEROSP	AS355 	AS355F1 	8680810	EU 										MAIN GEARBOX	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	30LG	7847 				5065				DURING ROUTINE INSPECTION, FOUND MAIN GEARBOX SUPPORT RIVETS WORKING. FOUND A 4 INCH PARTICLE CRACK IN SPAR AT STA 144.	5 INCHES. SUBMITTER SUSPECTS HARD LANDING OR OVERTORQUE AS CAUSE.					1	G	7	2 	3U				H11EU 					 
1995101300456	19951013	00456	EU 	1995	10	13	95ZZZX5721 	1	19950427	G	6210	117150071	BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	SKIN DEFORMED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	3803 	1502 		273	7173				BLADE FAILED INSPECTION FOR SKIN DEFORMATION AND LOOP ROVING. BLADE IS LOCATED AT CTI.						1	G	7	2 	3U				H13EU 					 
1995101300457	19951013	00457	EU 	1995	10	13	95ZZZX5722 	1	19950427	G	6210	117150071	BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	SKIN DEFORMED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	3803 	1502 		287	7173				BLADE FAILED INSPECTION FOR SKIN DEFORMATION AND LOOP ROVING. BLADE IS LOCATED AT CTI.						1	G	7	2 	3U				H13EU 					 
1995101300458	19951013	00458	EU 	1995	10	13	95ZZZX5723 	1	19950427	G	6210	117150071	BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	SKIN DEFORMED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	3803 	1502 		289	7173				BLADE FAILED INSPECTION FOR SKIN DEFORMATION AND LOOP ROVING. BLADE IS LOCATED AT CTI.						1	G	7	2 	3U				H13EU 					 
1995101300459	19951013	00459	EU 	1995	10	13	95ZZZX5724 	1	19950427	G	6210	117150071	BLADE 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	SKIN DEFORMED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	7060G	3803 	1502 		302	7173				BLADE FAILED INSPECTION FOR SKIN DEFORMATION AND LOOP ROVING. BLADE IS LOCATED AT CTI.						1	G	7	2 	3U				H13EU 					 
1995101300460	19951013	00460	EU 	1995	10	13	95ZZZX5725 	1	19950624	G	6210	117150081	BLADE 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R	SKIN DEFORMED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	158BK	3308 	203 		88	7058				BLADE FAILED INSPECTION FOR SKIN DEFORMATION AND LOOP ROVING. BLADE IS LOCATED AT CTI.						1	G	7	2 	3U				H13EU 					 
1995101300461	19951013	00461	EU 	1995	10	13	95ZZZX5726 	1	19950624	G	6210	117150081	BLADE 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R	SKIN DEFORMED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	158BK	3824 	203 		278	7058				BLADE FAILED INSPECTION FOR SKIN DEFORMATION AND LOOP ROVING. BLADE IS LOCATED AT CTI.						1	G	7	2 	3U				H13EU 					 
1995101300462	19951013	00462	SW 	1995	10	13	95ZZZX5727 	1	19950602	G	6230	206010454109	SLEEVE ASSY 			BELL 	206 	206B 	1181511	SW 										SWASHPLATE	BEARING WORN 	B			WG3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	33TV	580 			RE5336	4306				COMPLETED REPAIR TO SWASHPLATE ASSEMBLY, PN 206-010-450-113, SN RE21051, DUE TO WORN BEARING SEALS IN SLEEVE ASSEMBLY, P	N 206-010-454-109, SN RE5336. INSTALLED NEW SLEEVE ASSY, PN 206-010-454-109, SN RE5906.					1	G	7	1 	3U				H2SW 					 
1995101300463	19951013	00463	SW 	1995	10	13	95ZZZX5728 	1	19950427	G	6210	289052017	SEAL 			BELL 	206 	206B 	1181511	SW 										FREEWHEEL	LEAKING 	B			WG3R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	27	33TV	471 				4306				FOUND FREEWHEEL INPUT SEAL LEAKING OIL. REMOVED FREEWHEEL ASSY TO REPLACE SEAL ASSY. INSTALLED NEW SEAL, PN 2890-52017	, 1 EACH AND O-RINGS, PN MS2961-237, 1 EACH, AND PN MS29561-215, 1 EACH.					1	G	7	1 	3U				H2SW 					 
1995101300464	19951013	00464	SW 	1995	10	13	95ZZZX5729 	1	19950509	G	6330	MS141028	BEARING 			BELL 	206 	206B 	1181511	SW 										TRANSMISSION	LOOSE 	B			WG3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	33TV	511 				4306				TRANSMISSION RESTRAINT PIN ASSY BEARING AND SLEEVE LOOSE IN ASSY. REMOVED PIN ASSY AND INSTALLED NEW BEARING, PN MS1401	2-8, AND SLEEVE, PN 206-031-513-101, INTO PIN ASSY, AND REINSTALLED ON TRANSMISSION.					1	G	7	1 	3U				H2SW 					 
1995021000059	19950210	00059	SO 	1995	2	10	95ZZZX573 	1	19950101	G	5523	6358501	TRIM TAB 			PIPER 	PA28 	PA28161 	7102803	SO 										STABILIZER RT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13										INSPECTION OF STABILIZER TRIM TAB AND ARM ASSEMBLY FOUND CORROSION PER 'ALERTS' PUBLICATION WHICH CITES PIPER AIRCRAFT P	A28 AND PA32 SERIES. CLEANED, PAINTED AND REPAIRED AS NECESSARY.					1	L	7	1 	3O				2A13 					 
1995101300465	19951013	00465	EU 	1995	10	13	95ZZZX5730 	1	19950831	G	2810	FTA017521E	TANK 			BOLKMS	105 	BO105CBS 	5626008	EU 										FUEL MAIN	COLLAPSED 	B			CZ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	492HL				43937	S803				SNAPS HOLDING TANK ARE WORN ALLOWING TANK TO COLLAPSE. THE COLLAPSED TANK CAUSED ERRONEOUS FUEL QUANTITY READINGS. REP	LACED TANKS.					1	G	7	2 	3U			NC	H3EU 					 
1995101300466	19951013	00466	EU 	1995	10	13	95ZZZX5731 	1	19950627	G	7712	117902131	CONTROL 			BOLKMS	BK117 	BK117C1 	5626025	EU 										RPM CONTROL	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	596 			019403003	7505				OCCASIONAL RUNS IN 102 PERCENT MODE WITHOUT EXPLANATION. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995101300467	19951013	00467	EU 	1995	10	13	95ZZZX5732 	1	19950718	G	6210	365A11503002	BLADE 			AEROSP	SA365 	AS365N2 	8680815	EU 										TIP CAP	CRACKED 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	2XJ	2193 			3438	6396				CRACK AROUND AFT WASHER OF M/R BLADE TIP CAP. REPLACED WITH SERVICEABLE.						1	G	7	2 	3U			RT	H10EU 					 
1995101300468	19951013	00468	EU 	1995	10	13	95ZZZX5733 	1	19950623	G	6220	579060	BEARING 			AEROSP	SA365 	SA365N1 	8680668	EU 										SPHERICAL THRUST	BLISTERED 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	93SV	972 			1767	6286				BLUE SPHERICAL THRUST BEARING BLISTERED. INSTALLED 2 EACH SERVICEABLE SPHERICAL THRUST BEARINGS.						1	G	7	2 	3U				H10EU 					 
1995101300469	19951013	00469	EU 	1995	10	13	95ZZZX5734 	1	19950623	G	6220	579060	BEARING 			AEROSP	SA365 	SA365N1 	8680668	EU 										SPHERICAL THRUST	BLISTERED 	B			INDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	93SV	972 			3276	6286				BLUE SPHERICAL THRUST BEARING BLISTERED. INSTALLED 2 EACH SERVICEABLE SPHERICAL THRUST BEARINGS.						1	G	7	2 	3U				H10EU 					 
1995102000073	19951020	00073	CE 	1995	10	20	95ZZZX5739 	1	19950821	G	5400	52501014	BRACKET 			CESSNA	340 	340A 	2076405	CE 										NACELLE	SCREWS LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	21234	1400 				340A1207				NACELLE BRACKET SCREWS WORKED LOOSE CAUSING THE BRACKET TO CHAFE ON THE SKIN AND STIFFENER WHICH, IN TURN, CAUSED THE SK	IN TO CRACK. SUBMITTER RECOMMENDS CHECKING THESE SCREWS ON A 25-50 HOUR BASIS. THIS IS THE SECOND AIRCRAFT FOUND WITH 	THIS CONDITION, BOTH REQUIRING REPAIR.				1	L	7	2 	3O				3A25 					 
1995021000060	19950210	00060	SO 	1995	2	10	95ZZZX574 	1	19950101	G	5523	6358500	TRIM TAB 			PIPER 	PA28 	PA28161 	7102803	SO 										STABILIZER LT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13										INSPECTION OF STABILIZER TRIM TAB AND ARM ASSEMBLY FOUND CORROSION PER 'ALERTS' PUBLICATION WHICH CITES PIPER AIRCRAFT P	A28 AND PA32 SERIES. CLEANED, PAINTED AND REPAIRED AS NECESSARY.					1	L	7	1 	3O				2A13 					 
1995102000074	19951020	00074		1995	10	20	95ZZZX5740 	4	19950908	G	2216	047339900	SENSE SPRING 	BENDIX 	KS270A 	CESSNA	208 	208B 	2073701	CE 										AP PITCH SERVO	BROKEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	748FE				23930	208B0241				THIS SPRING, WHEN BROKEN, CAN CAUSE THE SERVO CLUTCH TO STAY ENGAGED INHIBITING EASY MOVEMENT AFTER AUTOPILOT DISCONNECT	. SUBMITTER RECOMMENDED INSPECTION OF SERVO 'PLAY' DURING ELEVATOR SERVO INSPECTION OF PHASE CARD INSPECTION PROGRAM. S	ERVO MUST BE REMOVED FROM MOUNT.				1	H	7	1 	3T				A37CE 					 
1995102000075	19951020	00075	CE 	1995	10	20	95ZZZX5741 	1	19950825	G	5751	05232192	BRACKET 			CESSNA	172 	172M 	2072418	CE 										RT AILERON	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	193JS	1798 				17265118				ANNUAL INSPECTION FOUND BOTH RT AND LT UPPER AILERON BRACKETS HAVE .50 INCH CRACK AT BEND IN BRACKET. CRACK EXTENDS FRO	M MIDDLE OF BEND OUTWARD. SUBMITTER SUGGESTS CAUSE OF EXCESSIVE TORQUE ON BELLCRANK STOP BUSHING BOLTS. RECOMMEND ALL 	INSPECTORS PAY SPECIAL ATTENTION TO BELLCRANK BRACKETS.				1	H	7	1 	3O			NT	3A12 					 
1995102000076	19951020	00076	CE 	1995	10	20	95ZZZX5742 	1	19950825	G	5751	05232193	BRACKET 			CESSNA	172 	172M 	2072418	CE 										LT AILERON	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	193JS	1798 				17265118				ANNUAL INSPECTION FOUND BOTH RT AND LT UPPER AILERON BRACKETS HAVE .50 INCH CRACK AT BEND IN BRACKET. CRACK EXTENDS FRO	M MIDDLE OF BEND OUTWARD. SUBMITTER SUGGESTS CAUSE OF EXCESSIVE TORQUE ON BELLCRANK STOP BUSHING BOLTS. RECOMMEND ALL 	INSPECTORS PAY SPECIAL ATTENTION TO BELLCRANK BRACKETS.				1	H	7	1 	3O			NT	3A12 					 
1995102000077	19951020	00077	EA 	1995	10	20	95ZZZX5743 	2	19950927	G	7310	LW120980210	LINE 			PIPER 	PA24 	PA24250 	7102404	SO 	LYC 	O540 	IO540* 	41532	EA 					INJECTOR B-NUT	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11		10 								INSPECTION FOUND INJECTOR FITTING BROKEN.						1	L	7	1 	3O	3	O		1A15 	1E4				 
1995102000078	19951020	00078	SO 	1995	10	20	95ZZZX5744 	1	19950918	G	5711	67070002	SPAR 			PIPER 	PA28 	PA28R200 	7102811	SO 										MLG WELL	CORRODED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	2611R	1776 				L687151A				MAIN SPAR EXFOLIATION CORROSION FOUND IN 2 SEPARATE AREAS WHERE THE LANDING GEAR WHEELWELL IS LOCATED.						1	L	7	1 	3O				2A13 					 
1995102000079	19951020	00079	CE 	1995	10	20	95ZZZX5745 	1	19950926	G	7920		HOSE 			CESSNA	177 	177B 	2073708	CE 										ENGINE COMP	DETERIORATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	19274	903 				17702566				DURING ANNUAL INSPECTION, FOUND ALL FUEL AND OIL HOSES IN ENGINE COMPARTMENT TO BE ORIGINAL - 18 YEARS OLD. SUBMITTER S	UGGESTS THE MECHANICS AND I.A.'S IN THE FIELD NEED MANDATORY TIME CHANGE REQUIREMENTS FOR FLEXIBLE HOSES.					1	H	7	1 	3O				A13CE 					 
1995102000080	19951020	00080	SO 	1995	10	20	95ZZZX5746 	2	19950926	G	8530	639615	ROCKER ARM 			CESSNA	150 	150H 	2071818	CE 	CONT 	O200 	O200A 	17020	SO 					EXHAUST ROCKER	FAILED 	B			KO2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	01	50231	2678 				15069153	690208A			THE EXHAUST VALVE WAS NOT STUCK IN THE GUIDE. THE BUSHING HAD BEEN CHANGED IN THE ARM AT SOME TIME (OIL HOLE IS NOT LIN	ED UP WITH OIL HOLE IN THE ARM). MAYBE THE BUSHING WAS TOO TIGHT OF A FIT.					1	H	7	1 	3O	3	O		3A19 	E252				 
1995102000081	19951020	00081	SO 	1995	10	20	95ZZZX5747 	1	19950922	G	3040	5553562	CONVERTER 	ALCO 		PIPER 	PA31T 	PA31T 	7103124	SO 										WIPER	SHAFT SEIZED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	171AF	4218 			5604	21T7920089				TRIPPED CIRCUIT BREAKER FOR WINDSHIELD WIPER SYSTEM FOUND WATER CONTAMINATION IN CONVERTER DUE TO BAD SHAFT SEALING. SU	BMITTER RECOMMENDS CONVERTERS BE DISASSEMBLED, CLEANED, AND RE-GREASED ON A 'TIME IN SERVICE' INTERVAL TO PREVENT THIS P	ROBLEM. SHAFT SEAL TYPE INADEQUATE.				1	L	7	2 	3T				A8EA 					 
1995102000083	19951020	00083	SO 	1995	10	20	95ZZZX5749 	1	19950801	G	5711	6207302	SPAR 			PIPER 	PA28 	PA28161 	7102803	SO 										WS 19.7-WS 57	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	2296Z	621 				287816116				DURING ANNUAL INSPECTION, EXFOLIATION CORROSION WAS FOUND ON LEFT WING MAIN SPAR BETWEEN STA NR 19.73 - STA 57.0. AFFEC	TED AREA WAS 6 INCHES LONG, ESTIMATE .125 INCH DEEP. AIRCRAFT HAD BEEN PURCHASED FROM PUERTO RICO.					1	L	7	1 	3O				2A13 					 
1995021000061	19950210	00061	SO 	1995	2	10	95ZZZX575 	1	19950101	G	2731	6524800	ARM ASSY 			PIPER 	PA28 	PA28161 	7102803	SO 										STABILIZER TRIM	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13										INSPECTION OF STABILIZER TRIM TAB AND ARM ASSEMBLY FOUND CORROSION PER 'ALERTS' PUBLICATION WHICH CITES PIPER AIRCRAFT P	A28 AND PA32 SERIES. CLEANED, PAINTED AND REPAIRED AS NECESSARY.					1	L	7	1 	3O				2A13 					 
1995102000084	19951020	00084	EA 	1995	10	20	95ZZZX5750 	2	19950724	G	8530	LW12717	CYLINDER 			GULSTM	680 	680FL 	0141608	SW 	LYC 	O540 	IGSO540B1C 	41532	EA 					EXHAUST VALVE	DEFECTIVE 	E				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			CE	09	290MP	191 				1553104	RL225550			JUST AFTER TAKEOFF, THE LEFT ENGINE BEGAN TO RUN ROUGH. THE AIRCRAFT RETURNED FOR LANDING AND A COMPRESSION CHECK WAS P	ERFORMED. THE NR 6 CYLINDER HAD LOW COMPRESSION DUE TO LEAKAGE PAST THE EXHAUST VALVE. THE EXHAUST VALVE APPEARED NORM	AL EXCEPT FOR DISCOLORIZATION FROM HEAT.				1	H	7	2 	3O	3	O		2A4 	1E7				 
1995102000085	19951020	00085	EA 	1995	10	20	95ZZZX5751 	2	19950712	G	7414	D4RN2021	MAGNETO 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					ENGINE	POINTS FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	01	4829G		447 		26693	17273377	L790676T			COMPLETE ENGINE FAILURE DUE TO MAG POINTS ATTACH COMING LOOSE. SUBMITTER RECOMMENDS BETTER MEANS OF ATTACHING POINT TO 	MAGNETO.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995102000086	19951020	00086	CE 	1995	10	20	95ZZZX5752 	1	19950723	G	2810	121640747	RESERVOIR 			CESSNA	210 	T210N 	2073456	CE 										LT FUEL	CRACKED 	D				K				NONE 				K	B		FLUID LOSS 	SMOKE/FUMES/ODORS/SPARKS 		IN	INSP/MAINT 	1			WP	07	6506G	2644 				21064406				PILOT REPORTED AN AVGAS ODOR IN COCKPIT AFTER AIRCRAFT SAT FOR APPROXIMATELY ONE HOUR. LEFT RESERVOIR TANK FOUND CRACKE	D ON AFT SIDE ABOVE WELDED FITTING. NO WEAR OR CHAFING PRESENT.					1	H	7	1 	3O				3A21 					 
1995102000087	19951020	00087	EA 	1995	10	20	95ZZZX5753 	2	19950627	G	8520		CRANKSHAFT 			GULSTM	680 	680FL 	0141608	SW 	LYC 	O540 	IGSO540B1A 	41532	EA 					NR 6 JOURNAL	FAILED 	E				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			Y	K		ENGINE STOPPAGE 	FLUID LOSS 		CR	CRUISE 	1			SW	99	114MN					1553107	L34250			WHILE IN CRUISE FLIGHT, THE RIGHT ENGINE QUIT. THE PROP CONTINUED TO WINDMILL. THE PILOT FEATHERED THE PROP AND SECURE	D RIGHT ENGINE. AN EMERGENCY LANDING WAS COMPLETED. THE ENGINE WAS INSPECTED. THE CRANKCASE WAS CRACKED AND DISTORTED	 AROUND NR 6 CYLINDER. CRANKSHAFT FAILED AT NR 6 JOURNAL. NR 6 ROD BROKEN AT BASE AND AFT OF PISTON PIN. CRANKSHAFT T	T UNKNOWN. ENGINE TT, 3,828.2 HOURS.			1	H	7	2 	3O	3	O		2A4 	1E7				 
1995102000088	19951020	00088	SO 	1995	10	20	95ZZZX5754 	2	19950901	G	8530	SA539988	VALVE 			CESSNA	182 	182 	2072702	CE 	CONT 	O470 	O470R 	17026	SO 					INTAKE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99		230 					191187R			CYLINDER FAILED COMP. TEST. INTAKE VALVE LEAK. DEFECTIVE INTAKE VALVE HAD ONE-FOURTH OF FACE BURNED AND PITTED, AND A 	SMALL CRACK ACROSS THE FACE. INTAKE VALVE MADE BY SUPERIOR AIR PARTS.					1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995102000089	19951020	00089	SO 	1995	10	20	95ZZZX5755 	1	19950811	G	8120	LW14463	DRAIN TANK 			PIPER 	PA32 	PA32RT300T 	7103216	SO 	LYC 	O540 	TIO540S1AD 	41532	EA 					TURBO	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	03	9244C	2056 				32R1887004	L510061A			TURBO DRAIN TANK FOUND CRACKED 1.50 INCHES LONG AND OIL LEAKING OUT. CRACK WAS AT BASE OF WELD WHERE MOUNT TUBE IS WELD	ED TO TANK. SHEET METAL WALL JUST AHEAD OF TANK WAS WORN THROUGH EDGE OF TANK WHICH HAD BEEN RIDING ON IT. SUBMITTER R	ECOMMENDS INSPECTING AIRCRAFT FOR BENDING LOAD ON TANK AND CAUSING TANK METAL TO FATIGUE AND CRACK. IF WEAR IS FOUND ON	 SHEET METAL, CUT OUT ROUND AREA AND PUT ON A CURVED PATCH.			1	L	7	1 	3O	3	O		A3SO 	E14EA				 
1995102000090	19951020	00090	CE 	1995	10	20	95ZZZX5756 	1	19950901	G	2436	363800961	REGULATOR 	LAMAR 		BEECH 	58 	58 	1152740	CE 										NR 1 DC SYSTEM	FAILED 	E				O				OTHER 				B	H		SMOKE/FUMES/ODORS/SPARKS 	ELECT. POWER LOSS-50 PC 		CL	CLIMB 	1			GL	13	6025Y	1115 			1931	TH1010				AIRCRAFT IN CLIMB TO CRUISE ALTITUDE, NOTICED SMOKE SMELL AND THEN SMOKE IN THE COCKPIT AND CABIN, CONTINUED TO GET WORS	E AND THEN A TOTAL ELECTRICAL FAILURE OF ALL COMPONENTS. FOUND LEFT (NR 1) VOLTAGE REGULATOR INOP. SUSPECT THE OVERVOL	TAGE RELAY INSIDE THE REGULATOR FAILED. OVERHAULED REGULATOR INSTALLED AND SYSTEM WORKED OK.				1	L	7	2 	3O				3A16 					 
1995102000091	19951020	00091	EA 	1995	10	20	95ZZZX5757 	2	19950824	G	8530	LW14995	RETAIN SPRING 			PIPER 	PA44 	PA44180 	7104402	SO 	LYC 	O360 	O360E1A6 	41514	EA 					NR 2 CYL TUBE	BROKEN 	B			OG5R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	21	852ND					4495006	L2456936A			INSPECTED OVERHAULED ENGINE (FACTORY OVERHAUL) PER SB 519 DURING SCHEDULED ENGINE CHANGE. FOUND NR 2 CYLINDER SHROUD SP	RING BROKEN. SPRING FOUND BEFORE ENGINE RUN-UP. INSTALLED NEW PART.					1	L	7	2 	3O	3	O		A19S0 	E286				 
1995102000092	19951020	00092	GL 	1995	10	20	95ZZZX5758 	3	19950828	G	6111	S84B0	BLADE 													MCAULY	2A36C	2A36C23 	GL 	PROPELLER	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15					B20299YS			73501		UPON INSPECTION, BLADE WAS FOUND CRACKED IN THREADS. BLADE HAS BEEN SCRAPPED.																5	C	P880	 
1995102000093	19951020	00093	EA 	1995	10	20	95ZZZX5759 	2	19950921	G	8520	LW11026	CRANKCASE 			MOONEY	M20 	M20C 	5870208	SW 	LYC 	O360 	O360A1D 	41514	EA 					RT HALF	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	639MA	2703 	1997 		LW745436A	2893	L745436A			RIGHT CRANKCASE HALF FROM PARTING SURFACE LOWER NR 3 BOLT HOLE HAS 1 EACH .25 INCH CRACK FROM BOLT HOLE TO PARTING SURFA	CE, AND 1 EACH 1.850 INCH CRACK FROM BOLT HOLE INTO CASE WEBBING. SUBMITTER CANNOT DETERMINE THE CAUSE OF CRACK. NOTE:	 THE PROPELLER GOVERNOR OIL LINE AND THE GENERATOR HAD TO BE REMOVED BEFORE THE CRACK AREA WAS VISIBLE.				1	L	7	1 	3O	3	O		2A3 	E286				 
1995021000062	19950210	00062	CE 	1995	2	10	95ZZZX576 	1	19950109	G	3246	4087A	WHEEL ASSY 	PARKERHANFIN		BEECH 	33 	F33A 	1151425	CE 										LIP AREA	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	1096W	10000				CE436				UPON INFLATION OF NOSE WHEEL AND TIRE ASSEMBLY, A 6 INCH PIECE OF THE WHEEL LIP FAILED. TIRE AND TUBE WERE DESTROYED, F	AILED SECTION OF WHEEL WAS FOUND 50 FEET AWAY. NO PERSONNEL WERE INJURED. SUSPECT CAUSE, FATIGUE-CASTING FLAW.					1	L	7	1 	3O				3A15 					 
1995102000094	19951020	00094		1995	10	20	95ZZZX5760 	2	19950917	G	7322	2520501	BEARING 	BENDIX 	DPN2 															FUEL CONT DRV	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23			2006 							FUEL CONTROL DRIVE BEARING FAILURE. UNDETERMINED CAUSE.																			 
1995102000095	19951020	00095	CE 	1995	10	20	95ZZZX5761 	1	19950911	G	5711	05111625	SPAR 			CESSNA	170 	170B 	2072306	CE 										FWD CARRY-THRU	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	3195A	1960 				25839				AIRCRAFT WAS IN FOR FIRST ANNUAL IN 8 YEARS. HEADLINER WAS TO BE REPLACED. UPON REMOVAL OF SUNVISORS AND HEADLINER, SE	VERE CORROSION, EXCEEDING 10 PERCENT OF SPAR MATERIAL THICKNESS, WAS FOUND.					1	H	7	1 	3O				A799 					 
1995102000096	19951020	00096	CE 	1995	10	20	95ZZZX5762 	1	19950830	G	3243	0411549	BRACKET 			CESSNA	182 	182Q 	2072732	CE 										LT MASTER CYL	BROKEN 	B			LX5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	821LL	5538 				18266198				LEFT BRAKE MASTER CYLINDER BRACKET BROKEN. BRACKET SET, PN 0411549, INSIDE BENT AND BROKEN, PN 0411550, OUTSIDE BADLY B	ENT.					1	H	7	1 	3O			NT	3A13 					 
1995102000097	19951020	00097	EA 	1995	10	20	95ZZZX5763 	2	19950925	G	7414	M3525	COIL 	SLICK 	4281 	CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					MAGNETO	OPEN 	B			CWBR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	05	6154Q		1299 		88040147	15285774	L2146015			PILOT REPORTED RT MAG INOPERATIVE. INVESTIGATION FOUND MAGNETO COIL OPEN, COIL REPLACED AND MAGNETO FUNCTIONED NORMALLY	. SUBMITTER STATED THIS IS 4TH SUCH PROBLEM WITH THIS COIL (ORANGE). NEW COIL IS BLACK, PN M3575.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995102000098	19951020	00098	CE 	1995	10	20	95ZZZX5764 	1	19950819	G	3242	C1630300313	BRAKE ASSY 			CESSNA	180 	180J 	2072622	CE 										LT MLG	SEIZED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	9797G					18052297				BRAKE WOULD NOT RELEASE AFTER BRAKE APPLICATION, PULLED APART AND FOUND GRITTY DEBRIS IN FLUID SIDE OF BRAKE PUCKS. CLE	ANED, REINSTALLED, AND OPERATIONALLY CHECK OK.					1	H	7	1 	3O				5A6 					 
1995102000099	19951020	00099	SO 	1995	10	20	95ZZZX5765 	2	19950814	G	8530	SA6323105	GASKET 			PIPER 	PA28 	PA28R201T 	7102813	SO 	CONT 	O360 	TSIO360FB 	17025	SO 					NR 3 CYL ROCKER	FAILED 	D				O				OTHER 				K			FLUID LOSS 			NR	NOT REPORTED 	1			NM	01	38182	3 				28R7703186	305238H			REPLACED ROCKER BOX COVER GASKETS WITH NEW SUPERIOR SILICON GASKET. USED ALL NORMAL PROCEDURES FOR INSTALLATION. COVER	S CAME OFF IN-FLIGHT CAUSING ENGINE OIL LOSS. AFTER FURTHER INVESTIGATION, SUPERIOR FOUND A SL NR P1B-93007, THAT SAYS 	TO USE LOCTITE ON SCREW THREADS FOR THIS GASKET ONLY. SUBMITTER FEELS GASKET IS DEFECTIVE AND A FATALLY DANGEROUS PRODU	CT. NO PAPERWORK WITH GASKET SAYING TO USE LOCTITE. ENGINE REQUIRES OVERHAUL.			1	L	7	1 	3O	3	O		2A13 	E9CE				 
1995102000100	19951020	00100	SW 	1995	10	20	95ZZZX5766 	1	19950915	G	7120	620032506	MOUNT 			GULSTM	500 	500S 	0141107	SW 										ENGINE	CORRODED 	B			HI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	9038N	5471 				3050				CORROSION BETWEEN PLATE AND CAST BEAM ALL FOUR SIDES. AREA BETWEEN PLATE AND BEAM CAN HOLD MOISTURE. CORROSION LOCATED	 UNDER PN 62003211 BLOCK. RECOMMEND REMOVE PLATES, CLEAN CORROSION, FILL WITH PRC AND REASSEMBLE. REPAIR WILL REQUIRE 	DER APPROVAL.				1	H	7	2 	3O				6A1 					 
1995102000101	19951020	00101	SW 	1995	10	20	95ZZZX5767 	1	19950915	G	7120	620032508	MOUNT 			GULSTM	500 	500S 	0141107	SW 										ENGINE	CORRODED 	B			HI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	1938S	4559 				3167				CORROSION BETWEEN PLATE AND CAST BEAM ALL FOUR SIDES. AREA BETWEEN PLATE AND BEAM CAN HOLD MOISTURE. CORROSION LOCATED	 UNDER P/N 62003211 BLOCK. RECOMMEND REMOVE PLATES, CLEAN CORROSION. FILL WITH PRC AND REASSEMBLE. REPAIR WILL REQUIR	E DER APPROVAL.				1	H	7	2 	3O				6A1 					 
1995102000102	19951020	00102	WP 	1995	10	20	95ZZZX5768 	2	19950918	G	7261	30748831	OIL TUBE 			BRAERO	DH125 	BAE125800A 	1500285	EU 	GARRTT	TFE731	TFE7315R 	01518	WP 					NR 6 BEARING	CRACKED 	D				E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	15	95AE	2578 				NA0447	P91455			DURING STABLE CRUISE, A DROP OF OIL PRESSURE INDICATED ON MASTER WARN PANEL LED TO AN ENGINE SHUT DOWN (RT) AFTER POWER 	BACK ELECTION AND CONTINUED DROP OF PRESSURE ON GAUGE. INSPECTION REVEALED A CRACKED OIL TUBE PROVIDING PRESSURE TO ENG	INE NR 6 BEARING. CRACK OCCURRED AT FERRULE ELBOW EXITING SHROUD. SENT BOTH ENGINE LINES (NR 1 AND NR 2 ENGINES) TO AL	LIED SIGNAL FOR EVALUATION. NEW LINES INSTALLED.			2	L	7	2 	4F	4	F	RT	A3EU 	E6WE				 
1995102000103	19951020	00103	NE 	1995	10	20	95ZZZX5769 	1	19950826	G	7120		BOLT 			CONAER	LA4 	LA4200 	5110310	NE 										ENGINE MOUNT	FAILED 	D		A		K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NE	05	8006E	1511 				1042				ONE LOWER ENGINE MOUNT BOLT BROKE IN-FLIGHT, CONDITION WAS DISCOVERED BY OWNER WHILE CHECKING OIL. ENGINE MOUNT SPACER	 WENT OUT THROUGH PROPELLER CAUSING SIGNIFICANT DAMAGE TO PROPELLER. WHEN MFG WAS ASKED, THEY SAID NEW BOLTS ARE NOW IN	STALLED AND SENT 4 NEW ONES. WHEN THE OTHER 3 BOLTS WERE REMOVED, A VERY VISIBLE WEAR MARK WAS NOTED WHERE THE ONE BROK	E. FOUR BOLTS OF THE NEW P\N NAS1307-52 WERE INSTALLED.			1	H	7	1 	3O				1A13 					 
1995021000063	19950210	00063	CE 	1995	2	10	95ZZZX577 	1	19950117	G	2435	IRT13	BEARING 	PRESTOLITE 	ALT9422 	CESSNA	310 	310R 	2074245	CE 										SLIP RING END	FAILED 	D				A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			EA	17	41159		375 		A98043	310R0727				PILOT REPORTED ALTERNATOR FAIL LIGHT CAME ON RETURNING TO HOME BASE. FOUND BRUSHES AND SPRINGS BROKEN. REMOVED END BEA	RING CAP AND FOUND BEARING WAS DESTROYED. THIS IS THE THIRD ALTERNATOR END BEARING FAILURE IN 3 MONTHS. THE OTHER TWO 	HAD 600 AND 700 HOURS S.O.H. FOUND THIS HAS BEEN A PROBLEM WITH THESE ALTERNATORS FOR SOME TIME. SUBMITTER PLANS TO IN	SPECT AND REPLACE BEARINGS AT 300 HOURS.			1	L	7	2 	3O				3A10 					 
1995102000104	19951020	00104	CE 	1995	10	20	95ZZZX5770 	1	19950807	G	2720	151350021	SUPPORT ASSY 			CESSNA	337 	T337B 	2075707	CE 										INBD RUD BAR	CRACKED 	B		A	VRQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	471DF		384 			337M0246				DURING NR 2 PROGRESSIVE INSPECTION, THE MOUNT WAS NOTICED FLEXING DURING RUDDER APPLICATION. THIS BRACKET HAD BEEN REPL	ACED FOR THE SAME REASON DURING THE ANNUAL ON 5-94. THIS HAS BEEN AN ONGOING PROBLEM WITH ACFT, APPROXIMATELY 6 CHANGES	, 13 ACFT IN THE FLEET.				1	H	7	2 	3O				A6CE 					 
1995102000105	19951020	00105	CE 	1995	10	20	95ZZZX5771 	1	19950921	G	2510	9653407367	SEAT 			BEECH 	58 	58P 	1152744	CE 										SEAT LATCH	PIN BROKEN 	B			FC6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	145Z	5226 				TJ289				SEAT LATCH PIN LOCKING PIN BROKEN. LOCK PIN SECURES LATCH AND SPRING TO ASSURE SEAT IS LOCKED IN PLACE.						1	L	7	2 	3O				A23CE 					 
1995102000106	19951020	00106	CE 	1995	10	20	95ZZZX5772 	1	19950920	G	7810		EXHAUST RISER 			BEECH 	60 	B60 	1153605	CE 										EXHAUST SYSTEM	HOLE BLOWN 	B			FC6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	234RD	826 				P566				EXHAUST RISER FROM CYLINDER BLOWN THROUGH ON 2 STACKS. ONE STACK RISER HAS APPROXIMATELY 1.50 INCH HOLE AND ONE WAS ABO	UT .50 INCH. HOLES CAUSED FROM EXHAUST HEAT DETERIORATION.					1	L	7	2 	3O				A12CE 					 
1995102000107	19951020	00107	EA 	1995	10	20	95ZZZX5773 	2	19950905	G	8520	LW75061	ROD BOLT 								LYC 	O360 	O360A1A 	41514	EA 					CON ROD	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	23										IT IS NOT UNCOMMON TO FIND THE LONGER LW 75061 ROD BOLTS THAT ARE CALLED OUT IN THE LATEST O-360 TEXTRON LYCOMING PARTS 	BOOK MIS-MATCHED WITH THE CONNECTING RODS. THE EARLIER RODS, SUCH AS THE 74502 ROD, REQUIRE A SHORTER CONNECTING ROD BO	LT (LW 74644). UNFORTUNATELY, DUE TO THE NECKED-DOWN DESIGN OF THE SHANK OF THE BOLT, THE 40 FEET/POUND TORQUE VALUE CA	N BE ACHIEVED WITH EITHER BOLT; BUT, WITH THE WRONG BOLT WHICH IS LONGER, ONLY ABOUT 80 PERCENT OF THE THREADS IN THE CO	NNECTING ROD NUT ARE MAKING CONTACT WITH THE BOLT THREADS.							3	O			E286				 
1995102000108	19951020	00108	EU 	1995	10	20	95ZZZX5774 	1	19950920	G	2912	M060024	FILTER 		96038001151 	PILATS	PC12 	PC12 	7090550	EU 										POWER PACK	CLOGGED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	74BE	172 				115				DURING 100-HOUR INSPECTION, FOUND HYDRAULIC FILTER BYPASS INDICATOR TRIPPED. RESET BUTTON, CYCLED GEAR, AND BUTTON TRIP	PED AGAIN. REPLACED FILTER TO FIX PROBLEM. OLD FILTER WAS INSPECTED FOR CONTAMINATION, BUT NOTHING VISIBLE WAS FOUND. 	 FILTER COULD BE BLOWN THROUGH USING MOUTH. FILTER MAY HAVE BEEN PARTIALLY RESTRICTED BY MICROSCOPIC PARTICLES.				1	L	7	1 	3T			RT	A78EU 					 
1995102000109	19951020	00109	CE 	1995	10	20	95ZZZX5775 	1	19950928	G	2822	50389043	PUMP 			BEECH 	80 	65B80 	1152812	CE 										FUEL BOOST	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	15	131BA		361 		122U	LD297				PILOT WAS PRE-FLIGHTING AIRCRAFT AND NOTICED FUEL LEAKING FROM BOOST PUMP MOTOR VENT TUBE. SUSPECTED CAUSE WAS FAILED S	EAL BETWEEN PUMP AND MOTOR OR CRACKED CASE BETWEEN PUMP AND MOTOR.					1	L	7	2 	3O				3A20 					 
1995102000139	19951020	00139		1995	10	20	95ZZZX5776 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					74920					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000140	19951020	00140		1995	10	20	95ZZZX5777 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					26217					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000141	19951020	00141		1995	10	20	95ZZZX5778 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					16370					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000142	19951020	00142		1995	10	20	95ZZZX5779 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					64897					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995021000064	19950210	00064	SO 	1995	2	10	95ZZZX578 	2	19950111	G	8550		ELBOW 			BBAVIA	7 	7AC 	2110102	SW 	CONT 	A65 	A658 	17003	SO 					CRANKCASE	BOGUS PART 	D				K				NONE 				K	W		FLUID LOSS 	INADEQUATE Q C 		IN	INSP/MAINT 	1			GL	23	84304		1 			2999	3658558			OIL PRESSURE LINE LEAKING AT 45 DEGREES, ELBOW EXITING THE CRANKCASE. REPLACED AUTOMOBILE FITTING WITH MS20823-4D FITTI	NG WITH A NR 60 RESTRICTOR. ALSO, REPLACED OIL PRESSURE LINE FROM CRANKCASE TO FIREWALL.					1	H	7	1 	3O	3	O		A759 	E205				 
1995102000143	19951020	00143		1995	10	20	95ZZZX5780 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					15683					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000144	19951020	00144		1995	10	20	95ZZZX5781 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					19198					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000145	19951020	00145		1995	10	20	95ZZZX5782 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					24630					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000146	19951020	00146		1995	10	20	95ZZZX5783 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					28817					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000147	19951020	00147		1995	10	20	95ZZZX5784 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					31342					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000148	19951020	00148		1995	10	20	95ZZZX5785 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					38802					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000149	19951020	00149		1995	10	20	95ZZZX5786 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					40273					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000150	19951020	00150		1995	10	20	95ZZZX5787 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					58821					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000151	19951020	00151		1995	10	20	95ZZZX5788 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					60336					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000152	19951020	00152		1995	10	20	95ZZZX5789 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					63037					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000153	19951020	00153		1995	10	20	95ZZZX5790 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					63546					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000154	19951020	00154		1995	10	20	95ZZZX5791 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					66600					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000155	19951020	00155		1995	10	20	95ZZZX5792 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					68200					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000156	19951020	00156		1995	10	20	95ZZZX5793 	4	19951002	G	2562	ELT1	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					99738					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000157	19951020	00157	SO 	1995	10	20	95ZZZX5794 	1	19950818	G	3260		DOWNLOCK SWITCH 			PIPER 	PA31 	PA31350 	7103110	SO 										MLG	REQUIRED LUBE 	A			BSYA	O				OTHER 				N			FALSE WARNING 			NR	NOT REPORTED 	1			GL	07	35871					318052123				SDF - RIGHT MAIN GEAR HAS NO DOWN AND LOCK INDICATION. CLEANED AND LUBED DOWN AND LOCK SWITCH. OPS CHECKS GOOD.						1	L	7	2 	3O				A20SO 					 
1995102000160	19951020	00160		1995	10	20	95ZZZX5797 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A23767					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000161	19951020	00161		1995	10	20	95ZZZX5798 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C15025					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000162	19951020	00162		1995	10	20	95ZZZX5799 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C33117					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995021000066	19950210	00066	GL 	1995	2	10	95ZZZX580 	3	19950117	G	6111	B3018S2	PITCH ROD 			MTSBSI	MU2 	MU2B35 	5780411	CE 						HARTZL	HCB3T	HCB3TN5 	GL 	PROPELLER	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	3330K		1901 			551		BV2109		THE ROD FAILED AT THE SPLIT RETAINER INDICATING THE TUBE IS NOT STRONG ENOUGH TO WITHSTAND SPRING PRESSURE. SUBMITTER R	ECOMMENDS ALL HARTZELL PROPS WITH THE OLD STYLE ROD BE CHANGED WITH THE NEW STRONGER ROD, PN C-1948, IAW HARTZELL SB 177	.				1	H	7	2 	3T			RT	A10SW 		6	C	P15EA	 
1995102000163	19951020	00163		1995	10	20	95ZZZX5800 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					10736					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000164	19951020	00164		1995	10	20	95ZZZX5801 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					13618					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000165	19951020	00165		1995	10	20	95ZZZX5802 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18119					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000166	19951020	00166		1995	10	20	95ZZZX5803 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18802					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000167	19951020	00167		1995	10	20	95ZZZX5804 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18819					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000168	19951020	00168		1995	10	20	95ZZZX5805 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					25125					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000169	19951020	00169		1995	10	20	95ZZZX5806 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13					29458					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000170	19951020	00170		1995	10	20	95ZZZX5807 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					32970					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000171	19951020	00171		1995	10	20	95ZZZX5808 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13					57321					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000172	19951020	00172		1995	10	20	95ZZZX5809 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					44984					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000173	19951020	00173		1995	10	20	95ZZZX5810 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13					46193					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000174	19951020	00174		1995	10	20	95ZZZX5811 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13					47211					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000175	19951020	00175		1995	10	20	95ZZZX5812 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					51360					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000176	19951020	00176		1995	10	20	95ZZZX5813 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					48703					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000177	19951020	00177		1995	10	20	95ZZZX5814 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					56835					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000178	19951020	00178		1995	10	20	95ZZZX5815 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					64121					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000179	19951020	00179		1995	10	20	95ZZZX5816 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13					72949					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000180	19951020	00180		1995	10	20	95ZZZX5817 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					93126					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000181	19951020	00181		1995	10	20	95ZZZX5818 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					95768					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000182	19951020	00182		1995	10	20	95ZZZX5819 	4	19951002	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					96717					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14, WHICH WAS MANDATED APRIL 21, 1986.																	 
1995102000183	19951020	00183	EA 	1995	10	20	95ZZZX5820 	2	19950727	G	7310	25244508	INJECTOR 	BENDIX 		PIPER 	PA28 	PA28R200 	7102811	SO 	LYC 	O360 	IO360C1C 	41514	EA 					MIXTURE STOP	SCREW MISSING 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	75139		853 		43621	28R7635269	L881951A			PILOT COMPLAINT OF A/C NOT STARTING. FOUND MIXTURE STOP SCREW MISSING ALLOWING MIX. CONTROL ARM TO GO BEYOND FULL RICH 	BACK TO I.C.O. MIXTURE CONTROL STRIKES SAFETY WIRE ON STOP CAUSING IT TO BREAK. RECOMMEND DIFFERENT METHOD OF SAFETYIN	G.				1	L	7	1 	3O	3	O		2A13 	1E10				 
1995102000184	19951020	00184	SO 	1995	10	20	95ZZZX5821 	1	19950625	G	3222	6705403	TRUNNION 			PIPER 	PA32 	PA32R301T 	7103220	SO 										NLG DRAG LINK	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	3577D	2014 				32R8029036				WHEN MOVING AIRCRAFT, NOSE GEAR TRUNNION BROKE FREE OF DRAG LINKS AND STARTED TO COLLAPSE. TRUNNION FAILED AT DRAG LINE	 ATTACH BOSS.					1	L	7	1 	3O				A3SO 					 
1995102000185	19951020	00185	EA 	1995	10	20	95ZZZX5822 	2	19950919	G	8530		CYLINDER 			PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	IO540C4B5 	41532	EA 					NR 6	CRACKED 	D	S			K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	13	2471M		980 		CP31039	277954065				THE PILOT REPORTED LOW EGT ON THE LEFT ENGINE. A VISUAL INSPECTION OF NR 6 CYLINDER WHERE THE EGT PROBE IS LOCATED REVE	ALED A CRACK AT THE LOWER SPARK PLUG HOLE. AFTER REMOVING THE CYLINDER, FOUND THE CRACK WENT FROM SPARK PLUG HOLE TO SP	ARK PLUG HOLE WITH MISSING METAL AROUND THE EXHAUST VALVE.				1	L	7	2 	3O	3	O		1A10 	1E4				 
1995102000186	19951020	00186	SO 	1995	10	20	95ZZZX5823 	1	19950919	G	2710	62701127	CONTROL CABLE 			PIPER 	PA34 	PA34220 	 	SO 										WS 70.5	WORN 	B		A	ECPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	9216E	3408 				3448012				LEFT AND RIGHT FORWARD AILERON CABLES ARE BEING WORN BY THE PULLEY AT WS 70.5. THE PULLEY AT THIS STATION CARRIES NO LO	AD FROM THE CABLE TENSION. IT APPEARS THAT IN-FLIGHT VIBRATION IS CUTTING THE CABLE IN HALF. NO PULLEYS HAVE BEEN FOUN	D FROZEN OR DAMAGED. OPERATOR HAS FLEET OF 5 AND PROBLEM IS APPARENT IN ALL.				1	L	7	2 	3O			 	A7SO 					 
1995102000187	19951020	00187	CE 	1995	10	20	95ZZZX5824 	1	19950920	G	5260	08119441	STEP 			CESSNA	310 	310R 	2074245	CE 										CABIN ENTRY	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	5071J	3116 				310R0151				DURING ANNUAL INSPECTION, FOUND CABIN ENTRY STEPS (2 EACH) CRACKED AT UPPER ATTACH HOLE. ONE STEP WAS CRACKED 3.5 INCHE	S LONG, THE OTHER STEP ONLY THE THICKNESS OF THE CASTING SHOWED SIGNS OF CRACKING. SUGGEST SHORT EDGE DISTANCE OF TOP H	OLE CAUSED CRACKING.				1	L	7	2 	3O				3A10 					 
1995102000188	19951020	00188	CE 	1995	10	20	95ZZZX5825 	1	19950920	G	5260	0819441	STEP 			CESSNA	310 	310P 	2074238	CE 										CABIN ENTRY	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	5872M	3781 				310P0172				DURING ANNUAL INSPECTION OF ANOTHER LIKE MODEL AIRCRAFT, CRACKS WERE NOTED ON CABIN ENTRY STEPS. LOOKING FOR A TREND, T	HIS ACFT WAS INSPECTED IN THE SAME LOCATION AND ONE STEP WAS FOUND CRACKED ALSO. CRACK ORIGIN WAS AT TOP ATTACH HOLE AN	D EXTENDED TO BOTTOM HOLE. SUBMITTER SUGGESTS SHORT EDGE DISTANCE OF TOP HOLE CAUSED CRACKING.				1	L	7	2 	3O				3A10 					 
1995102000189	19951020	00189	CE 	1995	10	20	95ZZZX5826 	1	19950918	G	7810	99103013	EXHAUST STACK 			CESSNA	402 	402B 	207590P	CE 										LT INBD EXHAUST	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	660W					402B0828				WHILE CHANGING TURBO HEADER ASSY, FOUND LT INBD EXHAUST PIPE FLANGE CRACKED UNDER CLAMP. REMOVED PIPE. CLOSER INSPECTI	ON REVEALED BELLMOUTH WAS ALSO CRACKED OVER HALF WAY AROUND. REPLACED PIPE. SUBMITTER SUGGESTS CLOSER INSPECTIONS OR L	IMIT TIME IN SERVICE.				1	L	7	2 	3O				A7CE 					 
1995102000190	19951020	00190	CE 	1995	10	20	95ZZZX5827 	1	19950918	G	8120	99103014	HEADER ASSY 			CESSNA	402 	402B 	207590P	CE 	CONT 	O520 	TSIO520E 	17040	SO 					TURBO	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	660W					402B0828				TRANSIENT AIRCRAFT REPORTED NO BOOST. INSPECTED TURBO, UNABLE TO ROTATE IMPELLER. REMOVED TURBO, FOUND INTERNAL DIVIDE	R OF HEADER ASSY BROKEN APART ENTIRE LENGTH. PIECE OF DIVIDER HAD BROKEN OFF AND JAMMED TURBO IMPELLER. HEADER ASSY WA	S ALSO BULGED AND RUPTURED IN REAR. REPLACED HEADER ASSY. REMOVED BROKEN OFF PIECES FROM TURBO CAVITY. SUBMITTER SUGG	ESTS CLOSER INSPECTION OF EXHAUST SYSTEM OR LIMITING TIME IN SERVICE.			1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995102000191	19951020	00191	CE 	1995	10	20	95ZZZX5828 	1	19950918	G	7810	99102962	SLIP JOINT 			CESSNA	402 	402B 	207590P	CE 										EXHAUST	SEIZED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	660W					402B0828				WHILE CHANGING TURBO HEADER ASSY AND AFT EXHAUST PIPE, UNABLE TO LINE UP DUE TO SEIZED SLIP JOINTS. REMOVED SLIP JOINTS	, FOUND INTERNALS BULGED AND DISTORTED. REPLACED SLIP JOINTS. SUBMITTER SUGGESTS CLOSER INSPECTIONS OR LIMIT TIME IN 	SERVICE.				1	L	7	2 	3O				A7CE 					 
1995102000192	19951020	00192	SO 	1995	10	20	95ZZZX5829 	1	19950912	G	2842	6810102	SENDER 	STWARNER 		PIPER 	PA32 	PA32260 	7103206	SO 										LT TIP TANK	FLOAT DETACHED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	4806S	4085 				321190				LEFT FUEL TIP TANK GAUGE READ FULL AT ALL TIMES. REMOVED SENDING UNIT. FLOAT WAS MISSING AND FOUND INSIDE TANK. INSTA	LLED SERVICE KIT NR 766-240 REPLACING SENDER AND GAUGE.					1	L	7	1 	3O				A3SO 					 
1995021000069	19950210	00069	CE 	1995	2	10	95ZZZX583 	1	19950105	G	2750	12163Y6331	FLEXSHAFT 			BEECH 	58 	58P 	1152744	CE 										RT FLAP	SEPARATED 	B			BYER	O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			EA	09	701JK	46 				TJ200				CRW - ON FINAL, PILOT SELECTED APPROACH FLAPS AND AIRCRAFT ROLLED HARD RIGHT. PILOT RECOVERED WITH AILERONS AND SELECTI	NG FLAPS UP. INSPECTION FOUND RIGHT FLAP FLEXSHAFT CABLE DRIVE END HAD SEPARATED FROM THE CABLE ON THE INBOARD END. CA	USE UNKNOWN. CABLE RETURNED TO BEECHCRAFT FOR EVALUATION.				1	L	7	2 	3O				A23CE 					 
1995102000193	19951020	00193	SO 	1995	10	20	95ZZZX5830 	1	19950629	G	5751	6237300	DOUBLER 			PIPER 	PA32 	PA32260 	7103206	SO 										AIL RT OB HINGE	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	4768S	1650 				321176				DURING ANNUAL INSPECTION, BOTH OUTBOARD AILERON HINGE DOUBLERS WERE FOUND CRACKED ABOUT ONE-HALF THE LENGTH OF AILERON H	INGE. AILERON HAS EXCESSIVE LOAD FROM BALANCE WEIGHT ON OUTER HINGE.					1	L	7	1 	3O				A3SO 					 
1995102000194	19951020	00194	SO 	1995	10	20	95ZZZX5831 	1	19950629	G	5751	6237301	DOUBLER 			PIPER 	PA32 	PA32260 	7103206	SO 										AIL LT OB HINGE	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	4768S	3338 				321176				DURING ANNUAL INSPECTION, BOTH OUTBOARD AILERON HINGE DOUBLERS WERE FOUND CRACKED ABOUT ONE-HALF THE LENGTH OF AILERON H	INGE. AILERON HAS EXCESSIVE LOAD FROM BALANCE WEIGHT ON OUTER HINGE.					1	L	7	1 	3O				A3SO 					 
1995102000195	19951020	00195	SO 	1995	10	20	95ZZZX5832 	1	19950629	G	5751	6237301	DOUBLER 			PIPER 	PA32 	PA32260 	7103206	SO 										AIL LT OTBD HING	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	7737J	1650 				321140				DURING ANNUAL INSPECTION, LT OUTBOARD AILERON HINGE DOUBLER WAS FOUND CRACKED ABOUT ONE-HALF THE LENGTH OF AILERON HINGE	. AILERON HAS EXCESSIVE LOAD FROM BALANCE WEIGHT ON OUTER HINGE.					1	L	7	1 	3O				A3SO 					 
1995102000196	19951020	00196	CE 	1995	10	20	95ZZZX5833 	1	19950901	G	2730	05130631	BRACKET 			CESSNA	172 	172H 	2072424	CE 										ELEV BELLCRANK	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	3784R	2130 				17255584				DURING 100-HOUR INSPECTION, BRACKET WAS FOUND CRACKED AT FORWARD AND AFT MOUNT FLANGES AND FORWARD LOWER MOUNT FLANGE. C	RACKS WERE ALSO FOUND RADIATING OUT FROM FORWARD FLANGE RIVET HOLES. CESSNA'S REPLACEMENT PART, 0513063-3, IS HEAVIER G	AUGE. MATERIAL WITH MORE FLANGE SPACE FOR RIVETING. SUBMITTER RECOMMENDS CLOSER ATTENTION DURING INSPECTIONS WITH REPL	ACMENT AT FIRST SIGN OF FATIGUE. BRACKET IS UNDER CREW FLOOR BELOW FUEL SELECTOR KNOB.			1	H	7	1 	3O			NT	3A12 					 
1995102000197	19951020	00197	CE 	1995	10	20	95ZZZX5834 	1	19950928	G	3230	3682001117	RETRACT ROD 			BEECH 	35 	V35B 	1151548	CE 										NLG AFT	NUTS LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	13	33VH	1824 				D9803				DURING AN ANNUAL INSPECTION, THE MECHANIC NOTED THE NOSE GEAR DOWNLOCK TENSION WAS ABNORMALLY HIGH. INVESTIGATION REVEA	LED THE TWO JAM NUTS WERE LOOSE ALLOWING THE ROD TO TURN SO AS TO LENGTHEN. SUBMITTER STATED CAREFUL ATTENTION SHOULD B	E PAID TO PROPERLY TIGHTENING JAM NUTS AFTER RIGGING VERIFYING NUT TIGHTNESS DURING INSPECTION. P/N AN316-6R AND P/N AN	316-7L.			1	L	7	1 	3O				3A15 					 
1995102000198	19951020	00198	CE 	1995	10	20	95ZZZX5835 	1	19950916	G	5753	0523920	BUSHING 			CESSNA	172 	172N 	2072434	CE 										LT OB FLAP TRACK	FAILED 	D				O				OTHER 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			NE	01	1449E	6066 				17271005				DURING ROUTINE FLIGHT, PILOT REPORTED A LOUD POP WHEN HE MOVED THE FLAP HANDLE TO RAISE THE FLAPS. THE RT FLAP RETRACTE	D, THE LEFT BOUND-UP AND WAS AT ALMOST 30 DEGREES. A SAFE LANDING WAS PERFORMED. INSPECTED THE FLAP SYSTEM AND FOUND W	HAT APPEARED TO BE THE LEFT OUTBOARD FLAP BUSHING HAD FAILED. THIS CAUSED THE FLAP TO BIND CAUSING DAMAGE TO FLAP, FLAP	 TRACK, AND BELLCRANK. LOG BOOK RESEARCH CONDUCTED. THESE BUSHINGS HAVE NEVER BEEN CHANGED.			1	H	7	1 	3O			NT	3A12 					 
1995102000199	19951020	00199	CE 	1995	10	20	95ZZZX5836 	1	19950920	G	2460		ELECTRIC SYS 			CESSNA	337 	T337G 	2075726	CE 										AVION COMP	FAILED 	D				O				OTHER 				H			ELECT. POWER LOSS-50 PC 			CR	CRUISE 	1			NM	03	245	1547 				P3370219				AIRCRAFT SUFFERED A SHORT-TERM, COMPLETE ELECTRICAL SYSTEM FAILURE WHILE IN IFR CONDITIONS ON A NIGHT FLIGHT. ELECTRICA	L SYSTEM BEGAN FUNCTIONING NORMALLY AGAIN AFTER AIRCRAFT RETURNED TO NON-PRECIP. VFR. SUSPECT CAUSE IS MOISTURE ENTERIN	G AVIONICS COMPARTMENT. SUBMITTER RECOMMENDS BETTER SEAL FOR AVIONICS COMPARTMENT HATCHES.				1	H	7	2 	3O				A6CE 					 
1995102000423	19951020	00423	CE 	1995	10	20	95ZZZX5837 	1	19950925	G	7830	202000327	FORMER 		225008501 	BEECH 	MU300 	400BEECH 		CE 										STANG FAIRING	CRACKED 	B		A	PAIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	908R	758 				RK44				LEFT ENGINE, OUTBOARD. THE FORWARD ATTACH FORMER CRACKED AT THE 2 MOUNT ATTACH HOLES. THIS ALLOWED THE LEADING EDGE OF	 THE STANG FAIRING TO FOLD BACK AND BREAK OFF. THE AIRCRAFT LANDED SAFELY. SUBMITTER STATED AFTER INSPECTING A SECOND 	BEECH JET, 2 MORE FORMERS HAVE BEEN FOUND CRACKED.				2	H	7	2 	4F			RT	A16SW 					 
1995102000424	19951020	00424	NE 	1995	10	20	95ZZZX5838 	2	19950821	G	7250	310940101	BLADE 			DOUG 	DC3 	DC3C 	3021457	WP 	PWA 	PT6 	PT6A67R 	52043	NE 					TURBINE	CRACKED 	H		A	BG7P	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	142Z	1534 				20494	PCE106136			WHILE PERFORMING AN ENGINE HOT SECTION INSPECTION, THE COMPRESSOR TURBINE WAS FOUND TO HAVE ALL 52 BLADE TIP TO SEGMENT 	CLEARANCES WORN BEYOND SERVICEABLE LIMITS. ONE BLADE WAS ALSO FOUND CRACKED 50 PERCENT THROUGH CHORD-WISE. SENT TURBIN	E WHEEL ASSY TO P & WC FOR RE-BLADING AND BALANCING. PERFORMED THE REQUIRED HOT SECTION REPAIRS.				2	L	7	2 	4R	4	T		A669 	E26NE				 
1995102000425	19951020	00425		1995	10	20	95ZZZX5839 	4	19950907	G	2210	SPZ500	AUTOPILOT SYSTEM	SPERRYFLT 		CESSNA	441 	441 	2076020	CE 										FLT DIR COMP	PINS OPEN 	B		A	DJFR	O				OTHER 				F			FLT CONT AFFECTED 			CR	CRUISE 	1			EA	23	1210Z					4410339				AIRCRAFT PORPOISES VIOLENTLY UPON AUTOPILOT COUPLED APPROACH TO AIRPORT WITH HILLY TERRAIN. TROUBLESHOT SYSTEM AND FOUN	D OPEN CONNECTION BETWEEN PINS 89 AND 92 ON FLIGHT DIRECTOR COMPUTER PLUG PL67. JUMPERING PINS PER CESSNA DRAWING NR 94	19120 CORRECTED PROBLEM, SAW NO EVIDENCE THAT THESE PINS WERE JUMPERED WHEN DELIVERED FROM THE FACTORY. OTHER AIRCRAFT 	COULD BE MANUFACTURED WITH THIS DEFECT. NOTE: THIS M OR D REPLACES THE M OR D FILED 8-30-95.			1	L	7	2 	3T			RT	A28CE 					 
1995021000070	19950210	00070	SO 	1995	2	10	95ZZZX584 	2	19950113	G	8530	648008	PISTON RING 								CONT 	O520 	IO520BB 	17032	SO 					CYLINDER	STICKING 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11							285909R			THIS ENGINE HAD TEST TIME ONLY ON A FACTORY REMANUFACTURED ENGINE. ALL SIX BOTTOM PISTON RINGS WERE EMBEDDED WITH ALUMI	NUM CAUSING RINGS TO 'STICK'. THIS ALSO CAUSED THE PISTONS TO REJECT.										3	O			E5CE				 
1995102000426	19951020	00426	SW 	1995	10	20	95ZZZX5840 	1	19950801	G	2810	5630308	CELL 	GOODYEAR 	BTC67 	GULSTM	690TP 	690A 	0141722	SW 										LT FWD INBD	CRACKED 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	23	333CA	3905 			735142	11136				WHEN PILOT ARRIVED AT HANGAR FOR A FLIGHT, HE NOTICED A STEADY STREAM OF FUEL COMING FROM A COUPLE OF DRAIN HOLES IN THE	 BOTTOM OF THE LT WING INBOARD OF THE ENGINE NACELLE. PILOT REPORTED HE HAD FILLED TANKS THE NIGHT BEFORE. A/C TURNED 	OVER TO MAINTENANCE. REMOVED THE FRONT 2 CELLS INBOARD OF THE ENGINE. FOUND ONE CELL WITH A CRACK IN THE NIPPLE FOR TH	E VENT INTERCONNECT. REPLACED CELL WITH NEW. NO LEAKS NOTED. THIS CELL WAS ORIGINAL WHEN THE A/C WAS MANUFACTURED. T	HESE CELLS HAVE TO BE REMOVED TO PERFORM AD94-04-14 (SPAR INSP) WHICH WAS ACCOMPLISHED 24 MONTHS PRIOR. SUBMITTER STATE	D REMOVAL AND INSTALLATION OF THESE CELLS EVERY 3 YEARS INCREASES THE CHANCE OF THESE PROBLEMS.	1	H	7	2 	3T				2A4 					 
1995102000427	19951020	00427	WP 	1995	10	20	95ZZZX5841 	1	19950821	G	7810	310802701	EXHAUST DUCT 			DOUG 	DC3 	DC3C 	3021457	WP 	PWA 	PT6 	PT6A67R 	52043	NE 					DRAIN BOSS	CRACK 	H			BG7P	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	142Z	1534 				20494	PCE16136			A 1 INCH CRACK WAS FOUND IN THE WELD AREA OF THE TURBINE EXHAUST DUCT DRAIN LOCATED AT THE 6 O'CLOCK POSITION. OIL HAD 	PUDDLED INSIDE THE EXHAUST DUCT DUE TO A FAILURE OF THE POWER TURBINE SHAFT NR 3 BEARING SEAL. DUE TO THE HIGH TEMPERAT	URE, THE OIL COKED AND RETAINED THE LATENT HEAT LONGER THAN THE SURROUNDING AREA. THIS CONCENTRATED HEAT IS SUSPECTED T	O HAVE CAUSED A THERMAL STRESS THAT INDUCED THE CRACK. THE AFFECTED ASSEMBLY WAS SENT TO P & WC FOR REPAIR.			2	L	7	2 	4R	4	T		A669 	E26NE				 
1995102000428	19951020	00428	WP 	1995	10	20	95ZZZX5842 	2	19950918	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		3556 			1233151952		P70128			PART REMOVED AT SCHEDULED INSPECTION, FOUND CRACKED AT FLANGE. SB TPE331-72-0840 AUTHORIZES INSTALLATION OF THIS PART T	O INCREASE SEAL PLATE FLANGE PRESSURE AGAINST FIRST STAGE ROTOR. INCREASED PRESSURE CAUSES CRACKING AT SEAL FLANGE. TH	IS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT = 20,000 CYCLES. SUBMITTER STATES THIS IS THE 14TH SEAL PLATE FOUN	D CRACKED. PART TOTAL CYCLES, 3,550.								4	T			E4WE				 
1995102000429	19951020	00429	WP 	1995	10	20	95ZZZX5843 	2	19950907	G	7250	3103893	SEAL 		31033155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		3556 			1233151957		P70129			DURING SCHEDULED INSPECTION, FOUND SEAL CRACKED AT FLANGE. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE I	NCREASED TENSION AGAINST THE FIRST STAGE ROTOR. THIS INCREASED TENSION RESULTS IN CRACKING AT THE SEAL FLANGE. THIS IS	 A CRITICAL LIFE-LIMITED COMPONENT. LIFE LIMIT - 20,000 CYCLES. SUBMITTER STATES THIS IS THE 13TH SEAL FOUND CRACKED. 	 PART TOTAL CYCLES, 3,550.								4	T			E4WE				 
1995102000430	19951020	00430	WP 	1995	10	20	95ZZZX5844 	2	19950918	G	7250	31038391	SEAL 		31035152 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		9724 			9233151477		P70023C			DURING SCHEDULED INSPECTION, FOUND SEAL FLANGE CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART WITH A SHIM TO 	INCREASE TENSION AGAINST 1ST STAGE ROTOR. INCREASE TENSION CAUSES CRACKING AT THE SEAL FLANGE. THIS IS A CRITICAL LIFE	-LIMITED COMPONENT. LIFE LIMIT IS 20,000 CYCLES. SUBMITTER STATES THIS IS THE 15TH CRACKED SEAL PLATE REPORTED BY THIS	 FACILITY. SUGGEST ALLIED SIGNAL DETERMINE/CORRECT CAUSE. PART TOTAL CYCLES, 9,933.								4	T			E4WE				 
1995102000431	19951020	00431	EA 	1995	10	20	95ZZZX5845 	1	19951010	G	5753	7570002003	FOREFLAP 			DHAV 	DHC7 	DHC7102 	2802708	EA 										LT WING	CORRODED 	B			WVER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	89068				EH008761	088				ON D-INSPECTION OF FLIGHT CONTROLS OF LEFT FOREFLAP, FOUND CORROSION ON BOTTOM STR 12 AND STR 14 WITH BORESCOPE, STA YW2	42.17 TO YW257.35. FOREFLAP PANELS ARE NOT REQUIRED TO BE REMOVED ON INSPECTION. SUBMITTER STATED THEY NEED REMOVAL FO	R INSPECTION OF CORROSION OF BOTTOM SKIN AND STRINGERS.				2	H	7	4 	4T				A20EA 					 
1995102000432	19951020	00432	EA 	1995	10	20	95ZZZX5846 	1	19951010	G	5753	7570002004	FOREFLAP 			DHAV 	DHC7 	DHC7102 	2802708	EA 										RT WING	CORRODED 	B			WVER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	89068	14952			EH008661	088				ON D-INSPECTION OF FLIGHT CONTROLS, FOUND A HINGE ARM WITH CORROSION AND, WITH THE OTHER FLAP PANELS OPEN, FOUND CORROSI	ON AROUND PANEL NUTPLATES, STA YW367.90 TO STA YW423.30. SUBMITTER STATES PANELS NEED REMOVAL AT INSPECTION OF FOREFLAP	.				2	H	7	4 	4T				A20EA 					 
1995102000433	19951020	00433	EA 	1995	10	20	95ZZZX5847 	1	19951010	G	3213	150113	STRUT PIN 			DHAV 	DHC7 	DHC7102 	2802708	EA 										LT MLG	CORRODED 	B			WVER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	89068	14952			584	088				ON A D-INSPECTION, REPLACED HARDWARE FOR UPPER DRAG STRUT AND WHEN STRUT PINS WERE REMOVED, THEY HAD CORROSION AND PITTI	NG. SUBMITTER STATED WHEN HARDWARE IS SHOWING CORROSION, PINS NEED TO BE INSPECTED FOR CORROSION.					2	H	7	4 	4T				A20EA 					 
1995102000434	19951020	00434	EA 	1995	10	20	95ZZZX5848 	1	19951010	G	3213	150113	STRUT PIN 			DHAV 	DHC7 	DHC7102 	2802708	EA 										LT MLG	CORRODED 	B			WVER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	89068	14952			571	088				ON A D-INSPECTION, REPLACED HARDWARE FOR UPPER DRAG STRUT AND WHEN STRUT PINS WERE REMOVED, THEY HAD CORROSION AND PITTI	NG. SUBMITTER STATED WHEN HARDWARE IS SHOWING CORROSION, PINS NEED TO BE INSPECTED FOR CORROSION.					2	H	7	4 	4T				A20EA 					 
1995102000435	19951020	00435	EA 	1995	10	20	95ZZZX5849 	1	19951010	G	5753	7570002004	FOREFLAP 			DHAV 	DHC7 	DHC7102 	2802708	EA 										HINGE	ARM CORRODED 	B			WVER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	89068	14952			EH008661	088				ON D-INSPECTION OF FLIGHT CONTROLS, FOUND CORROSION ON INBD FORFLAP HINGE ARM UNDER PANEL COVER. PANELS ARE NOT REQUIRE	D TO BE REMOVED ON INSPECTION. PANELS NEED REMOVAL FOR CORROSION INSPECTION.					2	H	7	4 	4T				A20EA 					 
1995021000071	19950210	00071	SO 	1995	2	10	95ZZZX585 	2	19950113	G	8530	646283	VALVE 								CONT 	O520 	IO520BA 	17032	SO 					CYLINDER	EXCESS WEAR 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	11							807022R			INSPECTION FOUND 2 EACH, PN 646283, VALVES OUT OF A FACTORY REMANUFACTURED ENGINE WITH TEST CELL BREAK-IN TIME ONLY. (L	ESS THAN 3 HOURS). THE VALVE STEM ENDS WERE THE ROCKER ARM CONTACTS, THE VALVES WERE WORN EXCESSIVELY. THE VALVES WERE	 PITTED AND CONCAVE.									3	O			E5CE				 
1995102000436	19951020	00436	EA 	1995	10	20	95ZZZX5850 	1	19951010	G	5753	7570002004	FOREFLAP 			DHAV 	DHC7 	DHC7102 	2802708	EA 										RT WING	CORRODED 	B			WVER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	89068	14952			EH008661	088				ON D-INSPECTION, NDT DEBOND CHECK OF RIGHT FOREFLAP FOUND CORROSION OF STR 14 AT STA YW257.35. SUBMITTER STATED REAR FO	REFLAP PANELS NEED REMOVAL AT INSPECTION AND INSPECT FOR CORROSION OF BOTTOM SKIN AND HINGE AREA BY BORECOPE AND DEBOND 	INSPECTIONS.				2	H	7	4 	4T				A20EA 					 
1995102000440	19951020	00440	CE 	1995	10	20	95ZZZX5854 	1	19950727	G	3244		TIRE 			LEAR 	35 	35LEAR 	5170600	CE 										MLG	FAILED 	A			BSYA	O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			GL	07	4358N					065				BLEW NR 3 TIRE ON TAKEOFF OUT OF DENVER. LANDED IN BURBANK, NO PROBLEM. CHANGED BOTH NR 3 AND NR 4 TIRES AN WHEEL ASSY	S.					2	L	7	2 	4F				A10CE 					 
1995102000441	19951020	00441	NM 	1995	10	20	95ZZZX5855 	1	19950922	G	5314	65C33023	KEEL BEAM CHORD 			BOEING	727 	727231 	1384079	NM 										FS 990 STR 29R	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	370PA	26579				22542				INSPECTION FOUND CORROSION/CRACK 8 INCHES LONG, BS 990, STR 29R, AT RADIUS OF KEEL BEAM CHORD. SUSPECT WATER ENTRAPMENT	. SUBMITTER SUGGESTS TO INSPECT AND APPLY CORROSION INHIBITOR.					2	L	7	3 	4F				A3WE 					 
1995102000442	19951020	00442	CE 	1995	10	20	95ZZZX5856 	1	19950921	G	2931	P500	GAUGE 			BEECH 	200 	200BEECH 	1152920	CE 										ACCUM PRESS	FAILED 	B			LX5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	971LL	765 				BB572				THIS GAUGE IS PART OF STC SA4378WP AVIADESIGN, INC., HYDRAULIC LANDING GEAR SYSTEM. GAUGE FOUND PEGGED ON HIGH SIDE. A	FTER RELEASING PRESSURE, GAUGE DROPPED TO A MINIMUM READING OF 800 P.S.I.G. SUBMITTER RECOMMENDS A BETTER QUALITY GAUGE	 BE USED IN SYSTEM.				1	L	7	2 	4T				A24CE 					 
1995102000443	19951020	00443	CE 	1995	10	20	95ZZZX5857 	1	19950825	G	2931	P500	GAUGE 			BEECH 	200 	B200 	1152922	CE 										ACCUM PRESS	FAILED 	B			LX5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	961LL	268 				BB1139				THIS GAUGE IS PART OF STC-5A4378WP AVIADESIGN, INC., HYDRAULIC LANDING GEAR RETRACTION SYSTEM. GAUGE FOUND PEGGED ON HI	GH SIDE. FOUND ANOTHER GAUGE WITH SAME SYMPTOM, IT HAD INTERNAL FAILURE. SUBMITTER RECOMMENDS A BETTER QUALITY GAUGE B	E USED IN SYSTEM.				1	L	7	2 	4T				A24CE 					 
1995102000444	19951020	00444	CE 	1995	10	20	95ZZZX5858 	1	19950825	G	2931	P500	GAUGE 			BEECH 	200 	200BEECH 	1152920	CE 										ACCUM PRESS	FAILED 	B			LX5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	981LL	371 				BB602				THIS GAUGE IS PART OF STC-SA4378WP. AVIADESIGN, INC., HYDRAULIC LANDING GEAR RETRACTION SYSTEM. GAUGE FAILED INTERNALL	Y - CONNECTING ARM EYELET BROKE OFF CAUSING NEEDLE TO SPRING LOAD TO MAXIMUM INDICATION. SUBMITTER RECOMMENDS A BETTER 	QUALITY GAUGE BE USED IN SYSTEM.				1	L	7	2 	4T				A24CE 					 
1995102000445	19951020	00445	WP 	1995	10	20	95ZZZX5859 	2	19950831	G	7250	3103839	SEAL 		31035155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		6388 			1233151944		P70098C			DURING SCHEDULED INSPECTION, FOUND SEAL CRACKED AT FLANGE. SB TPE331-72-0840, AUTHORIZES INSTALLATION OF THIS PART TO I	NCREASE SEAL PLATE TENSION AGAINST 1ST STAGE ROTOR ASSEMBLY. INCREASED TENSION ON THE SEAL FLANGE RESULTS IN CRACKING A	T THE FLANGE EDGE. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING REVIEW CAUSE AND EFFECT OF DISCREPANCY. NOTE: THIS IS	 A CRITCAL LIFE-LIMITED COMPONENT. LIFE LIMIT = 20,000 CYCLES. THIS IS THE 11TH SEAL FOUND CRACKED. PART TOTAL CYCLE	S, 7,877.							4	T			E4WE				 
1995021000072	19950210	00072	SO 	1995	2	10	95ZZZX586 	2	19950116	G	8530	653445	CYLINDER 								CONT 	O520 	IO520* 	17032	SO 					ROCKER ARM BOSS	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11										ROCKER ARM BOSS HELI-COIL THREADS STRIPPED. HELI-COIL WAS LOOSE IN THREADS.											3	O			E5CE				 
1995102000446	19951020	00446	NM 	1995	10	20	95ZZZX5860 	1	19950922	G	5521	65245711	SPAR CAP 			BOEING	727 	727231 	1384079	NM 										LT ELV STA 99.79	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	370PA					22542				CORRODED UPPER REAR SPAR CAP ON LEFT ELEVATOR AT STA 99.79, STA 136.50, AND STA 173.21. SUSPECT WATER ENTRAPMENT. SUBM	ITTER SUGGESTS TO INSPECT AND RE-SEAL SEAMS.					2	L	7	3 	4F				A3WE 					 
1995102000447	19951020	00447	NM 	1995	10	20	95ZZZX5861 	1	19950922	G	5315		FLOOR BEAM 			BOEING	727 	727231 	1384079	NM 										FS 351-360	CORRODED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	370PA	36579				22542				CORROSION OF FLOOR BEAM CHORD ANGLE. LOCATED JUST AFT OF NR 1 DOOR OPENING. AREA SUBJECT TO WATER ENTRAPMENT. SUBMITT	ER SUGGESTS IF FLOOR IN DOOR OPENING HAS LARGE AMOUNT OF WATER PRESENT, INSPECT AND RE-SEAL AREA.					2	L	7	3 	4F				A3WE 					 
1995102000448	19951020	00448	EU 	1995	10	20	95ZZZX5862 	1	19950921	G	2710	1457001	ACTUATOR 			SOCATA	TBM 	TBM700 	8682000	EU 										LT AIL TRIM	PINS CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	969RF	97 				9				AILERON TRIM INDICATOR WOULD NOT INDICATE. FURTHER TROUBLESHOOTING REVEALED CORROSION IN AILERON TRIM ACTUATOR POWER WI	RE HARNESS CONNECTION. PINS IN CONNECTOR WERE CORRODED AND BRITTLE. REMOVED ACTUATOR, PN 14570001, AND INSTALLED NEW, 	IMPROVED ACTUATOR, PN 14570002. OPERATIONAL CHECK NORMAL.				1	L	7	1 	3T			RT	A60EU 					 
1995102000449	19951020	00449	CE 	1995	10	20	95ZZZX5863 	1	19951004	G	7830	14054503	ACTUATOR 	PARKERHANFIN		RKWELL	NA265 	NA26560 	7630106	CE 										THRUST REVERSER	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	03	113T		18 		821	306113				REMOVED TRUST REVERSER ACTUATOR DUE TO LEAKING AT SHAFT. PARKER HANNIFIN CALLS OUT MINOR LEAKING AFTER SO MANY CYCLES. 	 ACTUATOR REMOVED HAS 18 HOURS TSO AND IS LEAKING SMALL 'PUDDLES' UNDER COWL.					2	L	7	2 	4J			RT	A2WE 					 
1995102000450	19951020	00450	CE 	1995	10	20	95ZZZX5864 	1	19951004	G	7830	14054503	ACTUATOR 	PARKERHANFIN		RKWELL	NA265 	NA26560 	7630106	CE 										THRUST REV	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	03	113T		18 		592	306113				REMOVED THRUST REVERSER ACTUATOR DUE TO LEAKING AT SHAFT. PARKER HANNIFIN CALLS OUT MINOR LEAKING AFTER SO MANY CYCLES.	 ACTUATOR REMOVED, HAS 18 HOURS TSO AND IS LEAKING SMALL 'PUDDLES' UNDER COWL.					2	L	7	2 	4J			RT	A2WE 					 
1995102000451	19951020	00451	CE 	1995	10	20	95ZZZX5865 	1	19951004	G	7830	14054503	ACTUATOR 	PARKERHANFIN		RKWELL	NA265 	NA26560 	7630106	CE 										THRUST REV	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	03	113T		13 		868	306113				REMOVED THRUST REVERSER ACTUATOR DUE TO LEAKING AT SHAFT. PARKER HANNIFIN CALLS OUT MINOR LEAKING AFTER SO MANY CYCLES.	 ACTUATOR REMOVED HAS 12.8 HOURS TSO AND IS LEAKING SMALL 'PUDDLES' UNDER COWL.					2	L	7	2 	4J			RT	A2WE 					 
1995102000452	19951020	00452	CE 	1995	10	20	95ZZZX5866 	1	19951001	G	2510	FOC72751612	SHOULDER HARNESS			LEAR 	60 	60LEAR 	5170707	CE 										RESTRAINT SYS	MISASSEMBLED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	23	227N	150 				049				HARNESS WAS RECEIVED IN UNSERVICABLE CONDITION FOR REPAIR, STRAP WOULD NOT RETRACT, STRAP HAD BEEN INSTALLED INCORRECTLY	, TAKE-UP REEL WAS PART NR 1107297-03. INSTALLER HAD INSTALLED STRAP INCORRECTLY AND TAKE-UP SPRING (TO RETRACT STRAP) 	WAS BROKEN. STRAP WAS MISSING A CLIP ON THE END ALSO. STRAP ALSO WAS MARKED TO INDICATE C/W TSO C22F. PART IS A SHOUL	DER HARNESS, TSO C22 IS ONLY FOR LAP BELTS.			2	L	7	2 	4F			RT	A10CE 					 
1995102000453	19951020	00453	EA 	1995	10	20	95ZZZX5867 	1	19950929	G	3230	150113	PIN 	MENASCO 	73210001 	DHAV 	DHC7 	DHC7102 	2802708	EA 										RT MLG	CORRODED 	B			WVER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	89068	14952			540	88				DURING D-INSPECTION, RIGHT MLG UPPER DRAG STRUT PINS WERE REMOVED AND FOUND TO HAVE CORROSION AND PITTING. SUBMITTER ST	ATED NEED TO INSPECT BY REMOVING PINS. PINS ARE NOT NORMALLY INSPECTED.					2	H	7	4 	4T				A20EA 					 
1995102000454	19951020	00454	EA 	1995	10	20	95ZZZX5868 	1	19950929	G	3230	150113	PIN 	MENASCO 	73210001 	DHAV 	DHC7 	DHC7102 	2802708	EA 										RT MLG	CORRODED 	B			WVER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	89068	14952			542	88				DURING D-INSPECTION, RIGHT MLG UPPER DRAG STRUT PINS WERE REMOVED AND FOUND TO HAVE CORROSION AND PITTING. SUBMITTER ST	ATED NEED TO INSPECT BY REMOVING PINS. PINS ARE NOT NORMALLY INSPECTED.					2	H	7	4 	4T				A20EA 					 
1995102000455	19951020	00455	CE 	1995	10	20	95ZZZX5869 	1	19950912	G	2750	45A62232001	BELLCRANK 			BEECH 	MU300 	400BEECH 		CE 										LT FLAP	GROOVED 	B		A	KI2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	85CR	878 				RK22				IN PROCESS OF ACCOMPLISHING 200-HOUR INSPECTION AND SERVICE OF FLAPS, FOUND THAT SCREW HAD BEEN INTERFERRING WITH AFT FL	AP BELLCRANK. PARTS MANUAL CALLS FOR SHORTER SCREWS IN SEVERAL LOCATIONS OF COVER PANEL, HOWEVER, PANEL ITSELF IS NOT M	ARKED. RECOMMEND IMMEDIATE INSPECTION OF PUSHROD AND BELLCRANK (ON BOTH FLAPS) AND PLACARD SPECIFIC SCREW HOLES.				2	H	7	2 	4F			RT	A16SW 					 
1995021000073	19950210	00073	SO 	1995	2	10	95ZZZX587 	1	19950110	G	5412		FRAME 			PIPER 	PA36 	PA36375 	7103620	SO 										FIREWALL	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	2335X	2100 				368202005				UPPER LEFT MOTOR MOUNT ATTACHMENT WEB CRACKED THROUGH AND BOLT PULLED FORWARD ALLOWING MOTOR MOUNT TO MOVE FORWARD. NO 	SPECIFIC SIGN OF AD 92-15-15. LAST ANNUAL STATES AD'S CHECKED THROUGH 93-16-14.					1	L	7	1 	3O				A10SO 					 
1995102000456	19951020	00456	CE 	1995	10	20	95ZZZX5870 	1	19950912	G	2750	45A62232002	BELLCRANK 			BEECH 	MU300 	400BEECH 		CE 										RT FLAP	GROOVED 	B		A	KI2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	85CR	878 				RK22				IN PROCESS OF ACCOMPLISHING 200-HOUR INSPECTION AND SERVICE OF FLAPS, FOUND THAT SCREW HAD BEEN INTERFERRING WITH AFT FL	AP BELLCRANK. PARTS MANUAL CALLS FOR SHORTER SCREWS IN SEVERAL LOCATIONS OF COVER PANEL, HOWEVER, PANEL ITSELF IS NOT M	ARKED. RECOMMEND IMMEDIATE INSPECTION OF PUSHROD AND BELLCRANK (ON BOTH FLAPS) AND PLACARD SPECIFIC SCREW HOLES.				2	H	7	2 	4F			RT	A16SW 					 
1995102000458	19951020	00458	NM 	1995	10	20	95ZZZX5872 	1	19950912	G	3221	651767639	SUPPORT FITTING 			BOEING	727 	727224 	1384076	NM 										NLG TRUNNION LT	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	32719	70645				20388				DURING C-7 CHECK, FOUND RT AND LT NLG TRUNNION SUPPORT FITTINGS HAVE CORROSION UNDER BUSHINGS. REMOVED CORROSION BY REA	MING BOTH TRUNNION SUPPORT FITTINGS OVERSIZE AND INSTALLING OVERSIZE BUSHINGS IAW SRM 53-40-1.					2	L	7	3 	4F				A3WE 					 
1995102000459	19951020	00459	NM 	1995	10	20	95ZZZX5873 	1	19950912	G	3221	651767640	SUPPORT FITTING 			BOEING	727 	727224 	1384076	NM 										NLG TRUNNION RT	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	32719	70645				20388				DURING C-7 CHECK, FOUND RT AND LT NLG TRUNNION SUPPORT FITTINGS HAVE CORROSION UNDER BUSHINGS. REMOVED CORROSION BY REA	MING BOTH TRUNNION SUPPORT FITTINGS OVERSIZE AND INSTALLING OVERSIZE BUSHINGS IAW SRM 53-40-1.					2	L	7	3 	4F				A3WE 					 
1995102000460	19951020	00460	NM 	1995	10	20	95ZZZX5874 	1	19950910	G	5320		SILL ANGLE 			BOEING	727 	7272M7 	138407S	NM 										R2 THRESHOLD	CRACKED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	723RW					21202				DURING CPEP INSPECTION PER C53-224-06, IT WAS NOTED, 'R-2 DOOR THRESHOLD SILL ANGLE CORRODED AND CRACKED'. NEW PARTS WE	RE FABED AND INSTALLED IAW B727-SRM 51-20-01, PAGE 68.					2	L	7	3 	4F				A3WE 					 
1995102000461	19951020	00461	NM 	1995	10	20	95ZZZX5875 	1	19950910	G	5320		SILL ANGLE 			BOEING	727 	7272M7 	138407S	NM 										L2 THRESHOLD	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	723RW					21202				DURING CPEP INSPECTION PER C53-224-06, IT WAS NOTED, 'L-2 DOOR THRESHOLD SILL ANGLE HAS HEAVY CORROSION SEVERAL PLACES'.	 NEW PARTS WERE FABED AND INSTALLED IAW B727 SRM 51-20-2.					2	L	7	3 	4F				A3WE 					 
1995102000462	19951020	00462	NM 	1995	10	20	95ZZZX5876 	1	19950912	G	5320		DOOR HEADER 			BOEING	727 	727224 	1384076	NM 										C3 DOOR	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	32719					20388				DOOR HEADER OVER C-3 DOOR OPENING HAS SEVERE EXFOLIATING CORROSION AT FWD END AND CENTER, BS 1090 TO BS 1010. ALSO, GUS	SET AT BS 1090 BULGING AND HAS POPPED RIVETS. FOUND DURING C-7 INSPECTION. REMOVED CORRODED PARTS. FABRICATED NEW PAR	TS IAW SRM 51-20-1 AND SRM 51-30-1.				2	L	7	3 	4F				A3WE 					 
1995102000463	19951020	00463	NM 	1995	10	20	95ZZZX5877 	1	19950912	G	5320	651986312	STIFFENER 			BOEING	727 	727224 	1384076	NM 										NLG TRUNNION	CRACKED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	32719					20388				DURING C-7 CHECK, FOUND RT SIDE VERTICAL STIFFENER THAT TIES INTO THE NLG TRUNNION FITTING CRACKED. REPLACED STIFFENER 	IAW SRM 51-30-2.					2	L	7	3 	4F				A3WE 					 
1995102000464	19951020	00464	EU 	1995	10	20	95ZZZX5878 	1	19950907	G	7830	12146021	FLEX SHAFT 			AMD 	FALC20	FALCON20C5 	2730107	EU 										THRUST REV	STRANDS BROKEN 	B			NU1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	4351M	638 				457				DURING AN INTERMEDIATE THRUST REVERSER INSPECTION ON AIRCRAFT, FOUND BOTH FLEX SHAFTS HAD BROKEN STRANDS IN THE OUTER ST	AINLESS STEEL BRAIDING. THE CAUSE OF THE BROKEN STRANDS WAS DUE TO THE SEPARATION IN THE TEFLON HOUSING THAT HOLDS THE 	ROTATING SHAFT. WHEN THE CABLE WAS ASSEMBLED, IT APPEARED THE MANUFACTURER DID NOT USE A CONTINUOUS RUN OF HOUSING MATE	RIAL.			2	L	7	2 	4F			RT	A7EU 					 
1995102000465	19951020	00465	EU 	1995	10	20	95ZZZX5879 	1	19950817	G	3350	6025021	BATTERY PACK 	GRIMES 		AMD 	FALC50	FALCON50MYST	2730106	EU 										EMERG LIGHTS	WRONG PARTS 	B		A	EBVR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	09	124HM				400	117				DURING 2AT INSPECTION, FOUND THAT TWO OF THE THREE EMERGENCY LIGHT BATTERY PACKS CONTAINED SUSPECTED UNAPPROVED BATTERIE	S. THE BATTERIES WERE D-CELL SIZE AND HAD BEEN PURCHASED FROM RADIO SHACK. A TOTAL OF FOUR BATTERIES WERE FOUND, ONE I	N ONE BATTERY PACK AND THREE IN THE OTHER.				2	L	7	3 	4F				A46EU 					 
1995021000074	19950210	00074	EA 	1995	2	10	95ZZZX588 	2	19950110	G	7414	M3975	COIL 	SLICK 	6293 	PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	IO540C4B5 	41532	EA 					LT MAG	SHORTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	27	46SD	864 			90010015	278054040	RL1349848A			ENGINE WOULD NOT START. TRACED PROBLEM DOWN TO SHORTED COIL IN LEFT MAG.						1	L	7	2 	3O	3	O		1A10 	1E4				 
1995102000466	19951020	00466	EU 	1995	10	20	95ZZZX5880 	1	19950817	G	3350	6025021	BATTERY PACK 	GRIMES 		AMD 	FALC50	FALCON50MYST	2730106	EU 										EMERG LIGHTS	WRONG PARTS 	B			EBVR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	09	124HM				403	117				DURING 2AT INSPECTION, FOUND THAT TWO OF THE THREE EMERGENCY LIGHT BATTERY PACKS CONTAINED SUSPECTED UNAPPROVED BATTERIE	S. THE BATTERIES WERE D-CELL SIZE AND HAD BEEN PURCHASED FROM RADIO SHACK. A TOTAL OF FOUR BATTERIES WERE FOUND, ONE I	N ONE BATTERY PACK AND THREE IN THE OTHER.				2	L	7	3 	4F				A46EU 					 
1995102000468	19951020	00468	CE 	1995	10	20	95ZZZX5882 	1	19950922	G	5510	1694400173	HINGE 			BEECH 	23 	B19 	1151215	CE 										LT STABILATOR	FAILED 	C	P	A		O				OTHER 				O			OTHER 			LD	LANDING 	1			NE	05	5137M	4821 				MB890				AFTER LANDING, AIRCRAFT EXPERIENCED A NOSE WHEEL SHIMMY. THE CONTROLS FOR THE STABILATOR FELT ABNORMAL FOLLOWING SHIMMY	 DURING ROLL-OUT. FURTHER INVESTIGATION REVEALED THE LEFT STABILATOR ATTACH BRACKET SHEERED OFF WITHOUT INDICATION OF W	ORKING - AD87-02-08 C/W 88 HOURS PREVIOUSLY.				1	L	7	1 	3O				A1CE 					 
1995102000469	19951020	00469	SO 	1995	10	20	95ZZZX5883 	2	19951002	G	8520	SA628488	LIFTER 			CESSNA	182 	182D 	2072710	CE 	CONT 	O470 	O470L 	17026	SO 					LIFTER FACE	FAILURE 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	9085X	92 				18253485	801719L4			INSPECTION FOR ENGINE MAKING METAL FOUND LIFTERS AND CAMSHAFT FAILURE. LIFTER P/N SA628488, P/N SA646277.						1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995102000470	19951020	00470	NM 	1995	10	20	95ZZZX5884 	1	19950927	G	7810	33681	TAILPIPE 			PIPER 	PA60 	PA60601P 	7106012	NM 										LT TURBO	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	3646K	678 			0406	61P085781634				DURING ANNUAL INSPECTION, TAILPIPE REMOVED. LARGE CRACK AT ONE OF THE UPPER WELDS NEAR TURBOCHARGER MATING FLANGE WAS N	OTED. CRACK WAS OPEN .1250 INCH WIDE AND EXTENDED THREE-FOURTHS OF THE WAY AROUND PIPE. THIS PIPE IS PART OF STC SA271	7S0 WHICH ELIMINATES REPETITIVE 50-HOUR DYE PEN. CHECKS OF STANDARD PIPER TAILPIPES PER AD 40-01-02. STC RECOMMENDS SHA	KING TAILPIPES BY HAND ON EACH PRE-FLIGHT. THIS IS THE FIRST FAILURE OF THE MALLEN AEROSPACE TAILPIPES THIS AGENCY HAS 	SEEN SINCE STARTING TO INSTALL THEM IN MID-1990.		1	M	7	2 	3O			RT	A17WE 					 
1995102000472	19951020	00472	CE 	1995	10	20	95ZZZX5886 	1	19950525	G	5532	6064000028	SKIN 			BEECH 	60 	60 	1153602	CE 										LT VERT STAB	CORRODED 	B	P		VIBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	129LP	866 				P322				WHEN AIRCRAFT WAS STRIPPED FOR PAINTING, SEVERE CORROSION WAS NOTED WITH HOLES THROUGH SKIN AND INTO HONEYCOMB. APPEARS	 TO BE INTERGRANULAR CORROSION, POSSIBLY STARTED AT MANUFACTURING PROCESS.					1	L	7	2 	3O				A12CE 					 
1995102000473	19951020	00473	SO 	1995	10	20	95ZZZX5887 	1	19950922	G	3230	4033600	DRAG LINK 			PIPER 	PA31 	PA31350 	7103110	SO 										NLG	BROKEN 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	01	601DA					318453002				NOSE GEAR RT DRAG LINK BROKE AT JUST FWD OF NOSE GEAR ACTUATOR ATTACH POINT. IDENTICAL TO CRACKS AND FAILURES NOTED IN 	AD 88-05-05 WHICH COVERS MLG DRAG LINKS. FOLLOWING INSP OF BROKEN DRAG LINK, IT IS THIS SUBMITTER'S OPINION THAT CRACK 	STARTED INTERNALLY IN DRAG LINK. IT SHOULD BE NOTED INSP OF THIS AREA OF DRAG LINK CAN ONLY BE ACCOMPLISHED BY REMOVAL 	OF LINK ASSY, PAYING SPECIAL ATTN TO AREA JUST FWD AND BETWEEN EARS FOR ACTUATOR ATTACHMENT. IT IS SUBMITTER'S RECOMMEN	DATION THIS DRAG LINK BE REPLACED WITH A STRONGER LINK ASSY, AS WAS DONE THROUGH AD 88-05-05, FOR THE LIKE MLG DRAG LINK	S AS AFOREMENTIONED, THIS FAILURE IS IDENTICAL TO THOSE ASSOCIATED WITH THE MAIN GEAR DRAG LINKS.	1	L	7	2 	3O				A20SO 					 
1995102000474	19951020	00474	CE 	1995	10	20	95ZZZX5888 	1	19950525	G	5512	6062000025	SKIN 			BEECH 	60 	60 	1153602	CE 										LT HORIZ STAB	CORRODED 	B	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	129LP	867 				P322				WHEN AIRCRAFT WAS STRIPPED FOR PAINTING, SEVERE CORROSION WAS NOTED WITH HOLES THROUGH SKIN AND INTO HONEYCOMB, APPEARS 	TO BE INTERGRANULAR CORROSION, POSSIBLY STARTED AT MANUFACTURING PROCESS.					1	L	7	2 	3O			 	A12CE 					 
1995021000075	19950210	00075	EA 	1995	2	10	95ZZZX589 	2	19950119	G	7414	ES10357426	DISTRIBUTOR BLK 	BENDIX 	S6LN200 	PIPER 	PA24 	PA24250 	7102404	SO 	LYC 	O540 	O540A1D5 	41532	EA 					ENGINE MAG	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	6917P	402 			627264	242051	L281740			CENTER BUSHING IN THE DISTRIBUTOR BLOCK CAME LOOSE WHERE IT WAS CAST INTO THE BLOCK MATERIAL ALLOWING DISTRIBUTOR GEAR T	O SHIFT AWAY FROM THE DRIVE GEAR CAUSING MAG TO FIRE OUT OF TIME (CROSS-FIRE TYPE OF CONDITION).					1	L	7	1 	3O	3	O		1A15 	E295				 
1995102700011	19951027	00011	EU 	1995	10	27	95ZZZX5899 	1	19950727	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	781LF	420 			3555	1178				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995021000076	19950210	00076	SO 	1995	2	10	95ZZZX590 	1	19950113	G	8120	LW12463	BEARING 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					RT ENG TURBO	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	09	59919				SJR0148	317552038	RL111868A			BEARINGS ON THE RIGHT ENGINE TURBOCHARGER FAILED ALLOWING SHAFT TO JUMP UP AND DOWN PULLING SEAL AWAY AND ALLOWING OIL T	O BE INTRODUCED TO THE HOT SIDE OF THE TURBO. REPLACED TURBOCHARGER AND INSPECTED RT ENGINE OIL FILTER FOR METAL. ENGI	NE OKAY.				1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995102700012	19951027	00012	EU 	1995	10	27	95ZZZX5900 	1	19950727	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	781LF	420 			0205	1178				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995102700013	19951027	00013	EU 	1995	10	27	95ZZZX5901 	1	19950727	G	6220	704A33633156	SPHERICAL STOP 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	781LF	420 			3609	1178				SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995102700014	19951027	00014	EU 	1995	10	27	95ZZZX5902 	1	19950530	G	6220	11714106117	SIGHT GLASS 			BOLKMS	105 	BO105CBS 	5626008	EU 										M/R HEAD	DEFECTIVE 	B			DYRR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	07	105NC					790				MAIN ROTOR HEAD SIGHT GLASS HAS IMPERFECTIONS IN THE U-CHANNEL. UNIT NEVER INSTALLED. REPLACED WITH NEW UNIT(S) CORREC	TED PROBLEM.					1	G	7	2 	3U			NC	H3EU 					 
1995102700015	19951027	00015	EU 	1995	10	27	95ZZZX5903 	1	19950823	G	6720	350A27191004	ROD 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	BENT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	96LG	186 				2817				TAIL ROTOR CONTROL ACTUATING ROD BEARING END BENT ENOUGH TO CHAFE BELLCRANK FORK AT ATTACH POINT. REPLACED WITH NEW UNI	T(S) CORRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995102700016	19951027	00016	EU 	1995	10	27	95ZZZX5904 	1	19950605	G	7712	305731365	INDICATOR 			SNIAS 	350 	AS350B2 	8680813	EU 										TORQUEMETER	SPINS 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	96LG	12 			431	2817				TORQUEMETER INDICATOR SPINS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995102700017	19951027	00017	EU 	1995	10	27	95ZZZX5905 	1	19950717	G	2913	704A34310006	PUMP 			SNIAS 	350 	AS350B2 	8680813	EU 										HYD SYS	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07	96LG	89 			31176971	2817				HYDRAULIC PUMP LEAKING HYDRAULIC FLUID FROM BOLTS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995102700018	19951027	00018	EU 	1995	10	27	95ZZZX5906 	1	19950331	G	6410	134615P	BUSHING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R BLADE	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911BY	319 				7127				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 4 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995102700019	19951027	00019	EU 	1995	10	27	95ZZZX5907 	1	19950331	G	6420	ABWT82008	BEARING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911BY	114 				7127				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995102700020	19951027	00020	EU 	1995	10	27	95ZZZX5908 	1	19950612	G	6240	G300102	ROTOR SPEED 			SNIAS 	350 	AS350B2 	8680813	EU 										ROTOR WARNING	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	6099P	12 			219	2818				ROTOR SPEED WARNING DEFECTIVE. NO HORN LIGHT. NO HORN DURING HYDRAULIC TEST. REPLACED WTIH NEW UNIT(S) CORRECTED PROB	LEM.					1	G	7	1 	3U				H9EU 					 
1995102700021	19951027	00021	SW 	1995	10	27	95ZZZX5909 	1	19950808	G	6320	206040032001	BEARING 		206040002029	BELL 	206 	206B 	1181511	SW 										M/R	FAILED 	B			ALGR	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	5008K		2521 		2835	2524				TRANSMISSION REMOVED FOR CHIP LIGHT. FOUND DURING TEAR DOWN FOR REPAIR THAT BEARING SET HAD BEGUN TO BREAK DOWN FROM FA	TIGUE.					1	G	7	1 	3U				H2SW 					 
1995102700022	19951027	00022	EU 	1995	10	27	95ZZZX5910 	1	19950902	G	2435	23032048	STARTER 			BOLKMS	105 	BO105CBS 	5626008	EU 										START/GEN	SCREEN FAILED 	B			CZ4R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			AL	01	493HL	3975 	384 		24722	S809				STARTER/GENERATOR SCREEN CAME OFF AND WENT THROUGH THE COOLING FAN CAUSING DAMAGE. REPLACED STARTER/GENERATOR.						1	G	7	2 	3U			NC	H3EU 					 
1995102700023	19951027	00023	SW 	1995	10	27	95ZZZX5911 	1	19950821	G	6220	206310005101	PILLOW BLOCK 		206011100159	BELL 	206 	206L3 	1182108	SW 										M/R HUB	BOLT STRETCH 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	731H				238	51562				THE SUBJECT BOLT LOST TORQUE SEVERAL TIMES. MAINTENANCE HAD NO WAY OF KNOWING IF THIS BOLT REQUIRED MORE THAN 1 RETORQU	E, AS THE BOLT POSITION IS NOT NOTED IN THE NON-ROUTINES. THE ONLY LOGICAL EXPLANATION IS THE BOLT MUST BE STRETCHING. 	 WHEN MEASURED, THE BOLT SHANK OD IS .003 INCH SMALLER AT CENTER THAN THE OUTBOARD DIMENSIONS. THIS BOLT (BOLTS) LOSE T	ORQUE OVER A SHORT PERIOD OF TIME. THE SUBMITTER STATED THEY WILL FORWARD A COPY OF THIS 8010-4 FORM ALONG WITH A BOLT 	TO BELL HELICOPTER, FOR ANALYSIS.		1	G	7	1 	3U				H2SW 					 
1995102700024	19951027	00024	GL 	1995	10	27	95ZZZX5912 	2	19950910	G	7250	A6871505	BEARING 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					NR 5	MAKING METAL 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	105NC	96 			104	790	CAE836124			INSPECTED AIRFRAME SCAVENGE OIL FILTER PER SUPERIOR TURBINE INFORMATION BULLETIN NR 95-IB001 (SB T95-SB001). FOUND 13 S	ILVER FLAKES IN FILTER BOWL. NO ABNORMAL INDICATIONS OR CHIP LIGHTS. REPLACED WTIH NEW SERVICEABLE BEARING. SUPERIOR 	TURBINE OFFERED EXCELLENT SERVICE WHEN ADVISED OF FINDINGS.				1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995102700025	19951027	00025	SW 	1995	10	27	95ZZZX5913 	1	19950909	G	2840	7G547	SWITCH 			BELL 	206 	206B 	1181511	SW 										FUEL BOOST	INOP 	B			WG3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	33TV	879 	879 		31002	4306				FORWARD FUEL BOOST PUMP PRESSURE SWITCH INOPERABLE AT 878.8 HOURS. REMOVED SWITCH, P/N 7G547, S/N 31002, AND INSTALLED 	NEW SWITCH, P/N 7G547, S/N 32230.					1	G	7	1 	3U				H2SW 					 
1995102700026	19951027	00026	SW 	1995	10	27	95ZZZX5914 	1	19950909	G	6230	206010454109	SLEEVE ASSY 			BELL 	206 	206B 	1181511	SW 										SWASHPLATE	WORN 	B			WG3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	33TV	299 			RE5906	4306				INSPECTED SWASHPLATE ASSY AT 878.2 HOURS, AND FOUND EXCESSIVE MOVEMENT IN SLEEVE ASSY. REMOVED SLEEVE ASSY DUE TO EXCES	SIVE WEAR ON SLEEVE. ID BEARING GLOVES ASSY TSN 298.7 HRS. INSTALLED NEW SLEEVE, P/N 206-010-454-108, S/N RE-6092, ONT	O SWASHPLATE ASSY.				1	G	7	1 	3U				H2SW 					 
1995110600015	19951106	00015		1995	11	6	95ZZZX5919 	4	19950928	G	3422	5201900102	GYRO 	AERONETICS 		AGUSTA	A109 	A109K2 	0260502	EU 										COCKPIT REMOTE	LOOSE PARTS 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	911RX	1059 			12640	10017				AFTER REMOVING GYRO FROM THE AIRCRAFT, A RATTLING NOISE WAS HEARD INSIDE THE GYRO HOUSING. THE UNIT WAS DISASSEMBLED AN	D INSPECTED. A SMALL BRASS KNURLED NUT (TOOL?) WAS FOUND INSIDE. THERE WAS IMPACT DAMAGE IN THE SPINNING PORTION OF TH	E GYRO.				1	G	7	2 	3U			RT	H7EU 					 
1995110600016	19951106	00016	WP 	1995	11	6	95ZZZX5920 	1	19950929	G	6210	369D21100516	BLADE 			HUGHES	369 	369D 	4470706	WP 										DAMPER	BEARING LOOSE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y	2218 	1594 		022226368	500716D				DURING 25-HOUR INSPECTION, DISCOVERED THE M/R BLADE DAMPER ATTACH BEARING (369A7951-15) WAS QUITE LOOSE. BLADE WAS REMO	VED, REPAIRED, AND REINSTALLED.					1	G	7	1 	3U				H3WE 					 
1995110600017	19951106	00017	GL 	1995	11	6	95ZZZX5921 	2	19950901	G	7310	77165001	FILTER ASSY 		306051 	BEECH 	36 	A36 	1151604	CE 	ALLSN 	250B 	250B17 	03012	GL 					FUEL FILTER	BROKEN 	B	P		CB5Y	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EU	03	250TP	718 				E2408	CAE880650			PILOT REPORTED A FUEL LEAK FROM THE ENGINE. INVESTIGATION REVEALED A LOOSE FILTER BOWL. ON A CLOSER EXAMINATION, FOUND	 FILTER BOWL HAD ALMOST DETACHED ITSELF FROM THE UPPER HOUSING. WHEN THE BOWL WAS FINALLY REMOVED, PART OF THE UPPER HO	USING TO WHICH THE FILTER BOWL CENTER ATTACHMENT BOLT IS SECURED, BROKE AWAY AND WAS FOUND ATTACHED TO THE BOLT.				1	L	7	1 	3O	3	T		3A15 	E10CE				 
1995110600018	19951106	00018	SO 	1995	11	6	95ZZZX5922 	1	19950525	G	5740	9010443	BOLT 			GULSTM	AA5 	AA5B 	3960105	SO 										WING ATTACH	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	74128	3799 				AA5B0148				WHEN INVESTIGATING WING BOLTS PER AGAC SB 185, RT WING AFT SHOULDER BOLT FOUND BROKEN.						1	L	7	1 	3O				A16EA 					 
1995110600019	19951106	00019	SW 	1995	11	6	95ZZZX5923 	1	19950901	G	6120	A295	LINKSCREW 			TMPSON	NAVION	NAVIONA 	6150104	SW 						HARTZL	HC12V	HC12V20* 	GL 	BLADE CLAMP	PIN SHEARED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	747WR					NAV4997		R430N		REMOVING PROPELLER TO CHECK FOR AN OIL LEAK, PIN, PITCH CHANGE, AND BLOCK FELL TO GROUND (LINKSCREW). FOUND PIN SHEARED	 IN HALF FOR REASONS UNKNOWN. PIN WAS .4375 INCH DIAMETER. MFG CLAIMS PIN SIZE INCREASED TO .50 INCH DIAMETER IN 1957 	DUE TO HISTORY OF .4375 INCH PINS FAILING.				1	L	7	1 	3O				A782 		5	C	P46GL	 
1995110600020	19951106	00020	CE 	1995	11	6	95ZZZX5924 	1	19950908	G	7810	265400836	EXHAUST DUCT 			CESSNA	208 	208 	2073702	CE 										ENG EXHAUST	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	2FOR	391 				20800239				OPERATOR COMPLAINED OF SUPPORT BRACKET FAILURES. AT 390.6 HOURS, CRACK IN ENGINE EXHAUST DUCT 24 INCHES LONG, SPLIT ON 	WELD SEAM. AIRCRAFT IS CORPORATE CONFIG NOT CARGO CONFIG.					1	H	7	1 	3T			NT	A37CE 					 
1995110600021	19951106	00021	SO 	1995	11	6	95ZZZX5925 	2	19950921	G	7414	10160844	DISTRIBUTOR 								CONT 	O520 	IO520* 	17032	SO 					MAG	BRUSH LOOSE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05		100 								MAG INOPERATIVE. FOUND DISTRIBUTOR SHAFT BLUE. OPENED MAG AND FOUND DISTRIBUTOR BRUSH LOOSE IN MAG CASE. FOUND DISTRI	BUTOR GEAR HUB AND COIL FINGER DAMAGED BY ARCING. BRUSH EITHER FELL OUT OR WAS INSTALLED IMPROPERLY. MAG RAN SEVERAL H	OURS USING BRUSH SPRING TO COMPLETE CIRCUIT.									3	O			E5CE				 
1995110600022	19951106	00022	CE 	1995	11	6	95ZZZX5926 	1	19950911	G	3260	12430192	BRACKET 			CESSNA	210 	T210N 	2073456	CE 										SQUAT SWITCH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	5408A	4080 				21063419				LANDING GEAR SQUAT SWITCH BRACKET CRACKED POSSIBLY DUE TO NOSE WHEEL SHIMMY.						1	H	7	1 	3O				3A21 					 
1995110600023	19951106	00023	NE 	1995	11	6	95ZZZX5927 	2	19950920	G	8530	399356	CYLINDER 			AIRTRC	AT300 	AT301 	0390103	SW 	PWA 	R1340 	R1340AN1 	52016	NE 					NR 4	HEAD BROKE 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			SO	11	2362D		16 			3010404	22167			CYLINDER HEAD BROKE AT EXHAUST VALVE ROCKER SHAFT ATTACHMENT PREVENTING THE ROCKER ARM FROM OPENING THE EXHAUST VALVE. T	HE ENGINE SUBSEQUENTLY QUIT AND THE AIRCRAFT CRASHED IN A FIELD.					1	L	7	1 	3R	3	R		A9SW 	5E2				 
1995110600024	19951106	00024	SO 	1995	11	6	95ZZZX5928 	2	19950616	G	8510	633908	SHAFT 			CESSNA	421 	421A 	2076012	CE 	CONT 	O520 	GTSIO520D 	17032	SO 					LT PROP	SHEARED 	D				E				ENGINE SHUTDOWN 				O			OTHER 			CR	CRUISE 	1			SO	09	422RD					421A0018	18865297			AIRCRAFT ARRIVED AT FBO WITH RIGHT ALTERNATOR PROBLEM. REPAIRED RIGHT ALTERNATOR. WHEN AIRCRAFT START ATTEMPTED, LEFT 	STARTER FOUND TO HAVE SHEARED THROUGH-BOLT. NEW STARTER INSTALLED. AIRCRAFT DEPARTED FBO AND RETURNED ABOUT 30 MINUTES	 LATER WITH LEFT ENGINE SHUT DOWN AND FEATHERED. OPERATOR STATED RPM DROPPED IN-FLIGHT. ON GROUND CHECK, FOUND LEFT PR	OP SHAFT SHEARED FORWARD OF BULL GEAR. SUSPECT ENGINE HAD SEVERE VIBRATION IN RECENT HISTORY DUE TO DAMPENER COMING LOO	SE CAUSING CRACK IN SHAFT. SUBMITTER RECOMMENDED ANY ENGINE SUBJECTED TO VIBRATIONS HAVE CRITICAL PARTS INSPECTED USING	 MAGNAFLUX/ZYGLO TECHNIQUES.	1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995110600025	19951106	00025	SO 	1995	11	6	95ZZZX5929 	2	19950925	G	7414	10382584	CONTACT ASSY 		S6LN1255 	CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					LT ENG RT MAG	BROKEN 	B			BYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	421BP	242 			C199305FR	421B0388	L235135R			DURING PRE-FLIGHT ENGINE CHECK, PILOT NOTED THE RIGHT MAGNETO ON THE LEFT ENGINE DEAD. MECHANIC REMOVED MAGNETO AND DIS	COVERED THE CONTACT ASSY CAM FOLLOWER ARM BROKE JUST FORWARD OF THE SECURING SCREW. CAUSE OF BREAK UNKNOWN.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995021000079	19950210	00079	SO 	1995	2	10	95ZZZX593 	1	19950111	G	5711	82200696	SPAR 			PIPER 	PA46 	PA46310P 	7104605	SO 										WS 93	BENT 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	4375P	2095 				468508031				UPON 100-HOUR INSPECTION, FOUND WING SURFACE DISTORTED, SKINS CREASED ON LOWER SURFACE WS 93.00 AT MAIN SPAR. REMOVAL O	F SKIN REVEALED LOWER SPAR CAP BENT, SPAR WEB CREASED AND RIBS DAMAGED. CAUSE UNKNOWN. SPAR CAP TOO WEAK AT JACK POINT	S.				1	L	7	1 	3O				A25SO 					 
1995110600026	19951106	00026	EU 	1995	11	6	95ZZZX5930 	1	19950825	G	7931		FITTING 			GROB 	G115 	G115C 	1660303	EU 										OIL PRESS XDUCER	CRACKED 	B			SL5R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NE	03	115AZ	57 				82035C				DURING SEARCH FOR OIL LEAK AT AFT PORTION OF ENGINE, FOUND ALUMINUM ELBOW FITTING SUPPORTING OIL PRESSURE TRANSDUCER CRA	CKED. IT APPEARS THE WEIGHT OF THE TRANSDUCER WAS TOO MUCH FOR THE ALUMINUM FITTING. MOVED TRANSDUCER OUTBOARD AFT AND	 SECURED TO ENGINE MOUNT USING ADEL CLAMPS, INSTALLED NEW FITTING IN ENGINE AND CONNECTED FITTING TO TRANSDUCER WITH HIG	H PRESSURE HOSE. SUBMITTER STATED IF THE FITTING BROKE COMPLETELY, ALL ENGINE OIL COULD HAVE BEEN LOST.			1	L	7	1 	3O			NT	A57EU 					 
1995110600027	19951106	00027	CE 	1995	11	6	95ZZZX5931 	1	19950912	G	3231		CONTROL ARM 			CESSNA	421 	421C 	2076016	CE 										RT GR DOOR	MISADJUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	421CV	4107 				421C0703				GEAR WOULD NOT UNLOAD IN UP POSITION WHEN RETRACTED IN SHOP. FOUND RIGHT GEAR DOOR OUTBOARD END HAD LOOSE LOCKNUT. SUS	PECT MECHANIC ADJUSTED DOOR AND DID NOT TIGHTEN NUT. IF DOOR WAS LATER DISCONNECTED, THE CONTROL ARM COULD HAVE BEEN MO	VED INADVERTENTLY WHICH COULD KEEP THE GEAR FROM RETRACTING FULLY. READJUSTED CONTROL ARM AND TIGHTENED NUTS. OPS CHEC	K SATISFACTORY.			1	L	7	2 	3O				A7CE 					 
1995110600028	19951106	00028	SO 	1995	11	6	95ZZZX5932 	2	19950922	G	8530		GUIDE 			CESSNA	172 	172 	2072402	CE 	CONT 	O300 	O300A 	17022	SO 					EXHAUST VALVE	EXCESS WEAR 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	27	6079A					28679	1599708A			NEW CYLINDERS FOR ENGINE ONLY LASTED FOR 85 HOURS WHEN EXHAUST GUIDES EXHIBITED EXCESS WEAR.						1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995110600030	19951106	00030	SO 	1995	11	6	95ZZZX5934 	2	19950826	G	8550	641734	FILTER ADAPTER 		641801 	CESSNA	172 	R172K 	2072431	CE 	CONT 	O360 	IO360K 	17025	SO 					CRANKCASE COVER	THREADS STRIPPED	G				O				OTHER 				K			FLUID LOSS 			NR	NOT REPORTED 	1			GL	25	1439V	2184 	616 			R1722191	230344R			OIL FITLER ADAPTER SEPARATED FROM ENGINE AT CRANKCASE COVER MOUNTING BOSS ALLOWING OIL SUPPLY TO BE EXHAUSTED. INVESTIG	ATION REVEALED 80 PERCENT OF THE MOUNTING THREADS CONTAINED IN THIS BOSS WERE STRIPPED. HIGH TEMP RTV WAS FOUND ON THES	E THREADS AS WELL AS THE THREADS OF THE OIL FILTER ADAPTER. THE TCM OVERHAUL MANUAL DOES NOT CALL FOR SEALER IN THIS AR	EA.			1	H	7	1 	3O	3	O		3A17 	E1CE				 
1995110600031	19951106	00031	SO 	1995	11	6	95ZZZX5935 	1	19950923	G	8120	4078009003	TURBOCHARGER 	GARRTT 		PIPER 	PA31 	PA31P 	7103120	SO 	LYC 	O541 	TIGO541E1A 	41539	EA 					SEAL	OIL LOSS 	B			EKIR	O				OTHER 				K	J		FLUID LOSS 	WARNING INDICATION 		AP	APPROACH 	1			WP	07	110SK	139 			XK019256	31P7630006	L13362			ENGINE LOST OIL PRESSURE ON APPROACH TO AIRPORT. UPON INSPECTION ON THE GROUND, FOUND NO OIL IN ENGINE. OIL ON TURBO C	ENTER HOUSING AND OVERBOARD EXHAUST STACK. FOUND NO OTHER EVIDENCE OF LEAKAGE. PRESSURE TESTED ALL OIL LINES AND HOSES	, FOUND NO OTHER LEAKS. SUSPECT LOSE OF TURBO SEAL.				1	L	7	2 	3O	3	O		A8EA 	E19EA				 
1995110600032	19951106	00032	CE 	1995	11	6	95ZZZX5936 	1	19950929	G	3213	50411082	BEARING 			CESSNA	340 	340A 	2076405	CE 										MLG INNER	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	05	340HH	2778 				340A0973				REF AD 9002-13 MAIN LANDING GEAR INNER BEARING. THIS AD IS APPLICABLE TO CESSNA 340-0001 THROUGH 340A-0801. WHEN RE-SE	ALING MAIN GEAR STRUTS ON 340A0973, FOUND INNER BEARINGS INSTALLED ON BOTH STRUTS. AD AND CESSNA SB NEEDS TO BE REVISED	 TO INCLUDE ALL SERIAL NUMBERS.				1	L	7	2 	3O				3A25 					 
1995110600033	19951106	00033	SO 	1995	11	6	95ZZZX5937 	1	19950905	G	3211	401335	BARREL NUT 			PIPER 	PA34 	PA34200 	7103405	SO 										RT MLG TRUNNION	FAILED 	D				K				NONE 				O			OTHER 			LD	LANDING 	1			WP	23	49SA					347350057				AFTER INSTALLING A NEW TRUNNION REQUIRED BY AD94-13-11, THE AIRCRAFT'S RIGHT GEAR COLLAPSED DURING LANDING. INVESTIGATI	ON REVEALED THE RIGHT TRUNNION PIN AND BOLT WERE DISENGAGED FROM THE TRUNNION AND WERE LAYING INSIDE OF THE WING. THE T	RUNNION PIN BOLT BARREL NUT WAS MISSING FROM THE AIRCRAFT. SUSPECTED FAILURE OF BARREL NUT CAUSED THIS INCIDENT. RECOM	MEND REQUIREMENT OF REPLACING BARREL NUT WITH NEW AND SPECIFIC TORQUE REQUIREMENT BE ADDED TO AD NOTE.			1	L	7	2 	3O				A7SO 					 
1995110600034	19951106	00034	SO 	1995	11	6	95ZZZX5938 	2	19951004	G	7322	P46F11	VENTURI 	FACET 	MA3SPA 	CESSNA	170 	170A 	2072304	CE 	CONT 	O300 	O300D 	17022	SO 					CARBURETOR	FAULTY 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	9026A	188 			104439	18781	34206D6D			ONE-PIECE VENTURI INSTALLED TO COMPLY WITH AD 93-18-03. AFTER INSTALLATION, AIRCRAFT WOULD NOT RUN SMOOTHLY, FUEL CONSU	MPTION INCREASED ABOUT ONE AND ONE-HALF GALLONS PER HOUR. SUBMITTER STATED THAT THE AD SHOULD HAVE BEEN A MANDITORY INS	PECTION AT ANNUAL ONLY.				1	H	7	1 	3O	3	O		A799 	E253				 
1995110600035	19951106	00035	EA 	1995	11	6	95ZZZX5939 	2	19951005	G	8530	LW19001	VALVE 			GULSTM	AA5 	AA5A 	3960106	SO 	LYC 	O320 	O320E2G 	41508	EA 					NR 3 CYL EXHAUST	FAILED 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			GL	05	9671U					AA5A0037	L4300227A			PILOT REPORTED POWER LOSS OF MAX RPM 1600. INSPECTED POWERPLANT, FOUND NR 3 CYLINDER HAD NO COMPRESSION. PULLED CYLIN	DER, FOUND EXHAUST VALVE BROKEN. TOP OF PISTON AND CYLINDER HEAD DAMAGED BADLY. SUSPECT VALVE FATIGUE AS CAUSE OF FAIL	URE.				1	L	7	1 	3O	3	O		A16EA 	E274				 
1995021000080	19950210	00080	SO 	1995	2	10	95ZZZX594 	1	19950111	G	5712	8309603	RIB 			PIPER 	PA46 	PA46310P 	7104605	SO 										WS 93	DAMAGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	4375P	2095 				468508031				UPON 100-HOUR INSPECTION, FOUND WING SURFACE DISTORTED, SKINS CREASED ON LOWER SURFACE WS 93.00 AT MAIN SPAR. REMOVAL O	F SKIN REVEALED LOWER SPAR CAP BENT, SPAR WEB CREASED AND RIBS DAMAGED. CAUSE UNKNOWN. SPAR CAP TOO WEAK AT JACK POINT	S.				1	L	7	1 	3O				A25SO 					 
1995110600036	19951106	00036	CE 	1995	11	6	95ZZZX5940 	1	19950907	G	2701	05131661	CONTROL WHEEL 		05131822 	CESSNA	172 	172D 	2072410	CE 	CONT 	O300 	O300D 	17022	SO 					PILOT	BROKE 	G				A				UNSCHED LANDING 				O			OTHER 			AP	APPROACH 	1			SW	11	2519U	1670 				17250119	27720D2D			AFTER 40 MINUTES OF CRUISE FLIGHT TO 3,000 FEET MSL, THE ENGINE LOST POWER. ABOUT 80 FEET ABOVE THE GROUND, ON SHORT FI	NAL TO A HAY FIELD, THE CONTROL WHEEL BROKE. THE PILOT GRABBED THE CONTROL WHEEL TUBE AND STARTED TO FLARE FOR LANDING 	WHEN THE AIRCAFT STRUCT THE GROUND IN A NOSE-LOW ATTITUDE. CAUSE OF POWER LOSS AND CONTROL WHEEL BREAKAGE STILL UNDER I	NVESTIGATION.			1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995110600037	19951106	00037	SO 	1995	11	6	95ZZZX5941 	2	19950907	G	8500		ENGINE 			CESSNA	172 	172D 	2072410	CE 	CONT 	O300 	O300D 	17022	SO 					POWER SECTION	FAILED 	G				A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			SW	11	2519U	1670 				17250119	27720D2D			AFTER 40 MINUTES OF CRUISE FLIGHT TO 3,000 FEET MSL, THE ENGINE LOST POWER. ABOUT 80 FEET ABOVE THE GROUND, ON SHORT FI	NAL TO A HAY FIELD, THE CONTROL WHEEL BROKE. THE PILOT GRABBED THE CONTROL WHEEL TUBE AND STARTED TO FLARE FOR LANDING 	WHEN THE AIRCAFT STRUCT THE GROUND IN A NOSE-LOW ATTITUDE. CAUSE OF POWER LOSS AND CONTROL WHEEL BREAKAGE STILL UNDER I	NVESTIGATION.			1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995110600038	19951106	00038		1995	11	6	95ZZZX5942 	1	19950601	G	6120	SK112324	YOKE 													HAMSTD	14RF	14RF9 	NE 	PITCH CHANGE	ARMS CRACKED 	B			H2SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		5530 	2513 		165					THE SUBJECT YOKE WAS RECEIVED FOR WORN WEAR PLATES. VISUAL EXAMINATION REVEALED TWO CRACKED YOKE ARMS; ONE CRACK EXTEND	ED ALMOST THE TOTAL THICKNESS OF THE ARM ON ONE SIDE OF THE ARM. THE SECOND ARM CONTAINED A CRACK APPROXIMATELY 0.400 I	NCH IN LENGTH. THE CRACKS ALSO EXTENDED PARTIALLY ACROSS THE TOP OF THE ARMS. FPI FOUND NO OTHER CRACKS. THE PART HAS	 BEEN FORWARDED TO HAMILTON STANDARD ENGINEERING FOR EVALUATION. THIS IS THE FIRST YOKE OF THIS TYPE (MODIFIED) FOUND, 	WITH CRACKS, AT THIS FACILITY.												6	C	P11NE	 
1995110600039	19951106	00039	EU 	1995	11	6	95ZZZX5943 	1	19950901	G	7820		MUFFLER 	WALLCOLMNY 		SLNSBY	T67 	T67M260 	8323006	EU 										TAILPIPE	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3004H	588 				2126				THE MUFFLER TAILPIPE IS CHAFING ON THE FIREWALL. A WEAR SPOT WAS FOUND ON INSPECTION. THE ENGINE WAS GROUND RUN AT AN 	OPERATING TEMPERATURE WHICH CAUSED THE MUFFLER TAILPIPE TO EXPAND UP TO 13 MM CAUSING IT TO TOUCH FIREWALL AT FRAME NR 1	. SUBMITTER RECOMMENDS REPOSITIONING TAILPIPE DOWN MORE TO PREVENT THIS DEFECT.				1	L	7	1 	3O			NT	A73EU 					 
1995110600040	19951106	00040	EU 	1995	11	6	95ZZZX5944 	1	19950901	G	7820		MUFFLER 			SLNSBY	T67 	T67M260 	8323006	EU 										TAILPIPE	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3154Z	705 				2110				THE MUFFLER TAILPIPE IS CHAFING ON THE FIREWALL. A WEAR SPOT WAS FOUND ON INSPECTION. THE ENGINE WAS GROUND RUN AT OPE	RATING TEMPERATURE WHICH CAUSED THE MUFFLER TAILPIPE TO EXPAND UP TO 13 MM CAUSING IT TO TOUCH FIREWALL AT FRAME NR 1. S	UBMITTER RECOMMENDS REPOSITIONING TAILPIPE DOWN MORE TO PREVENT THIS DEFECT.				1	L	7	1 	3O			NT	A73EU 					 
1995110600041	19951106	00041	SO 	1995	11	6	95ZZZX5945 	2	19950510	G	8530		RINGS 			BEECH 	58 	58P 	1152744	CE 	CONT 	O520 	TSIO520WB 	17040	SO 					CYLS 2,4,6	SEIZED 	B			VIBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	6685D	602 				TJ241	274203R			THE OPERATOR REPORTED EXCESSIVE OIL CONSUMPTION. COMPRESSION ON CYLINDERS 2, 4, AND 6 WAS BELOW MINIMUMS WITH BLOWBY BY	 PISTON RINGS. DISASSEMBLY REVEALED THE RINGS ON ALL THREE PISTIONS WERE SEIZED DUE TO CARBON BUILD-UP. THE ENGINE HAS	 BEEN SERVICED WITH AEROSHELL 15W50 OIL SINCE COMPLETING NORMAL BREAKING. SUBMITTER STATED THIS SAME CONDITION HAS BEEN	 NOTED ON OTHER CONTINENTAL ENGINES USING AEROSHELL 15W50.			1	L	7	2 	3O	3	O		A23CE 	E8CE				 
1995110600042	19951106	00042	SO 	1995	11	6	95ZZZX5946 	2	19950925	G	8520	530184A2	CONNECTING ROD 			CESSNA	170 	170B 	2072306	CE 	CONT 	C145 	C1452 	17012	SO 					NR 6 CYLINDER	BROKEN 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	03	2209D	3600 				20361	6241D12			NR 6 CONNECTING ROD FRACTURED APPROXIMATELY 2 INCHES BELOW PISTON SKIRT. BREAK SHOWED EVIDENCE OF PROGRESSION OVER TIME	. FINAL FRACTURE WAS APPROXIMATELY ONE-HALF THE DIAMETER OF THE ROD WITH SOME MINOR CORROSION EVIDENT ALONG THE BEGINNI	NG OF THE CRACK. AREA OF BREAK WAS CONSISTENT WITH A STRESS RELATED BUILD-UP CAUSED BY NICKING THE ROD THROUGH POOR MAI	NTENANCE HANDLING DURING OVERHAULS. ENGINE HAD TWO MAJORS AND A TOP OVERHAUL LOGGED. MAGNAFLUXED AT LAST OVERHAUL.			1	H	7	1 	3O	3	O		A799 	E253				 
1995110600043	19951106	00043	SO 	1995	11	6	95ZZZX5947 	1	19950827	G	3220	3200	TAILWHEEL 	SCOTTAVATION		MAULE 	M5 	M5235C 	5460135	SO 										TAIL GEAR	PAWL BROKEN 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			NM	07	9281E				14969	7155C				AIRCAFT CRASHED ON RUNWAY DESTROYING MAIN LANDING STRUCTURE, PROP STRIKE, AND DAMAGE TO LEFT WING TIP. PILOT REPORTED N	O LEFT TAILWHEEL STEERING. DURING DISASSEMBLY AND INSPECTION, ONE PAWL WAS BROKEN ON TAILWHEEL ASSEMBLY.					1	H	7	1 	3O				3A23 					 
1995110600056	19951106	00056	CE 	1995	11	6	95ZZZX5948 	1	19950819	G	3213	1048100445	TORQUE KNEE 			BEECH 	58 	58P 	1152744	CE 										RT MLG UPPER	BUSHING MISSING 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	05	112Z	184 				TJ371				DURING A PROGRESSIVE INSPECTION, MAINTENANCE FOUND RT MLG UPPER TORQUE KNEE MISSING OUTBOARD BUSHING, PN 60-810024. THE	 TORQUE KNEE, PN 104-8100445, COMES FROM THE MANUFACTURER WITH THESE BUSHINGS INSTALLED. BEECH HAS NO APPROVED FIELD RE	PAIR CRITERIA FOR REPLACING THESE BUSHINGS. SUBMITTER STATED THIS MALFUNCTION HAS OCCURRED ON SAME TYPE AIRCRAFT PREVIO	USLY.			1	L	7	2 	3O				A23CE 					 
1995110600057	19951106	00057	SO 	1995	11	6	95ZZZX5949 	1	19950929	G	8120	60051004B	HOUSING 	ROTOMASTER 	3AT6EE10J2 	PIPER 	PA28 	PA28R201T 	7102813	SO 	CONT 	O360 	TSIO360FB 	17025	SO 					TURBO EXHAUST	CRACKED 	B				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	8088D	940 			212901	287921043	248060R			DURING COMPLIANCE WITH AD 82-27-03 AND AFTER REMOVING THE EXHAUST HOUSING OF THE TURBOCHARGER, A CRACK, APPROXIMATELY .7	5 INCH LONG, WAS NOTED IN THE WEB AREA NEAR THE INLET. PARAGRAPH J OF THE AD STATES THE 200-HOUR REPETITIVE INSPECTION 	REQUIREMENT IS RELIEVED IF THIS PART NUMBER IS INSTALLED. CRACKS OF THIS NATURE ARE ALLOWABLE IN THE OTHER CASTINGS OF 	EARLIER MANUFACTURE. SINCE NO DATA WAS AVAILABLE ON THIS P/N, IT WAS REPLACED.			1	L	7	1 	3O	3	O		2A13 	E9CE				 
1995021000081	19950210	00081	SO 	1995	2	10	95ZZZX595 	1	19950111	G	5712	8311203	RIB 			PIPER 	PA46 	PA46310P 	7104605	SO 										WS 93	DAMAGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	4375P	2095 				468508031				UPON 100-HOUR INSPECTION, FOUND WING SURFACE DISTORTED, SKINS CREASED ON LOWER SURFACE WS 93.00 AT MAIN SPAR. REMOVAL O	F SKIN REVEALED LOWER SPAR CAP BENT, SPAR WEB CREASED AND RIBS DAMAGED. CAUSE UNKNOWN. SPAR CAP TOO WEAK AT JACK POINT	S.				1	L	7	1 	3O				A25SO 					 
1995110600058	19951106	00058	SO 	1995	11	6	95ZZZX5950 	1	19950911	G	7160	3225002	SUPPORT RING 			PIPER 	PA23 	PA23250 	7102308	SO 										AIR FILTER	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	54854	4200 				277554154				PREMATURE ENGINE OVERHAUL MAY HAVE BEEN A RESULT OF WORN FILTER SUPPORT RINGS. EDGES OF RING FLANGES WERE ABOUT 50 PERC	ENT MISSING. THE ALUMINUM PIECES PRESUMABLY WERE INGESTED INTO ENGINES. THESE RINGS WERE NOT REPLACED AT O/H IN 1992, 	BUT BOTH REPLACED AT 1995 ANNUAL. HOW MUCH OF THE FLANGES HAVE BEEN INGESTED SINCE 1992 IS UNKNOWN.				1	L	7	2 	3O				1A10 					 
1995110600059	19951106	00059	CE 	1995	11	6	95ZZZX5951 	1	19950928	G	5312	971230412	BULKHEAD 			CESSNA	180 	180 	2072602	CE 										FS 172	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	4661A					32258				AT ANNUAL INSPECTION, FOUND BULKHEAD CRACKED AT THE 12:00 O'CLOCK POSITION BETWEEN THE RIVETS THAT ATTACH DORSAL FIN ATT	ACH FITTING. IT IS DIFFICULT TO SEE WHEN INSPECTING AND EASILY MISSED. A SMALL DOUBLER SHOULD BE INSTALLED WHEN THE VE	RTICAL STABILIZER IS REMOVED PER AC 43.13-1A. BULKHEAD SHOULD BE INSPECTED EACH 200 HOURS UNTIL A DOUBLER IS INSTALLED.	 PART TT, 2,686.0 HOURS.			1	H	7	1 	3O			NC	5A6 					 
1995110600060	19951106	00060	SW 	1995	11	6	95ZZZX5952 	1	19950901	G	7160	94008505	AIR CONTROL 			MOONEY	M20 	M20F 	5870214	SW 										ALTERNATE AIR	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	05	3506N					680076				INSTALLED CONTROL AND FOUND THREADED BULKHEAD SLEEVE TO BE 6 INCHES SHORT OF FIREWALL. INSPECTED MOONEY DWG 940088 DATE	D 8-28-95 AND FOUND DIMENSIONALLY WRONG FOR MODEL AIRCRAFT. THIS PART IS LISTED AS A RETROFIT WITH A MOVEABLE THREADED 	SLEEVE (SLEEVE IS CRIMPED AT BOTH ENDS).				1	L	7	1 	3O				2A3 					 
1995110600061	19951106	00061	SO 	1995	11	6	95ZZZX5953 	1	19950918	G	3243		MASTER CYLINDER 			AYRES 	S2 	S2AAYRES 	0143002	SO 										RT BRAKE	FAILED 	H				O				OTHER 				O			OTHER 			LD	LANDING 	1			EA	07	4977C					1020				POST-INCIDENT INVESTIGATION FOUND RIGHT MASTER BRAKE CYLINDER NOT ACTUATING RIGHT BRAKE. BRAKE ON RIGHT MAIN GEAR DOOR 	NOT FUNCTIONING. WHEN BOTH BRAKES WERE APPLIED, AIRCRAFT TURNED LEFT AND HIT OBJECTS OFF THE RUNWAY CAUSING SUBSTANTIAL	 DAMAGE TO THE AIRCRAFT. AIRCRAFT DIRECTIONAL CONTROL COULD NOT BE MAINTAINED WITH THIS CONDITION.				1	L	7	1 	3R				2A9 					 
1995110600063	19951106	00063	CE 	1995	11	6	95ZZZX5955 	1	19950922	G	2510	4102381	FLOORBOARD 			CESSNA	150 	152 	2071835	CE 										RT SEAT INBD	CRACKED 	G	P		YQSV	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	6318M	6238 				15284670				DURING REPLACEMENT OF SEAT RAILS, THE FLOORBOARD WAS FOUND CRACKED AT THE AFT END OF THE RT SEAT INBOARD SEAT RAIL. THE	 AREA AFT OF THE LT SEAT INBOARD SEAT RAIL SHOWS SIGNS OF CHAFING. THE NEW AND OLD RAILS ARE NOT ROUNDED OFF AND HAVE S	HARP EDGES WHICH MAY HAVE CONTRIBUTED TO THIS CRACKING PROBLEM. THIS IS THE SECOND OCCURRENCE FOR THIS OPERATOR. SUBMIT	TER RECOMMENDS DRESSING RAILS WITH A FILE.			1	H	7	1 	3O			NT	3A19 					 
1995110600064	19951106	00064	GL 	1995	11	6	95ZZZX5956 	3	19950926	G	6114		HUB 			CESSNA	340 	340A 	2076405	CE 						MCAULY	3AF32C	3AF32C93 	GL 	NR 3 SOCKET	CRACKED 	H	P	A		K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	27	1373G					340A0072		791233		DURING ROUTINE ACFT INSPECTION, PROPELLER HUB WAS VISUALLY INSPECTED FOR CONDTIION. NR 3 BLADE SOCKET WAS LEAKING GREAS	E. LARGE CRACK IN BLADE SOCKET WALL WAS FOUND. THE CRACK ORIGINATES AT THE FIRST FULL SOCKET THREAD INBOARD AND HAS PR	OGRESSED THROUGH THE HUB WALL AND THROUGH THE OUTBOARD LIP. MCCAULEY SB 209 AND SL 1993-11 ADDRESSES THIS PROBLEM. BLA	DE SEPARATION WAS IMMINENT. HUB IS SCRAP.			1	L	7	2 	3O				3A25 		5	C	P22EA	 
1995110600065	19951106	00065	CE 	1995	11	6	95ZZZX5957 	1	19950921	G	2434	1101912	GENERATOR 	DELCO 		CESSNA	182 	182G 	2072716	CE 										FIELD COIL	SHORTED 	B	L		AW4R	O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			WP	11	3289S				45746	18255789				INVESTIGATION FOR COCKPIT ODOR FOUND UPON OPENING THE BATTERY COMPARTMENT, THE BATTERY WAS EXTREMELY HOT AND MOST OF THE	 ELECTROLYTE HAD BOILED OUT. TROUBLESHOOTING REVEALED THE FIELD COIL HAD GROUNDED OUT IN THE GENERATOR.					1	H	7	1 	3O			NT	3A13 					 
1995110600066	19951106	00066	SW 	1995	11	6	95ZZZX5958 	1	19950915	G	7120	620032506	MOUNT 			GULSTM	500 	500S 	0141107	SW 										CAST BEAM	CORRODED 	B		A	HI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	9038N	5471 				3050				FOUND MOUNT CORROSION BETWEEN PLATE AND CAST BEAM ON ALL FOUR SIDES. AREA BETWEEN PLATE OF BEAM CAN HOLD MOISTURE. REC	OMMEND REMOVE PLATES, CLEAN CORROSION, FILL WITH PRC, AND REASSEMBLE. REPAIR WILL REQUIRE DER.					1	H	7	2 	3O				6A1 					 
1995110600067	19951106	00067	SW 	1995	11	6	95ZZZX5959 	1	19950915	G	7120	620032508	MOUNT 			GULSTM	500 	500S 	0141107	SW 										CAST BEAM	CORRODED 	B			HI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	1938S	4559 				3167				FOUND MOUNT CORROSION BETWEEN PLATE AND CAST BEAM ON ALL FOUR SIDES. AREA BETWEEN PLATE AND BEAM CAN HOLD MOISTURE. RE	COMMEND REMOVE PLATES, CLEAN CORROSION. FILL WITH PRC AND REASSEMBLE. REPAIR WILL REQUIRE DER.					1	H	7	2 	3O				6A1 					 
1995021000082	19950210	00082	SO 	1995	2	10	95ZZZX596 	1	19950111	G	5730		SKIN 			PIPER 	PA46 	PA46310P 	7104605	SO 										WS 93	DISTORTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	4375P	2095 				468508031				UPON 100-HOUR INSPECTION, FOUND WING SURFACE DISTORTED, SKINS CREASED ON LOWER SURFACE WS 93.00 AT MAIN SPAR. REMOVAL O	F SKIN REVEALED LOWER SPAR CAP BENT, SPAR WEB CREASED AND RIBS DAMAGED. CAUSE UNKNOWN. SPAR CAP TOO WEAK AT JACK POINT	S.				1	L	7	1 	3O				A25SO 					 
1995110600068	19951106	00068	WP 	1995	11	6	95ZZZX5960 	1	19950920	G	5511	H2310016	SPAR 			NANCNG	CJ6A 	CJ6A 	056183N	WP 										HORIZ STAB FWD	CRACKED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09						0320004				IMPORTED FROM CHINA, EXPERIMENTAL EXHIBITION CERTIFICATION PENDING. DURING INSPECTION PRIOR TO FAA CERTIFICATION, MECHA	NIC DISCOVERED CRACK IN FORWARD SPAR ASSEMBLY OF HORIZONTAL STABILIZER IN AREA BETWEEN VERTICAL STABILIZER TO HORIZONTAL	 STABILIZER ATTACH POINT. THIS AIRCRAFT HAD NOT BEEN OVERHAULED, REBUILT BY MFG PRIOR TO SALE AND EXPORT TO U. S. BUYER	. ONE OF FIVE AIRCRAFT WITH THIS AREA FOUND CRACKED.			1	L	7	1 	3R			RT	EXPA1L71					 
1995110600069	19951106	00069	WP 	1995	11	6	95ZZZX5961 	1	19950920	G	5511	H2310016	SPAR 			NANCNG	CJ6A 	CJ6A 	056183N	WP 										HORIZ STAB FWD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	457AB	2586 				1232004				IMPORTED FROM CHINA, EXPERIMENTAL EXHIBITION CERTIFICATION PENDING. DURING INSPECTION PRIOR TO FAA CERTIFICATION, MECHA	NIC DISCOVERED CRACK IN FORWARD SPAR ASSEMBLY OF HORIZONTAL STABILIZER IN AREA BETWEEN VERTICAL STABILIZER TO HORIZONTAL	 STABILIZER ATTACH POINT. THIS AIRCRAFT HAD NOT BEEN OVERHAULED, REBUILT BY MFG PRIOR TO SALE AND EXPORT TO U. S. BUYER	. ONE OF FIVE AIRCRAFT WITH THIS AREA FOUND CRACKED.			1	L	7	1 	3R			RT	EXPA1L71					 
1995110600070	19951106	00070	WP 	1995	11	6	95ZZZX5962 	1	19950920	G	5511	H2310016	SPAR 			NANCNG	CJ6A 	CJ6A 	056183N	WP 										HORIZ STAB FWD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	59WT					1232010				IMPORTED FROM CHINA, EXPERIMENTAL EXHIBITION CERTIFICATION PENDING. DURING INSPECTION PRIOR TO FAA CERTIFICATION, MECHA	NIC DISCOVERED CRACK IN FORWARD SPAR ASSEMBLY OF HORIZONTAL STABILIZER IN AREA BETWEEN VERTICAL STABILIZER TO HORIZONTAL	 STABILIZER ATTACH POINT. THIS AIRCRAFT HAD NOT BEEN OVERHAULED, REBUILT BY MFG PRIOR TO SALE AND EXPORT TO U. S. BUYER	. ONE OF FIVE AIRCRAFT WITH THIS AREA FOUND CRACKED.			1	L	7	1 	3R			RT	EXPA1L71					 
1995110600071	19951106	00071	WP 	1995	11	6	95ZZZX5963 	1	19950920	G	5511	H2310016	SPAR 			NANCNG	CJ6A 	CJ6A 	056183N	WP 										HORIZ STAB FWD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09						1232009				IMPORTED FROM CHINA, EXPERIMENTAL EXHIBITION CERTIFICATION PENDING. DURING INSPECTION PRIOR TO FAA CERTIFICATION, MECHA	NIC DISCOVERED CRACK IN FORWARD SPAR ASSEMBLY OF HORIZONTAL STABILIZER IN AREA BETWEEN VERTICAL STABILIZER TO HORIZONTAL	 STABILIZER ATTACH POINT. THIS AIRCRAFT HAD NOT BEEN OVERHAULED, REBUILT BY MFG PRIOR TO SALE AND EXPORT TO U. S. BUYER	. ONE OF FIVE AIRCRAFT WITH THIS AREA FOUND CRACKED.			1	L	7	1 	3R			RT	EXPA1L71					 
1995110600072	19951106	00072	WP 	1995	11	6	95ZZZX5964 	1	19950920	G	5511	H2310016	SPAR 			NANCNG	CJ6A 	CJ6A 	056183N	WP 										HORIZ STAB FWD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	357AB	2350 				1432023				IMPORTED FROM CHINA, EXPERIMENTAL EXHIBITION CERTIFICATION PENDING. DURING INSPECTION PRIOR TO FAA CERTIFICATION, MECHA	NIC DISCOVERED CRACK IN FORWARD SPAR ASSEMBLY OF HORIZONTAL STABILIZER IN AREA BETWEEN VERTICAL STABILIZER TO HORIZONTAL	 STABILIZER ATTACH POINT. THIS AIRCRAFT HAD NOT BEEN OVERHAULED, REBUILT BY MFG PRIOR TO SALE AND EXPORT TO U. S. BUYER	. ONE OF FIVE AIRCRAFT WITH THIS AREA FOUND CRACKED.			1	L	7	1 	3R			RT	EXPA1L71					 
1995110600073	19951106	00073	SW 	1995	11	6	95ZZZX5965 	1	19950919	G	7160		AIR BOX VALVE 			BBAVIA	7 	7AC 	2110102	SW 										ENGINE INTAKE	FAILED 	G		A		A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			GL	23	84458	3556 				7AC3153				THE SPOT WELD WHICH ATTACHES THE BUTTERFLY VALVE TO THE SHAFT BROKE WHICH ALLOWED THE VALVE TO BE SUCKED UP INTO THE CAR	BURETOR AND BLOCK OFF THE AIR TO THE ENGINE. THIS CAUSED THE ENGINE RPM TO DROP TO 700 RPM. THE PILOT LANDED IN A PLOW	ED FIELD, NO FURTHER DAMAGE TO AIRCRAFT.				1	H	7	1 	3O				A759 					 
1995110600074	19951106	00074	EU 	1995	11	6	95ZZZX5966 	1	19950926	G	5753	T700A5755097001	CARRIAGE 			SOCATA	TBM 	TBM700 	8682000	EU 										RT FLAP	CRACKED 	B		A	OLKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	157JB	1535 				6				WHILE COMPLYING WITH SB 70-048-57, A CRACK WAS FOUND IN THE LOWER WEB OF THE RIGHT FLAP INBOARD CARRIAGE, ONE INCH FROM 	THE AFT ROLLER STUD. CRACK WAS BEYOND ALLOWABLE STOP DRILL LIMITS IAW THIS SB. PART WAS CHANGED WITH NEW PART NUMBER W	HICH HAS BEEN MODIFIED WITH THICKER WEBS. SUBMITTER SUGGESTS OPERATORS WHO HAVE NOT C/W THIS SB SHOULD DO SO BEFORE FUR	THER FLIGHTS.			1	L	7	1 	3T			RT	A60EU 					 
1995110600076	19951106	00076	SO 	1995	11	6	95ZZZX5968 	1	19950928	G	3230	7873903	LINK ATTACH 			PIPER 	PA28 	PA28181 	7102807	SO 										RT MLG TORQUE	CRACKED 	D	S		OKDV	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	6912D	9522 				288590052				DURING MAINTENANCE, VISUALLY DISCOVERED CRACK .50 INCH LONG ON RT MLG AXLE STUB OUTBOARD TORQUE LINK ASSY POINT. FURTHE	R EXAMINATION DISCOVERED CRACK EXTENDED 1 INCH LONG INSIDE OF THE MACHINED AREA. AREA BARELY VISIBLE DUE TO LUBRICANTS/	DIRT ON THE PART. SUSPECT CAUSE IS FATIGUE.				1	L	7	1 	3O				2A13 					 
1995110600077	19951106	00077	SO 	1995	11	6	95ZZZX5969 	1	19951009	G	5751	4619015	SPAR 		4020041 	PIPER 	PA31 	PA31350 	7103110	SO 										RT AILERON	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	74972	3800 				317305123				ON COMPLIANCE WITH PIPER SB 974, AILERON HINGE INSPECTION AND REPLACEMENT, FOUND BOTH AILERON SPAR AND RIB CRACKED ON BO	TH LEFT AND RIGHT AILERONS. CRACKS NOT VISIBLE UNLESS AILERON HINGE BRACKETS ARE REMOVED.					1	L	7	2 	3O				A20SO 					 
1995021000083	19950210	00083	SO 	1995	2	10	95ZZZX597 	1	19950111	G	2820	9804472	LINE 			PIPER 	PA28 	PA28161 	7102803	SO 										RT FUEL	CORRODED 	B	P		DYTR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	15	163ER	7945 				2841144				THE PROBLEM WAS FOUND DURING AN INSPECTION TO FIND THE SOURCE OF A HEAVY FUEL SMELL IN THE AIRCRAFT CABIN. THE LEAK WAS	 FOUND IN THE FUEL LINE ON THE RIGHT SIDE OF THE CABIN AS IT ENTERED INTO THE AIRCRAFT CABIN THROUGH THE WING ROOT. THE	 CAUSE OF THE LEAK WAS A HOLE THAT HAD CORRODED THROUGH. THE CORROSION HAD OCCURRED DUE TO THE MOISTURE RETENSION OF TH	E OLD STYLE PAPER FUEL LINE LABEL. TO PREVENT THIS FROM RECURRING, THE OLD STYLE PAPER LABELS MUST BE REMOVED, AND THE 	FUEL LINE CLEANED, TREATED, AND NEW PLASTIC LABELS INSTALLED.		1	L	7	1 	3O				2A13 					 
1995110600078	19951106	00078	SO 	1995	11	6	95ZZZX5970 	1	19951009	G	5751	4019008	SPAR 		4020022 	PIPER 	PA31 	PA31350 	7103110	SO 										LT AILERON	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	74972	3800 				317305123				ON COMPLIANCE WITH PIPER SB 974, AILERON HINGE INSPECTION AND REPLACEMENT, FOUND BOTH AILERON SPAR AND RIB CRACKED ON BO	TH LEFT AND RIGHT AILERONS. CRACKS NOT VISIBLE UNLESS AILERON HINGE BRACKETS ARE REMOVED.					1	L	7	2 	3O				A20SO 					 
1995110600079	19951106	00079	CE 	1995	11	6	95ZZZX5971 	1	19950810	G	3240	215284	BRAKE ASSY 	BFGOODRICH 		CESSNA	500 	550 	2076604	CE 										WHEEL	DEFECTIVE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	75ZA		309 			5500214				INSTALLED THE BF GOODRICH WHEEL BRAKES ON CESSNA 550 APPROXIMATELY ONE YEAR AGO TO TAKE ADVANTAGE OF THE GUARANTEED PROR	ATED 1,000 LANDING LIFE OF THIS WHEEL BRAKE ASSYS. THE PROBLEM IS THAT THE WHEEL BRAKES ARE ONLY LASTING APPROX 300-400	 LANDINGS BEFORE THE ROTORS IN THESE BRAKES ARE CRACKING OR BREAKING COMPLETELY IN TWO. HAVE HAD TWO WHEEL BRAKES LOCK 	UP COMPLETELY WITHIN THE LAST 2 MONTHS DUE TO WHEEL BRAKE ROTOR FAILURE.			1	L	7	2 	4F				A22CE 					 
1995110600080	19951106	00080	CE 	1995	11	6	95ZZZX5972 	1	19950925	G	5321	24113954604	FLOOR SKIN 			LEAR 	35 	36A 	5170603	CE 										FS 346-370	DELAMINATING 	B		A	TJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	36BP	3520 				032				WHILE PRESSURIZING AIRCRAFT FOR 1,200 HOUR INSPECTION, AIRCRAFT WOULD NOT MAKE ALLOWABLE LEAK RATE. FOUND LOWER SKIN OF	 DIVAN SEAT FLOOR SITTING ON TOP OF WING SKIN WITH AIRCRAFT PRESSURIZED. FOUND UPPER AND LOWER DIVAN SEAT SKIN SEPARATI	NG FROM THE HONEYCOMB CENTER OF THE FLOOR WITH AIRCRAFT UNPRESSURIZED. LOWER SKIN WOULD RETURN TO ITS NORMAL POSITION. 	 ALSO, FOUND FLOOR SUPPORT STRINGER CRACKED DUE TO THE MOVEMENT OF THE FLOOR STRUCTURE. FOUND UNSEALED WELL NUTS AND PO	P RIVETS IN UPPER SKIN THAT WOULD ALLOW PRESSURIZATION INTO HONEYCOMB STRUCTURE.		2	L	7	2 	4F				A10CE 					 
1995110600081	19951106	00081	CE 	1995	11	6	95ZZZX5973 	1	19950922	G	5321	4102381	FLOORBOARD 			CESSNA	150 	152 	2071835	CE 										RT SEAT INBD	CRACKED 	G	P		YQSV	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	64901	8068 				15281467				DURING ROUTINE REPLACEMENT OF SEAT RAILS, THE FLOORBOARD WAS FOUND CRACKED AT THE AFT END OF THE RIGHT SEAT INBOARD SEAT	 RAIL. THE NEW AND OLD SEAT RAILS ARE NOT ROUNDED OFF AND HAVE SHARP EDGES WHICH MAY HAVE CONTRIBUTED TO THIS CRACKING 	PROBLEM. SUBMITTER RECOMMENDS DRESSING EDGES WITH FILE.				1	H	7	1 	3O			NT	3A19 					 
1995110600082	19951106	00082	SO 	1995	11	6	95ZZZX5974 	1	19950919	G	2710	62701127	CONTROL CABLE 			PIPER 	PA34 	PA34220 	 	SO 										WS 70.5	WORN 	B		A	ECPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	9195E					3433170				LEFT AND RIGHT FORWARD AILERON CABLES ARE BEING WORN BY THE PULLEY AT WS 70.5. THE PULLEY AT THE STATION CARRIES NO LOA	D FROM THE CABLE TENSION. IT APPEARS THAT IN-FLIGHT VIBRATION IS CUTTING THE CABLE IN HALF. NO PULLEYS HAVE BEEN FOUND	 FROZEN OR DAMAGED. OPERATOR HAS FLEET OF 5 AND PROBLEM IS APPARENT IN ALL.				1	L	7	2 	3O			 	A7SO 					 
1995110600083	19951106	00083	CE 	1995	11	6	95ZZZX5975 	1	19950926	G	2731	965260211	ACTUATING ROD 			BEECH 	58 	58 	1152740	CE 										LT ELEV TRIM	BROKEN 	G		A		A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			CL	CLIMB 	1			SO	16	4375W	3800 				TH489				SHORTLY AFTER DEPARTURE, ACFT BEGAN A VIOLENT SHAKING AND FLUTTER. PILOT REDUCED SPEED AND RETURNED TO AIRPORT. PILOT	 STATED THE ACFT WAS ALMOST UNABLE TO BE CONTROLLED. AN UNEVENTFUL LANDING WAS MADE. INSP REVEALED THE LT ELEV TRIM TA	B ACTUATING ROD HAD BROKEN APPROX 1 INCH FROM THE END WHERE IT ATTACHED AT THE JACK SCREW. THIS APPARENTLY ALLOWED TRIM	 TAB TO FLUTTER AND THIS ACTION WAS FED BACK TO THE CONTROL YOKE. BREAK OCCURRED AT A POINT THAT REMAINS WELL WITHIN TH	E CONFINES OF THE HORIZ STAB. SUBMITTER SUGGESTS INSPECTION OF THIS AREA ON INSPECTING THE AD CONCERNING THE RIVET REPL	ACEMENT HAD BEEN C/W.	1	L	7	2 	3O				3A16 					 
1995110600084	19951106	00084	EU 	1995	11	6	95ZZZX5976 	1	19950926	G	5753	T700A5755097000	CARRIAGE 			SOCATA	TBM 	TBM700 	8682000	EU 										LT FLAP	CRACKED 	B			OLKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	157JB	1535 				6				WHILE C/W SB 70-048-57, 2 CRACKS WERE FOUND. ONE IN THE LOWER WEB OF THE LT FLAP INBOARD CARRIAGE, ONE INCH FROM THE AF	T ROLLER STUD, AND THE OTHER IN THE VERTICAL WEB, .3750 INCH FROM THE FORWARD ROLLER STUD. BOTH CRACKS WERE BEYOND ALLO	WABLE STOP DRILL LIMITS IAW THIS SB. PART WAS CHANGED WITH NEW P/N WHICH HAS BEEN MODIFIED WITH THICKER WEBS. SUBMITTE	R SUGGESTS OPERATORS WHO HAVE NOT C/W THIS SB SHOULD DO SO BEFORE FURTHER FLIGHTS.			1	L	7	1 	3T			RT	A60EU 					 
1995110600085	19951106	00085	SW 	1995	11	6	95ZZZX5977 	1	19951005	G	3246		WHEEL 			MOONEY	M20 	M20J 	5870219	SW 										NLG	WRONG PART 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15	201EL					240144				HAD TO REMOVE WRONG NOSE WHEEL. AIRCRAFT CALLS FOR CLEVELAND WHEEL, P/N 40-87. ALSO, FOUND SEVERE CORROSION AND WRONG 	BOLTS AND NUTS.					1	L	7	1 	3O				2A3 					 
1995110600086	19951106	00086	SO 	1995	11	6	95ZZZX5978 	1	19950920	G	3230	6701200	TORQUE LINK 			PIPER 	PA28 	PA28R180 	7102809	SO 										LT MLG	BROKEN 	H				O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			WP	13	312CA	3447 				28R30590				PILOT REPORTED LANDING GEAR WOULD NOT RETRACT. TROUBLESHOOTING FOUND LT LANDING GEAR UPPER TORQUE LINK INBOARD LUG CRAC	KED AND BROKEN CAUSING SAFETY (SQUAT) SWITCH ACTIVATING CLIP NOT TO ACTIVATE SWITCH ARM. REPLACED TORQUE LINK WITH NEW 	PART. LUG HAD APPARENT CORROSION IN OLD FRACTURE LEADING TO FAILURE. SUSPECT CAUSE, OVERTORQUEING DURING A PREVIOUS AS	SEMBLY, SETTING UP A STRESS ON LINK LUG. SUBMITTER RECOMMENDS ADHERING TO MANUFACTURES MAINTENANCE INSTRUCTIONS WHEN IN	STALLING.		1	L	7	1 	3O				2A13 					 
1995110600087	19951106	00087	SW 	1995	11	6	95ZZZX5979 	1	19950918	G	3220		TAILWHEEL 	SCOTT 		BBAVIA	8 	8GCBC 	1220803	SW 										MAIN SHAFT	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	03	8592V	8125 	150 			14975				THE TAILWHEEL MAIN SHAFT SHEARED AT THE 'STEP' (SHANK DIAMETER CHANGES) CAUSING THE TIRE, FORK, AND ASSORTED INTERNAL PA	RTS TO DEPART THE AIRCRAFT. THIS TAILWHEEL HAS APPROX 25,000 LANDINGS AND TAKEOFFS ON IT. SUSPECT CAUSE OF FAILURE IS 	FATIGUE DUE TO EXTENDED USE.				1	H	7	1 	3O				A21CE 					 
1995021000084	19950210	00084	SO 	1995	2	10	95ZZZX598 	1	19950113	G	2820	9804472	LINE 			PIPER 	PA28 	PA28161 	7102803	SO 										RT FUEL	CORRODED 	B		A	DYTR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	15	162ER	7477 				2841152				THE PROBLEM WAS FOUND DURING AN INSPECTION FOR THE SOURCE OF A HEAVY FUEL SMELL IN THE CABIN. THE LEAK WAS FOUND IN THE	 FUEL LINE ON THE RIGHT SIDE OF THE CABIN AS IT CAME THROUGH THE WING ROOT. THE CAUSE OF THE LEAK WAS A HOLE THAT HAD C	ORRODED THROUGH. THE CORROSION HAD OCCCURED DUE TO MOISTURE COLLECTING IN THE OLD STYLE PAPER FUEL LINE TAG. THE PREVEN	T THIS FROM RECURRING, THE OLD STYLE PAPER LABELS MUST BE REMOVED, THE FUEL LINES CLEANED, TREATED, AND NEW PLASTIC LABE	LS INSTALLED. THIS IS THE THIRD AIRCRAFT FOUND THIS MONTH.		1	L	7	1 	3O				2A13 					 
1995110600088	19951106	00088	EU 	1995	11	6	95ZZZX5980 	2	19950907	G	8530	850710	OIL SEAL 			AMTR 	FLTSTR	FLIGHTSTAR 	05644KB	GL 	ROTAX 	582 	ROTAX582 	55555	EU 					ROTARY VALVE	LEAKING 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	09	93FS	86 				093	4317143			AFTER TOTAL ENGINE FAILURE WITH NO WARNING, ROTARY VALVE SHAFT WAS FOUND DEFECTIVE. ROTARY VALVE SPLINES WERE FOUND MEL	TED OFF. FAILURE WAS FOUND TO BE DUE TO ROTARY VALVE OIL BEING DILUTED BY WATER. WATER WAS FOUND IN ROTARY VALVE OIL T	ANK. SEAL HAD FAILED. INSPECTED THREE OTHER AIRCRAFT AND FOUND SAME PROBLEM. SUBMITTER STATED THIS IS AN EXPERIMENTAL	 AIRCRAFT, BUT A PROBLEM NEEDS TO BE ADDRESSED.			1	H	7	1 	3I	3	I		EXPA1H71	EXPE3I				 
1995110600089	19951106	00089	CE 	1995	11	6	95ZZZX5981 	1	19950920	G	3233	1053840023	ACTUATOR 			BEECH 	76 	76 	1153005	CE 										MLG	ROD BROKE 	B			SYVR	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			WP	19	2008K					ME72				LEFT MLG ACTUATOR ROD BROKE AT THE THREADED END DURING GEAR RETRACTION. THE GEAR FREE-FELL AND LOCKED IN THE DOWN POSIT	ION. THE GEAR WAS MOVED UP AND DOWN BY HAND AND NO BINDING OR LOOSENESS WAS FOUND. NEW ACTUATOR WAS INSTALLED AND THE 	LANDING GEAR WAS OPERATED SEVERAL TIMES WITHOUT ANY PROBLEMS. WHY THE PART BROKE IS UNCLEAR, BUT IT APPEARS TO HAVE BEN	T BEFORE IT BROKE.			1	L	7	2 	3O				A29CE 					 
1995110600268	19951106	00268	EA 	1995	11	6	95ZZZX5982 	2	19951004	G	8530		CYLINDER 			PIPER 	PA60 	PA60600 	7106001	NM 	LYC 	O540 	IO540K1J5 	41532	EA 					LT ENG NR 4	SEPARATED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	05	6892R					600887816125	L1888448A			LEFT ENGINE NR 4 CYLINDER SEPARATED FROM ENGINE. CAUSE UNKNOWN AT THIS TIME. REMOVED AND REPLACED ENGINE, PROPELLER, A	ND ACCESSORIES.					1	M	7	2 	3O	3	O	RT	A17WE 	1E4				 
1995110600269	19951106	00269	CE 	1995	11	6	95ZZZX5983 	1	19950905	G	3230		LANDING GEAR 			CESSNA	310 	310R 	2074245	CE 										MLG	MALFUNCTION 	H				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			GL	07	6160X					310R1305				GEAR WOULD NOT EXTEND. HAD INSPECTED AND FAA ISSUED FERRY PERMIT. JACKED ACFT, CHECKED WIRING AND SWITCHES. COULD NOT	 DUPLICATE, CYCLED GEAR SEVERAL TIMES.					1	L	7	2 	3O				3A10 					 
1995110600270	19951106	00270	SW 	1995	11	6	95ZZZX5984 	2	19950829	G	8500		ENGINE 			CESSNA	195 	195 	2073102	CE 	JACOBP	R755 	R755B1 	35007	SW 					POWERPLANT	FAILED 	D				A				UNSCHED LANDING 				E	B	R	VIBRATION/BUFFET 	SMOKE/FUMES/ODORS/SPARKS 	PARTIAL RPM/PWR LOSS 	CR	CRUISE 	1			SW	01	9368A					7447	11465			ON FIRST FLIGHT AFTER MAINTENANCE (STARTER REPLACEMENT) ON 8-29-95, 25 MINUTES INTO FLIGHT, HAD SUDDEN ONSET OF ENGINE V	IBRATION. HEADED TOWARD AIRPORT. WITHIN 1 MINUTE HAD COMPLETE LOSS OF OIL PRESSURE. OVER NEXT FEW MINUTES, HAD OIL TE	MP PAST RED LINE AND OFF SCALE, OIL PRESSURE REMAINED ZERO, VIBRATION WORSENED, HAD PARTIAL POWER LOSS, AND BURNING ODOR	. WAS ABLE TO RETURN AND LAND WITH PARTIAL POWER (ABOUT 10-12 INCHES MP). NO DAMAGE TO AIRFRAME. SUBSEQUENT INSPECTIO	N FOUND MECHANICAL PROBLEMS RELATED TO THE RECENT MAINTENANCE.		1	H	7	1 	3R	3	R	NC	A790 	TC237				 
1995110600271	19951106	00271	SO 	1995	11	6	95ZZZX5985 	2	19950616	G	8530	639272	CYLINDER 			CESSNA	185 	A185E 	2072818	CE 	CONT 	O520 	IO520D 	17032	SO 					NR 5	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	1997U		300 			18501766	175979R			DURING AN INSPECTION OF THE ENGINE, THE NR 5 CYLINDER WAS FOUND CRACKED BETWEEN THE TOP SPARK PLUG HOLE AND INJECTOR NOZ	ZLE HOLE. INVESTIGATION REVEALED THE MAGNETO TO ENGINE TIMING WAS 10 DEGREES ADVANCED. AFTER THE NR 5 CYLINDER WAS REM	OVED, THE PISTON, PISTON PIN, AND CONNECTING ROD WERE FOUND TO SHOW SIGNS OF EXCESSIVE HEAT. THE NR 2 CYLINDER WAS THEN	 PULLED AS A PRECAUTIONARY MEASURE AND WHILE THE CYLINDER WAS NOT CRACKED, THE PISTON, PISTON PIN, AND CONNECTING ROD WE	RE ALL FOUND HEAT-DAMAGED. THE ENGINE WAS THEN REMOVED FROM SERVICE AND THE OVERHAUL FACILITY CONTACTED REGARDING THIS 	DISCREPANCY. REFERENCE SB M84-8 AND SB M94-8.	1	H	7	1 	3O	3	O		3A24 	E5CE				 
1995110600272	19951106	00272	EA 	1995	11	6	95ZZZX5986 	2	19950921	G	8530		FLANGE 								LYC 	O320 	O320* 	41508	EA 					INTAKE PIPE	WARPED 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	05										ORDERED NEW INTAKE FLANGES FROM FACTORY. FOUND WARPED. THIS CONDITION COULD LEAD TO BURNED VALVES AND POWER LOSS.											3	O			E274				 
1995110600273	19951106	00273	CE 	1995	11	6	95ZZZX5987 	1	19950913	G	3297	YGD20	WIRE 			CESSNA	172 	172RG 	2072438	CE 										NLG SWITCH	FAILED 	D				O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			SW	03	6461V	2861 				172RG0716				LANDING GEAR FAILED TO COMPLETELY RETRACT WHEN SELECTED. CAUSE WAS DETERMINED TO BE BROKEN WIRE FOR SQUAT SWITCH WHICH 	WAS SHIELDED INSIDE VINYL TUBING WHICH HAD BECOME BRITTLE AND HARD CAUSING WIRE TO FLEX REPEATEDLY IN ONE SPOT.					1	H	7	1 	3O			 	3A17 					 
1995110600274	19951106	00274	SO 	1995	11	6	95ZZZX5988 	2	19950301	G	8550	632970	OIL PUMP 			CESSNA	340 	340A 	2076405	CE 	CONT 	O520 	TSIO520N 	17040	SO 					ENGINE	SEAL FAILED 	D				O				OTHER 				K	W		FLUID LOSS 	INADEQUATE Q C 		NR	NOT REPORTED 	1			GL	07	808TW	85 				34A0304	R508512			IN-FLIGHT, OIL PUMP CASE SEAL FAILURE. SILK THREAD DISPLACED FROM PARTING FLANGE. INSPECTIONS REVEALED WARP AT PARTING	 FLANGE. SILICONE USED BY OVERHAUL FACILITY TO SEAL FLANGE. THIS SHOP SUGGESTS FOLLOWING TCM DIRECTIVES FOR SEALER IN 	THIS AREA. SILICON SHOULD 'NOT' BE USED.				1	L	7	2 	3O	3	O		3A25 	E8CE				 
1995110600275	19951106	00275	CE 	1995	11	6	95ZZZX5989 	1	19950922	G	5312	07126161	BULKHEAD 			CESSNA	182 	182K 	2072724	CE 										AFT FUSELAGE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	02	3103F	5345 				18258103				AFT MOST BULKHEAD CRACKED AT UPPER LEFT RUDDER CONTROL CABLE HOLE.						1	H	7	1 	3O			NT	3A13 					 
1995021000085	19950210	00085	SW 	1995	2	10	95ZZZX599 	1	19950111	G	5521	442119	SPAR 			GULSTM	112 	114 	7630314	SW 										RT ELEV HINGE	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	5877N	2379 				14422				UPON REPLACEMENT OF OUTBOARD HINGE ATTACHMENT OF RT ELEVATOR, CRACKS WERE FOUND IN SPAR. INSPECTION OF LT ELEVATOR REVE	ALED SAME CRACKS ONLY WORSE. CRACKS ARE FOUND BY BOLT HOLES FOR OUTBOARD HINGE ATTACHMENTS. CRACKS CAN BE SEEN THROUGH	 HOLES IN OUTBOARD RIB WITH FLEXIBLE LIGHT, AFTER TIP IS REMOVED.				1	L	7	1 	3O				A12SO 					 
1995110600276	19951106	00276		1995	11	6	95ZZZX5990 	4	19950924	G	2562		ELT 	ACK 		CESSNA	150 	150 	2071802	CE 										BATTERY	FAILED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	1766Q				005839	15073066				ELT DID NOT OPERATE AFTER ACCIDENT, MID-AIR COLLISION. EXAMINATION OF BATTERIES, DURACELL, MN1300, REVEALED THAT THEY A	LL WERE LOW, 1.25V OR LESS. BATTERIES WERE HEAVILY CORRODED AS WERE THE ELT CONTACTS. THE NEGATIVE BATTERY LEAD APPEAR	S NOT TO HAVE BEEN SOLDERED TO THE BATTERY CONTACT. THE CIRCUIT BOARD HAS A CONCENTRATION OF BATTERY ACID IN THE AREA A	ROUND THE BATTERY CONTACTS. A TEST OF THE BOARD INDICATES THE UNIT WAS UNABLE TO TRANSMIT. UNIT IS A TSO-C912.			1	H	7	1 	3O			NT	3A19 					 
1995110600277	19951106	00277	GL 	1995	11	6	95ZZZX5991 	3	19950925	G	6114	B3334	COLLAR 			BEECH 	300 	300BEECH 	1152930	CE 						HARTZL	HCB4M	HCB4M 	GL 	PROP LOW STOP	RING DEBONDS 	B		A	JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09								FW669		BEECH KING AIR 300 PROP LOW STOP COLLAR DEBONDS AT RING THAT PROVIDES COLLAR LOCATION ON A.C. THIS IS POTENTIALLY DAMAG	ING TO SEVERAL COMPONENTS IN THE IMMEDIATE AREA OF THE LOW STOP COLLAR. FOUR REPORTS ON RING DEBONDED ON 4 PROPS.					2	L	7	2 	4T				A24CE 		6	C	P56GL	 
1995110600278	19951106	00278	GL 	1995	11	6	95ZZZX5992 	3	19950925	G	6114	B3334	COLLAR 			BEECH 	300 	300BEECH 	1152930	CE 						HARTZL	HCB4M	HCB4M 	GL 	PROP LOW STOP	RING DEBONDED 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09								FW487		BEECH KING AIR 300 PROP LOW STOP COLLAR DEBONDS A RING THAT PROVIDES COLLAR LOCATION ON A.C. THIS IS POTENTIALLY DAMAGI	NG TO SEVERAL COMPONENTS IN THE IMMEDIATE AREA OF THE LOW STOP COLLAR.					2	L	7	2 	4T				A24CE 		6	C	P56GL	 
1995110600279	19951106	00279	GL 	1995	11	6	95ZZZX5993 	3	19950925	G	6114	B3334	COLLAR 			BEECH 	300 	300BEECH 	1152930	CE 						HARTZL	HCB4M	HCB4M 	GL 	PROP LOW STOP	RING DEBONDED 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09								FW672		BEECH KING AIR 300 PROP LOW STOP COLLAR DEBONDS A RING THAT PROVIDES COLLAR LOCATION ON A.C. THIS IS POTENTIALLY DAMAGI	NG TO SEVERAL COMPONENTS IN THE IMMEDIATE AREA OF THE LOW STOP COLLAR.					2	L	7	2 	4T				A24CE 		6	C	P56GL	 
1995110600280	19951106	00280	GL 	1995	11	6	95ZZZX5994 	3	19950925	G	6114	B3334	COLLAR 			BEECH 	300 	300BEECH 	1152930	CE 						HARTZL	HCB4M	HCB4M 	GL 	PROP LOW STOP	RING DEBONDED 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09								FW626		BEECH KING AIR 300 PROP LOW STOP COLLAR DEBONDS A RING THAT PROVIDES COLLAR LOCATION ON A.C. THIS IS POTENTIALLY DAMAGI	NG TO SEVERAL COMPONENTS IN THE IMMEDIATE AREA OF THE LOW STOP COLLAR.					2	L	7	2 	4T				A24CE 		6	C	P56GL	 
1995110600281	19951106	00281	GL 	1995	11	6	95ZZZX5995 	3	19951010	G	6111	808021	BLADE PIN 			CESSNA	210 	210L 	2073448	CE 						MCAULY	3A32C	D3A32C88 	GL 	PROPELLER	BROKEN 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	13	59210				4460	21060161		808021		DISASSEMBLED PROPELLER, FOUND ONE BLADE PIN BROKEN. BROKEN PIN WAS FOUND TO HAVE BEEN GROUND SHORT ON STONE AND NOT MAC	HINED AS SB NR 99 SECTION C STATES. REMAINING TWO BLADE PINS WERE FOUND OVERTORQUED BY AT LEAST 5 POUNDS PER MANUAL 720	415.				1	H	7	1 	3O				3A21 		5	C	P21EA	 
1995110600282	19951106	00282	CE 	1995	11	6	95ZZZX5996 	1	19950929	G	5210	504300431183	INTERCOSTAL 			BEECH 	100 	100BEECH 	1152916	CE 										CABIN DOOR AFT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	93BC	7375 				B41				INSPECTION FINDS SEVERAL INTERCOSTALS CRACKED EACH YEAR. THE WORKING OF AND STRESS THAT RESULTS FOR USING THE CABIN AIR	STAIR DOOR IS THE CAUSE OF THE INTERCOSTAL CRACKING. SUBMITTER RECOMMENDATION IS FOR A FORWARD CABIN AIRSTAIR DOOR SUPP	ORT CABLE.				1	L	7	2 	3T				A14CE 					 
1995110600283	19951106	00283	CE 	1995	11	6	95ZZZX5997 	1	19951006	G	2432	563800561	BATTERY 	GILLBATT 		BEECH 	60 	B60 	1153605	CE 										CELL	SHORTED 	G				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	23	100RE					P570				LEAD/ACID BATTERY SHORTED BETWEEN CELLS CAUSING BATTERY TO OVERHEAT AND LOSS OF POWER.						1	L	7	2 	3O				A12CE 					 
1995110600284	19951106	00284	CE 	1995	11	6	95ZZZX5998 	1	19951005	G	3222	05430181	CAP 			CESSNA	172 	172D 	2072410	CE 										NLG STRUT	FAILED 	B			S6AR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CE	01	2089Y					17249589				NLG STRUT CAP THAT HOLDS STRUT HOUSING TO ENGINE MOUNT, FAILED. FOUND BOLT MISSING. SUSPECT HARD LANDING AFTER BOLT CA	ME LOOSE AS CONTRIBUTING FACTOR.					1	H	7	1 	3O			NT	3A12 					 
1995110600285	19951106	00285	CE 	1995	11	6	95ZZZX5999 	1	19951012	G	3230	35815109	CONTROL CABLE 			BEECH 	33 	F33A 	1151425	CE 										LT UPLOCK	FRAYED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	625JP	776 				CE1503				DURING ROUTINE INSPECTION, LEFT UPLOCK CABLE WAS FOUND HEAVILY FRAYED. JACKED A/C AND RETRACTED GEAR TO CHECK CABLE TEN	SION. RIGHT UPLOCK CABLE TENSION WAS 75 POUNDS. CORRECT CABLE TENSION IS 52 AND ONE-HALF, PLUS 10 OR MINUS ZERO, POUND	S. SUBMITTER RECOMMENDS CAREFUL CHECK OF UPLOCK CABLE TENSION AT ANNUAL INSPECTION OR AT ANY TIME THE LANDING GEAR RETR	ACT SYSEM IS BEING WORKED ON.			1	L	7	1 	3O			 	3A15 					 
1995021000086	19950210	00086	SW 	1995	2	10	95ZZZX600 	1	19950111	G	5521	4421110	SPAR 			GULSTM	112 	114 	7630314	SW 										LT ELEV HINGE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	5877N	2379 				14422				UPON REPLACEMENT OF OUTBOARD HINGE ATTACHMENT OF RT ELEVATOR, CRACKS WERE FOUND IN SPAR. INSPECTION OF LT ELEVATOR REVE	ALED SAME CRACKS ONLY WORSE. CRACKS ARE FOUND BY BOLT HOLES FOR OUTBOARD HINGE ATTACHMENTS. CRACKS CAN BE SEEN THROUGH	 HOLES IN OUTBOARD RIB WITH FLEXIBLE LIGHT, AFTER TIP IS REMOVED.				1	L	7	1 	3O				A12SO 					 
1995110600286	19951106	00286		1995	11	6	95ZZZX6000 	1	19951011	G	2510	44466021	LAP BELT 	AMERICANSFTY	4455552 															BELT HALF	BROKEN 	B			PS9R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05										ITEM RETURNED FOR REPAIR TO REPAIR STATION. RETRACTOR WOULD NOT RETRACT STRAP. PART HAD BEEN 'RENOVATED RECENTLY PER F	AR NR 43' PER TAG ON PART. TAG DID NOT IDENTIFY BELT MAKERS REPAIR STATION LICENSE NUMBER.																		 
1995110600287	19951106	00287	EU 	1995	11	6	95ZZZX6001 	1	19950928	G	2820		VENT LINE 			SLNSBY	T67 	T67M260 	8323006	EU 										COCKPIT	FUEL FUMES 	D				O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			TO	TAKEOFF 	1			SW	17	3047K	337 				2147				AIR CREW REPORTED A STRONG SMELL OF FUEL WHEN FULL POWER WAS SET FOR TAKEOFF. FUEL TANK VENT LINES ARE ROUTED IN COCKPI	T AND OUT THROUGH BELLY OF AIRCRAFT. SUSPECT FUEL FUMES COMING IN FROM AROUND VENT LINES.					1	L	7	1 	3O			NT	A73EU 					 
1995110600288	19951106	00288	EU 	1995	11	6	95ZZZX6002 	1	19950928	G	2820		VENT LINE 			SLNSBY	T67 	T67M260 	8323006	EU 										COCKPIT	FUEL FUMES 	D				O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			TO	TAKEOFF 	1			SW	17	3037T	453 				2136				AIR CREW REPORTED A STRONG SMELL OF FUEL WHEN FULL POWER WAS SET FOR TAKEOFF. FUEL TANK VENT LINES ARE ROUTED IN COCKPI	T AND OUT THROUGH BELLY OF AIRCRAFT. SUSPECT FUEL FUMES COMING IN FROM AROUND VENT LINES.					1	L	7	1 	3O			NT	A73EU 					 
1995110600289	19951106	00289	EU 	1995	11	6	95ZZZX6003 	1	19951005	G	2434	ALU8421LS	ATERNATOR 			SLNSBY	T67 	T67M260 	8323006	EU 										DC SYSTEM	DEFECTIVE 	D				O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			SW	17	3189K	19 			4121131	2211				ALTERNATOR LIGHT CAME ON DURING FLIGHT. TESTED ALTERNATOR AND FOUND TO BE DEFECTIVE.						1	L	7	1 	3O			NT	A73EU 					 
1995110600290	19951106	00290	EU 	1995	11	6	95ZZZX6004 	1	19951005	G	2434	ALU842ALS	ALTERNATOR 	ELECTROSYS 		SLNSBY	T67 	T67M260 	8323006	EU 										DC SYSTEM	DEFECTIVE 	D				O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			SW	17	3189W	13 			4121135	2214				ALTERNATOR LIGHT CAME ON DURING FLIGHT. TESTED AND FOUND DEFECTIVE.						1	L	7	1 	3O			NT	A73EU 					 
1995110600291	19951106	00291	EU 	1995	11	6	95ZZZX6005 	1	19951005	G	2434	ALU8R21LS	ALTERNATOR 	ELECTROSYS 		SLNSBY	T67 	T67M260 	8323006	EU 										DC SYSTEM	DEFECTIVE 	D				O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			SW	17	3190H	23 			4121122	2215				ALTERNATOR LIGHT CAME ON DURING FLIGHT. TESTED AND FOUND DEFECTIVE.						1	L	7	1 	3O			NT	A73EU 					 
1995110600292	19951106	00292	CE 	1995	11	6	95ZZZX6006 	1	19950918	G	5751	05238001	AILERON 			CESSNA	172 	172D 	2072410	CE 										LT LOWER LE SKIN	RIVET FAULTY 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	500BB	6989 				17249768				DURING ANNUAL INSPECTION, FOUND 6 RIVET HEADS MISSING ON LOWER SKIN OF RIGHT AILERON WHERE BALANCE WEIGHTS ARE ATTACHED 	AND SKIN WAS LOOSE. FOUND ONE RIVET NEXT TO THESE WITH BLISTERED PAINT, THAT WHEN SCRAPED WITH FINGERNAIL, THE HEAD POP	PED OFF. AILERON SKIN BENEATH THESE HEADS WAS CLEAR OF CORROSION. CHECKING LEFT AILERON, ONE RIVET HEAD WAS MISSING IN	 SAME GENERAL LOCATION. OWNER OF ACFT CHECKED 3 OTHER SIMILAR PLANES AND FOUND ONE OF THE 172'S HAD SIMILAR PROBLEM. R	IVETS WILL BE DRILLED OUT AND REPLACED.		1	H	7	1 	3O			NT	3A12 					 
1995110600293	19951106	00293	CE 	1995	11	6	95ZZZX6007 	1	19950918	G	5751	05238000	AILERON 			CESSNA	172 	172D 	2072410	CE 										RT LOWER LE SKIN	RIVET FAULTY 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	500BB	6989 				17249768				DURING ANNUAL INSPECTION, FOUND 6 RIVET HEADS MISSING ON LOWER SKIN OF RIGHT AILERON WHERE BALANCE WEIGHTS ARE ATTACHED 	AND SKIN WAS LOOSE. FOUND ONE RIVET NEXT TO THESE WITH BLISTERED PAINT, THAT WHEN SCRAPED WITH FINGERNAIL, THE HEAD POP	PED OFF. AILERON SKIN BENEATH THESE HEADS WAS CLEAR OF CORROSION. CHECKING LEFT AILERON, ONE RIVET HEAD WAS MISSING IN	 SAME GENERAL LOCATION. OWNER OF ACFT CHECKED 3 OTHER SIMILAR PLANES AND FOUND ONE OF THE 172'S HAD SIMILAR PROBLEM. R	IVETS WILL BE DRILLED OUT AND REPLACED.		1	H	7	1 	3O			NT	3A12 					 
1995110600294	19951106	00294	SO 	1995	11	6	95ZZZX6008 	1	19950925	G	8120	LW18822	INTERCOOLER 			PIPER 	PA31 	PA31P350 	7103111	SO 	LYC 	O540 	LTIO540V2AD 	41533	EA 					LT SUPPORT BRCKT	CRACKED 	B			FGQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	50RN	153 				31P8414013	RL269968A			INSPECTION FOUND A CRACK INITIATED IN THE RADIUS OF A MACHINED AREA FOR THE LT SUPPORT BRACKET, AND PROPOGATED FORE AND 	AFT. THIS IS THE SECOND FAILURE FOUND OF THIS TYPE ON THE MOJAVE INTERCOOLERS. CURRENTLY, THERE ARE NO NEW PARTS AVAIL	ABLE AND NO REPAIR DATA AVAILABLE.				1	L	7	2 	3O	3	O	RT	A8EA 	E14EA				 
1995110600295	19951106	00295	EA 	1995	11	6	95ZZZX6009 	2	19951005	G	8530	73806P	PUSH ROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					NR 1-4 EXHAUST	DAMAGED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NE	03	4648L					15284205	L2282415			DURING A 100-HOUR INSPECTION, A SMALL DENT IN NR 1 AND NR 4 EXHAUST PUSH ROD SHROUDS WAS DETECTED. THEY SEEMED TO BE LE	AKING OIL. A FURTHER INSPECTION OF THE PUSH RODS REVEALED A VERY DEEP GROOVE OR CHANNEL WORN INTO THEM WHERE THE DENT I	N THE SHROUD WAS LOCATED. REPLACED ALL PUSH RODS IN NR 1 AND NR 4 CYLINDERS ALONG WITH THE RESPECTIVE SHROUDS. SUSPECT	 NR 1 EXHAUST PUSH ROD HAD DAMAGE CAUSED BY A ROCK KICKED UP BY THE PROPELLER.			1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995021000087	19950210	00087	SW 	1995	2	10	95ZZZX601 	1	19950111	G	3230	1TL1493D	SWITCH 			MOONEY	M20 	M20C 	5870208	SW 										MLG	FAILED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	9313V	2556 			6912	690091				MOVED GEAR SWITCH (HANDLE) TO DOWN POSITION. GEAR REMAINED IN UP POSITION. CYCLED SWITCH UP THEN DOWN AND GEAR MOVED D	OWN NORMAL. WHEN OPERATIONAL CHECK PERFORMED, MOVED SWITCH TO GEAR DOWN AND GEAR STAYED UP. WIGGLED SWITCH IN DOWN POS	ITION AND GEAR CAME DOWN. SEVERAL CYCLES WERE PERFORMED AND SWITCH WORKED ABOUT HALF OF THE CYCLES. INSTALLED NEW SWIT	CH AND GEAR OPERATED NORMALLY. HIGH TIME AIRCRAFT SHOULD HAVE THIS SWITCH REPLACED TO PREVENT A GEAR-UP LANDING.			1	L	7	1 	3O				2A3 					 
1995110600296	19951106	00296	CE 	1995	11	6	95ZZZX6010 	1	19951005	G	3234	25800	SELECTOR VALVE 			BEECH 	200 	B200 	1152922	CE 										MLG RETRACT	DEFECTIVE 	B			LX5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	961LL		194 		1077	BB1139				THIS UNIT IS PART OF STC SA4378WP, HYDRAULIC LANDING GEAR RETRACTION SYSTEM. LANDING GEAR SELECTOR VALVE BYPASSING FLUI	D INTERNALLY.					1	L	7	2 	4T				A24CE 					 
1995110600297	19951106	00297	CE 	1995	11	6	95ZZZX6011 	1	19951017	G	7922	75944	VALVE 			CESSNA	172 	172 	2072402	CE 										THERMO BYPASS	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	8943B	298 				36643				THIS VALVE HAS VERY LITTLE TIME ON IT. SUBMITTER STATED 80 PERCENT OF ALL VALVES INSPECTED WITH THIS PIN HAVE FAILED IN	SPECTION IAW SB S18B. RECOMMEND SB BE MADE INTO AN AD.					1	H	7	1 	3O			NT	3A12 					 
1995110600596	19951106	00596	CE 	1995	11	6	95ZZZX6012 	1	19951003	G	2752	C3010020312	ACTUATOR 			CESSNA	182 	182H 	2072718	CE 										FLAP JACKSCREW	REQUIRED LUBE 	D				O				OTHER 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			GL	27	2034X	4503 				18256134				PILOT REPORTED FLAPS WOULD NOT EXTEND IN-FLIGHT, BUT FUNCTION PROPERLY ON THE GROUND. FOUND JACKSCREW HAD NOT BEEN LUBE	D IAW CESSNA MANUALS, BULLETINS, AND AD, AND HAD WORN OUT JACKSCREW AND COLLAR. INSTALLED NEW UNIT.					1	H	7	1 	3O			NT	3A13 					 
1995110600597	19951106	00597	SO 	1995	11	6	95ZZZX6013 	2	19951004	G	8530	24047	GUIDE 			CESSNA	172 	172E 	2072412	CE 	CONT 	O300 	O300D 	17022	SO 					NR 2 CYL EXH	DEFECTIVE 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			GL	27	3809S	284 				1725109	28327030			PILOT REPORTED ENGINE RUNNING ROUGH. COMPRESSION CHECK CYLINDERS, ALL 70/80 OR BETTER. SPARK PLUG INSPECTION SHOWED NR	 2 CYLINDER NOT FIRING PROPERLY. FOUND NR 2 EXHAUST VALVE STICKING. REAMED GUIDE AND RETURNED TO SERVICE.					1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995110600598	19951106	00598	SO 	1995	11	6	95ZZZX6014 	2	19951012	G	7414	K3823	DISTRIBUTOR GEAR	SLICK 	6210 	CESSNA	206 	TU206G 	2073357	CE 	CONT 	O520 	TSIO520M 	17040	SO 					RT MAG	DESTROYED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			CE	03	6352Z		583 		6010051	U20606250	520381			PILOT EXPERIENCED ROUGH ENGINE. UPON LANDING AND GROUND RUN-UP, RIGHT MAGNETO WAS DISCOVERED DEAD. DISASSEMBLY SHOWED 	THAT ELECTRODE POSTS IN DISTRIBUTOR BLOCK ASSEMBLY HAD COME IN CONTACT WITH ELECTRODE FINGER ON DISTRIBUTOR GEAR. ELECT	RODE FINGER WAS TORN AWAY FROM GEAR AND GEAR WAS ABOUT ONE-HALF MELTED AWAY. NEW MAGNETO WAS INSTALLED AND RUN-UP WAS G	OOD.			1	H	7	1 	3O	3	O		A4CE 	E8CE				 
1995110600599	19951106	00599	EA 	1995	11	6	95ZZZX6015 	2	19950808	G	8550	LW11252	OIL PUMP 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	LTIO540J2BD 	41533	EA 					ENGINE	SEIZED 	D				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CL	CLIMB 	1			SO	15	61367					317552088	L104468A			AIRCRAFT ON CLIMB-OUT AT 4,500 FEET OIL PUMP SEIZED AND SEVERAL ACCESSORY GEARS SHEARED INCLUDING CRANK GEAR CAUSING ENG	INE TO FAIL. AIRCRAFT LANDED, SINGLE ENGINE. TIME ON ENGINE, 1,139 HOURS SINCE MAJOR OVERAHUL.					1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995110600600	19951106	00600	CE 	1995	11	6	95ZZZX6016 	1	19951011	G	2752	505211516	PISTON 			BEECH 	300 	300BEECH 	1152930	CE 										LT FLAP ACTUATOR	CRACKED 	B			MZ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	911RB	1629 				FA217				DURING THE PERFORMANCE OF A REGULAR INSPECTION, THE PISTON FOR THE LT OUTBOARD FLAP ACTUATOR WAS FOUND CRACKED ALONG THE	 LENGTH OF THE PISTON. CAUSE OF CRACK IS UNKNOWN. THE FLAP WAS OPERATING NORMALLY.					2	L	7	2 	4T				A24CE 					 
1995110600601	19951106	00601	CE 	1995	11	6	95ZZZX6017 	1	19951013	G	7160	BA7210	AIR FILTER 	BRACKETT 		BEECH 	35 	V35 	1151538	CE 										INTAKE	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	5421U					D8507				AD95-03-02 SHOULD INCLUDE THIS BRACKETT, BA7210, AS WE FOUND THE GASKET MOVED FROM PROPER POSITION.						1	L	7	1 	3O				3A15 					 
1995110600602	19951106	00602	CE 	1995	11	6	95ZZZX6018 	1	19951002	G	3010	P610050	HOSE 		AK210160H 	CESSNA	210 	P210N 	2073454	CE 										TAIL-WING DEICE	FAILED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	731MU	1 				P21000498				UPON INSTALLATION OF DE-ICE KIT ONTO PARTIALLY CONNECTED SYSTEM, FIRST TEST OF DE-ICE SYSTEM, TAIL FAILED TO INFLATE. F	OUND NEW HOSE TO HAVE SPLIT. REPAIRED SPLIT. AIRCRAFT FLEW ONE HOUR, TAIL BOOTS FAILED TO INFLATE. FOUND 3 HOSES SPLI	T FOR TAIL BOOTS. REPAIRED HOSES. UPON NEXT TEST, LT OUTBOARD WING FAILED TO INFLATE. HOSE HAD BROKEN AT BOOT NIPPLE.	 REPLACED HOSE. NEXT TEST, TAIL FAILED TO INFLATE, FOUND 3 MORE HOSES FAILED, ONE AT HOSE TO BOOT NIPPLE.			1	H	7	1 	3O				3A21 					 
1995110600603	19951106	00603	GL 	1995	11	6	95ZZZX6019 	3	19951009	G	6114	C5480C66	HUB 													MCAULY	2A34C	2A34C66 	GL 	NR 2 SOCKEET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19					727893			727893		UPON INSPECTION, HUB WAS FOUND CRACKED IN NR 2 BLADE SOCKET. HUB HAS BEEN SCRAPPED.																5	C	P3EA	 
1995021000088	19950210	00088	CE 	1995	2	10	95ZZZX602 	1	19950109	G	3230	50410011	BELLCRANK 			CESSNA	401 	401 	207590C	CE 										LT MLG	FAILED 	C		A		K				NONE 				O			OTHER 			TX	TAXI/GRND HDL 	1			WP	07	1253B	6625 				4010031				WHILE AIRCRAFT WAS TAXIING, LT LANDING GEAR COLLAPSED. THE AIRCRAFT RECEIVED MODERATE DAMAGE. INVESTIGATION BY MAINTEN	ANCE PERSONNEL REVEALED BELLCRANK FAILED IN MULTIPLE AREAS ALLOWING MAIN DRAG LINK TO RETRACT BACK OVER CENTER. PREVENT	ION - REMOVE HIGH CYCLE ASSEMBLIES, 500-HOUR DYE PENETRANT INSPECTION, TAXI SLOWER WHEN CORNERING.				1	L	7	2 	3O				A7CE 					 
1995110600604	19951106	00604	CE 	1995	11	6	95ZZZX6020 	1	19950911	G	5312		BULKHEAD 			BEECH 	58 	58 	1152740	CE 										WEB FACE	CRACKED 	B		A	BA4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	5647C	6495 				TH1574				INSPECTION FOUND CRACKS IN WEB FACE, AREA HUCK BOLT FASTENER. SUBMITTER STATED SB 2269 AND AD 90-08-14 SERIAL NUMBERS S	HOULD BE UPGRADED TO INCLUDE TH-1574. THIS AIRCRAFT'S TOTAL TIME IS 6,495 HOURS.					1	L	7	2 	3O				3A16 					 
1995110600605	19951106	00605	EU 	1995	11	6	95ZZZX6021 	1	19951007	G	5531	TB1031000103	RIB 			SOCATA	TB20 	TB20TRINIDAD	8680695	EU 										VERTICAL STAB	RIVETS LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	20KP	837 				683				RIVETS IN VERTICAL STABILIZER AT RIB TB 10.31.000.103 LOOSENED CAUSING TOP OF STABILIZER TO BE LOOSE.						1	L	7	1 	3O			RT	A51EU 					 
1995110600606	19951106	00606		1995	11	6	95ZZZX6022 	1	19951011	G	7160	D9181	FILTER 	AIRBORNE 																INTAKE	SEAL FAILED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	07										NEW FILTER WAS TAKEN FROM BOX. SEAL ON TOP OF FILTER BROKE APART WHEN IT WAS TOUCHED. DATE ON BOX WAS 8-94. CHECKED 7	 OTHER FILTERS WITH SAME DATE. ALL WERE OK.																		 
1995110600607	19951106	00607	SO 	1995	11	6	95ZZZX6023 	1	19951005	G	7810	40C19819	FLANGE 			PIPER 	PA46 	PA46350P 		SO 										RT EXHAUST	ERODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	49PK	740 				4622050				FOUND A MASSIVE EXHAUST LEAK WHILE PERFORMING AN ENGINE 100-HOUR INSPECTION. CONNECTING FLANGE FOR NR 3 TO NR 5 EXHAUST	 WAS ERODED THROUGH ONE-THIRD OF CIRCUMFERENCE. NORMAL WEAR. SUBMITTER STATED CLOSER INSPECTION OF EXHAUST SYSTEM DURI	NG NORMAL OIL CHANGES.				1	L	7	1 	3O			RT	A25SO 					 
1995110600608	19951106	00608		1995	11	6	95ZZZX6024 	4	19951002	G	2210	KCD2A	RELAY 			BEECH 	MU300 	400BEECH 		CE 										AP PITCH TRIM	FAILED 	B		A	OG5R	K				NONE 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			GL	21	3038V	575 				RK93				AIRCRAFT HAS EXPERIENCED 3 DIFFERENT AUTOPILOT PITCH TRIM PROBLEMS AT AIRCRAFT TOTAL TIMES OF 164.1 HOURS, 311.7 HOURS, 	AND 886.3 HOURS. SAMPLE PROBLEMS ARE 'TRIM HORN BEEPS ON A/P ENGAGEMENT' OR 'A/P PITCH TRIM FAIL LIGHTS INTERMITTENTLY'	. TRIM SPEED ALSO SLOWS UP BEFORE FAILURE. ALL PROBLEMS WERE TRACED TO GROUP OF 3 RELAYS IN TRIM RELAY BANK. THESE AR	E 3 OF 4 FAILURES IN 2 A/C FLEET.			2	H	7	2 	4F			RT	A16SW 					 
1995110600609	19951106	00609	CE 	1995	11	6	95ZZZX6025 	1	19950918	G	5520		BALANCE WEIGHT 			BEECH 	90 	C90A 	1152911	CE 										RT ELEVATOR	SCREW LOOSE 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	476JA	4060 				LJ1161				DURING INSPECTION, ONE NAS 14411 SCREW WAS FOUND MISSING FROM THE RT ELEVATOR BALANCE WEIGHT WHICH SECURES THE BALANCE W	EIGHT TO THE ELEVATOR. A TORQUE CHECK OF THE REMAINING THREE SCREWS FOUND ALL OF THEM LOOSE. IN ADDITION, THE ELEVATOR	 BALANCE WEIGHT SCREWS ON THE LT ELEVATOR WERE ALSO LOOSE.				1	L	7	2 	3T			RT	3A20 					 
1995110600610	19951106	00610		1995	11	6	95ZZZX6026 	4	19951012	G	3418	2551A11	TRANSMITTER 	CONRAC 		AMD 	FALC10	FALCON10 	2730101	EU 										STALL SYS	EXPLODED 	B		A	GFER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	163AV	4808 			14412	163				DURING GROUND CHECKS, POWER WAS SUPPLIED TO THE STALL VANE HEATER. AT THAT MOMENT, A LOUD EXPLOSION WAS HEARD AND OILY 	SMOKE DETECTED IN THE COCKPIT. FURTHER INVEST REVEALED TRANSMITTER HAD, IN FACT, EXPLODED WITH ENOUGH FORCE TO BLOW OFF	 MECHANISM HOUSING AND INTERNAL TRANSMITTER COVER. INTERNAL MECH WAS FUSED AND MELTED. SURROUNDING EQUIP UNDAMAGED. N	O ANCILLIARY SYS CAUSE COULD BE IDENTIFIED AND LIKELY THE CAUSE WAS INTERNAL TO TRANSMITTER ITSELF. THE MECHANISM IS FI	LLED WITH A LUBRICANT WHICH WAS FOUND FLAMMABLE DURING AN INFORMAL SHOP TEST & IT IS LIKELY LUBRICANT CONTRIBUTED TO FOR	CE OF EXPLOSION. THE SYSTEM C/B DID NOT OPEN & WAS FOUND IN PROPER OPERATING CONDITION. UNIT REPLACED.	2	L	7	2 	4F				A33EU 					 
1995110600611	19951106	00611	CE 	1995	11	6	95ZZZX6027 	1	19950929	G	2841	L15H3	SWITCH 			CESSNA	500 	550 	2076604	CE 										LOW LEVEL FUEL	FAILED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	37201	330 			3417	550655				DURING DEFUEL, FOUND ANOTHER BAD LOW LEVEL SWITCH. EITHER THE WARNING LIGHT FAILS TO ILLUMINATE, OR IT STAYS LIT AFTER 	REFUELING. UPON REMOVAL, SWITCH USUALLY FEELS NORMAL, THAT IS, FREE MOVEMENT. RECORDS SHOWS 8 EACH CHANGED SWITCHES OV	ER THE PAST 2 YEARS. SWITCHES ARE KEYED FOR PROPER INSTALLATION SO THEY CAN ONLY MOUNT ONE WAY, AND ITS INTERNAL SWITCH	ING MECHANISM IS TRIGGERED BY MAGNETS IN THE FLOAT.			1	L	7	2 	4F				A22CE 					 
1995110600612	19951106	00612	CE 	1995	11	6	95ZZZX6028 	1	19950803	G	5210	0710620204	DOOR 			CESSNA	206 	P206B 	2073309	CE 										RT CABIN	DEPARTED 	G	S			O				OTHER 				D			INFLIGHT SEPARATION 			NR	NOT REPORTED 	1			GL	13	4794F	4068 				P2060394				RT CABIN DOOR WAS HEAVILY MODIFIED FOR SKY DIVING APPLICATIONS. FORWARD LATCH PIN WAS WORN AND ALLOWED DOOR TO UNLATCH 	IN-FLIGHT. DUE TO THE HIGH SPEEDS INVOLVED, THE DOOR BROKE IN HALF AND DEPARTED THE AIRCRAFT.					1	H	7	1 	3O				A4CE 					 
1995110600613	19951106	00613	CE 	1995	11	6	95ZZZX6029 	1	19950927	G	5312		BULKHEAD 			BEECH 	200 	200BEECH 	1152920	CE 										LT CABIN	CRACKED 	B	S		LX5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	971LL	10575				BB572				DURING PRIMARY INSPECTION, FOUND CRACKED BULKHEADS UNDER LEFT CABIN FLOOR, JUST FORWARD OF MAIN CABIN DOOR AREA. THREE 	ADJACENT BULKHEADS WERE CRACKING IN SAME AREA.					1	L	7	2 	4T				A24CE 					 
1995110600614	19951106	00614	CE 	1995	11	6	95ZZZX6030 	1	19950915	G	2821	652635015	ADAPTOR 			CESSNA	500 	550 	2076604	CE 										FUEL FILTER	MISMANUFACTURED 	B	L		JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	55WL					5500140				FOUND FUEL FILTER INLET FITTING O-RING EXTRUDED FROM FITTING. THERE WAS NO EVIDENCE OF FUEL LEAKING. DISCOVERED IMPROP	ERLY MACHINED LAND ON FITTING WOULD NOT ALLOW SEAL TO PROPERLY MATE WITH SEAL RECESS IN HOUSING. REPLACED FITTINGS WITH	 NEW PARTS WHICH DID NOT HAVE LANDS. LEAK CHECK NORMAL.				1	L	7	2 	4F				A22CE 					 
1995110600615	19951106	00615	CE 	1995	11	6	95ZZZX6031 	1	19951004	G	2821	7585751	FILTER ASSY 	PUROLATOR 		CESSNA	500 	550 	2076604	CE 										BOWL	SEPARATED 	B		A	UQRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	550CP	3058 			30	5500275				FILTER BOWL AND FILTER SEPARATED FROM FILTER HEAD/ASSEMBLY. THE HEILCOIL IN THE HEAD CASTING PULLED FROM HEAD. FUEL PR	ESSURE WAS LOST TO THE ASSOCIATED ENGINE. UPON FURTHER INSPECTION, THE OTHER FUEL FILTER ASSEMBLY WAS STARTING TO FAIL 	IN A SIMILAR WAY. SUSPECT CAUSE OF FAILURE IS OVERTIGHTENING OF FILTER HOLD-DOWN.				1	L	7	2 	4F				A22CE 					 
1995110600616	19951106	00616		1995	11	6	95ZZZX6032 	4	19950802	G	2562	1104	ELT 	ARTEX 		BEECH 	MU300 	400BEECH 		CE 										CASE	BROKEN 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	3038V	612 			53854	RK93				UPON SCHEDULED REMOVAL FOR INSPECTION, ELT BATTERY CASE WAS FOUND SPLIT OPEN AND LEAKING. CASE WAS SPLIT INTO SEVERAL P	IECES. AREA BETWEEN BATTERY PACK AND HEAD OF ELT APPEARED TO HAVE OVERHEATED. BATTERY IS MOUNTED UNDERNEATH AIR CONDIT	IONER CONDENSOR AND ABOVE ANTI-SKID CONTROL BOX. ALL ABOVE COMPONENTS ARE LOCATED BEHIND TAILCONE BAGGAGE COMPARTMENT. 	 IT IS NOT KNOWN IF ELT FAILED ON ITS OWN OR IF EXCESSIVE EXTERNAL HEAT WAS A FACTOR. INSTALLED NEW ELT'S. ELT INSPECT	ION FREQUENCY BEING INCREASED.		2	H	7	2 	4F			RT	A16SW 					 
1995110600617	19951106	00617		1995	11	6	95ZZZX6033 	4	19950814	G	2562	1104	ELT 	ARTEX 		BEECH 	MU300 	400BEECH 		CE 										CASE	LEAKING 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	3196N	13 			55035	RK96				ELT AND BATTERY WAS INSTALLED AS AN ASSEMBLY 8-2-95 AT A/C TT 601.4 HOURS. AT A/C TT 614.0 HOURS, ELT WAS FOUND LEAKING	 LIQUID THROUGH SPLIT LINE OF ELT CASE. ELT TTSN IS 12.6 HOURS, 28 DAYS AFTER INSTALLATION.					2	H	7	2 	4F			RT	A16SW 					 
1995110600618	19951106	00618	CE 	1995	11	6	95ZZZX6034 	1	19950818	G	3010	45AS660109	HEAT MAT 			BEECH 	MU300 	400BEECH 		CE 										LT ELEV HORN	DELAMINATED 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	3196N	256 				RK96				DURING PILOT'S PRE-FLIGHT, DISCOVERED DELAMINATION ON LT ELEVATOR HORN HEAT MAT. NO DELAMINATION ALLOWED PER BEECH 400A	 MANUAL. REMOVED AND REPLACED LT ELEVATOR HORN HEAT MAT.					2	H	7	2 	4F			RT	A16SW 					 
1995110600619	19951106	00619	CE 	1995	11	6	95ZZZX6035 	1	19950303	G	3010	45AS6601010	HEAT MAT 			BEECH 	MU300 	400BEECH 		CE 										RT ELEV HORN	BURNED 	B			OG5R	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	21	3196N	64 				RK96				PILOT REPORTED TAIL ANTI-ICE FAILED IN-FLIGHT. INSPECTED AIRCRAFT, FOUND RT ELEVATOR HORN MAT BURNED. REMOVED AND REPL	ACED RT ELEVATOR HORN MAT IAW BEECH 400A MANUAL 30-10-00, PAGES 34 TO 39. ANTI-ICE AND DE-ICE FOR TAIL CHECKED GOOD.					2	H	7	2 	4F			RT	A16SW 					 
1995110600620	19951106	00620	CE 	1995	11	6	95ZZZX6036 	1	19950610	G	3010	45AS660109	HEAT MAT 			BEECH 	MU300 	400BEECH 		CE 										LT ELEV HORN	SHORTED 	B			OG5R	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	21	3038V	473 				RK93				PILOT REPORTED HORIZONTAL STABILIZER ANTI-ICE FAIL LIGHT IN THE AIR. INSPECTION OF SYSTEM REVEALED LT ELVATOR HORN HEAT	 MAT WAS BURNED. REPLACED LT ELEVATOR HEAT MAT. OPERATIONALLY CHECK GOOD.					2	H	7	2 	4F			RT	A16SW 					 
1995110600621	19951106	00621	CE 	1995	11	6	95ZZZX6037 	1	19950609	G	3010	45AS6601010	HEAT MAT 			BEECH 	MU300 	400BEECH 		CE 										RT ELEV HORN	CRACKED 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	3196N	341 				RK96				DURING 400-HOUR INSPECTION, MECHANIC FOUND RT ELEVATOR HORN HEAT MAT CRACKED AT TIP THROUGH BLACK CASTING AND ALUM. ANT	I-ICE DE-ICE SYSTEM STILL FUNCTIONING OKAY, BUT NO CRACKS ALLOWED IN PART PER BEECH 400A MANUAL. REMOVED AND REPLACED R	T ELEVATOR HORN HEAT MAT.				2	H	7	2 	4F			RT	A16SW 					 
1995110600622	19951106	00622		1995	11	6	95ZZZX6038 	4	19950802	G	2562	1104	ELT 	ARTEX 		BEECH 	MU300 	400BEECH 		CE 										CASE	BROKEN 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	3196N	601 			53777	RK96				UPON SCHEDULED REMOVAL FOR INSPECTION, ELT BATTERY CASE WAS FOUND SPLIT OPEN AND LEAKING. CASE WAS SPLIT INTO SEVERAL P	IECES. AREA BETWEEN BATTERY PACK AND HEAD OF ELT APPEARED TO HAVE OVERHEATED. BATTERY IS MOUNTED UNDERNEATH AIR CONDIT	IONER CONDENSOR AND ABOVE ANTI-SKID CONTROL BOX. ALL ABOVE COMPONENTS ARE LOCATED BEHIND TAILCONE BAGGAGE COMPARTMENT. 	 IT IS NOT KNOWN IF ELT FAILED ON ITS OWN OR IF EXCESSIVE EXTERNAL HEAT WAS A FACTOR. INSTALLED NEW ELT'S. ELT INSPECT	ION FREQUENCY BEING INCREASED.		2	H	7	2 	4F			RT	A16SW 					 
1995110600623	19951106	00623	NE 	1995	11	6	95ZZZX6039 	2	19950914	G	7313		NOZZLE 			LEAR 	25 	25 	5170506	CE 	GE 	CJ610 	CJ6106 	30006	NE 					1ST STAGE	DEFECTIVE 	D				O				OTHER 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			GL	07	121EL					010	251382			RT ENGINE FLAMED OUT AT 42,000 FEET. DISASSEMBLED ENGINE, SENT FIRST STAGE NOZZLE OUT FOR RE-WORK, REASSEMBLED ENGINE. 	 TEST FLIGHT OK.					2	L	7	2 	4J	4	J		A10CE 	1E16				 
1995021000208	19950210	00208	SO 	1995	2	10	95ZZZX604 	2	19950108	G	8500		ENGINE 			PIPER 	PA34 	PA34200T 	7103406	SO 	CONT 	O360 	LTSIO360EB 	17025	SO 					RT ENGINE	MALFUNCTIONED 	E	L		C2SA	A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			CE	01	24KG					348070309	312526			VFR FROM MARSHALLTOWN TO DSM. RT ENGINE QUIT, PILOT WENT THROUGH THE CHECK LIST AND FEATHERED THE ENGINE. THE FUEL SEL	ECTOR COULD NOT MOVE. THE A/C HAD BEEN STORED IN A HEATED HANGAR OVERNIGHT. OPERATOR TOOK SAMPLES OF FUEL AND NOTHING 	FOUND. TEST FLEW OKAY.				1	L	7	2 	3O	3	O		A7SO 	E9CE				 
1995110600624	19951106	00624	CE 	1995	11	6	95ZZZX6040 	1	19950911	G	3213		STRUT 			LEAR 	25 	25 	5170506	CE 										LT MLG	FAILED 	C				K				NONE 				O			OTHER 			LD	LANDING 	1			SO	17	155AG					037				AIRCRAFT INVOLVED IN HEAVY LANDING CAUSING LEFT MAIN STRUT TO FAIL. AIRCRAFT WAS ON APPROACH WHEN AIRCRAFT WAS ABOUT TO	 LAND AND WIND-DOWN FORCE CAUSED AIRCRAFT TO HIT RUNWAY HARD.					2	L	7	2 	4J				A10CE 					 
1995110600625	19951106	00625		1995	11	6	95ZZZX6041 	4	19951002	G	2210	KCD2A	RELAY 			BEECH 	MU300 	400BEECH 		CE 										AP PITCH TRIM	FAILED 	B			OG5R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	21	3196N	478 				RK96				AUTOPILOT PITCH TRIM FAILED 2 TIMES IN FLIGHT. PROBLEM TRACED TO RELAYS IN PITCH TRIM RELAY BANK. THREE NEW RELAYS INS	TALLED AND PROBLEM WAS CORRECTED. THIS IS 1 OF 4 OCCURRENCES IN 2 AIRCRAFT FLEET.					2	H	7	2 	4F			RT	A16SW 					 
1995110600626	19951106	00626	NE 	1995	11	6	95ZZZX6042 	2	19951003	G	7240	3008822	RIVET 			CESSNA	500 	500CESSNA 	2076602	CE 	PWA 	JT15 	JT15D1 	52060	NE 					LEFT ENGINE	SHEARED 	B			SI6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	88GJ	4222 				5000155	76332			DURING A HOT SECTION INSPECTION, RIVETS IN THE SUPPORT RING THAT HOLD THE DEFLECTOR SEGMENTS WERE FOUND MISSING. PIECES	 OF THE MISSING RIVETS WERE FOUND THROUGHOUT THE AFT END OF THE ENGINE. THE HIGH PRESSURE TURBINE BLADE TIPS WERE FOUND	 DAMAGED DUE TO THE RIVETS. ALL 71 BLADES WERE REPLACED ON THE HIGH PRESSURE TURBINE DISC ASSEMBLY DUE TO THE DAMAGE IN	FLICTED BY THE RIVETS.			1	L	7	2 	4F	4	F		A22CE 	E1NE				 
1995110600627	19951106	00627	WP 	1995	11	6	95ZZZX6043 	1	19951011	G	2910	ER9196D	REDUCER 			CVAC 	440 	440 	2422902	WP 										LT MLG WELL	FAILED 	B			GMCR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	23	5124					507				THREADED BARREL OF REDUCER FITTING FAILED AT BASE OF THREADS CAUSING SUBSEQUENT HYDRAULIC LEAKAGE A LT MAIN LANDING GEAR	 RELIEF VALVE LOCATED IN LEFT MAIN LANDING GEAR WW. AIRCRAFT LANDED WITHOUT INCIDENT AT DTW.					2	L	7	2 	4R				6A6 					 
1995110600628	19951106	00628	CE 	1995	11	6	95ZZZX6044 	1	19950919	G	3610	99120432	REGULATOR 	LUCAS 		CESSNA	500 	550 	2076604	CE 										PNEUMATIC	GASKET FAILED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5314J	500 			RF2073	550663				AT ALMOST EVERY PHASE INSPECTION, FIND THE 23 PSI PNEU REGULATOR LEAKING BLEED AIR DUE TO BLOWN GASKET. REGULATOR IS LO	CATED NEXT TO THE AFT PRESSURE BULKHEAD AND PROVIDES PNEUMATIC PRESSURE FOR DE-ICE BOOTS, INSTRUMENTS, AND PRESSURIZATIO	N CONTROL. ALSO, FOUND CAP SCREW ON CAP WITH ALMOST NO TORQUE AT ALL.				1	L	7	2 	4F				A22CE 					 
1995110600629	19951106	00629	NM 	1995	11	6	95ZZZX6045 	1	19951010	G	2910		LINE 			BOEING	747 	747122 	1384872	NM 										LT WING FAIRING	CRACKED 	B			GK4Y	A				UNSCHED LANDING 				B	K		SMOKE/FUMES/ODORS/SPARKS 	FLUID LOSS 		CR	CRUISE 	1			WP	03	854FT					19754				DURING CRUISE, FLIGHT DECK HAD HYDRAULIC FUMES. AIRCRAFT RETURNED TO NADI. FOUND 2 HYD LINES CRACKED IN LT WING FAIRIN	G AREA. LINES REPAIRED AND OTHER INSP CARRIED OUT AS REQUIRED. FULL REPORT WILL BE IN MAIL.					2	L	7	4 	4F				A20WE 					 
1995110600630	19951106	00630	EU 	1995	11	6	95ZZZX6046 	1	19951010	G	2750	3803007010	BEVEL GEAR 		3803008401 	FOKKER	F27 	F27MK400 	4990626	EU 										FLAP GEARBOX	TEETH WORN 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	08	2MIL	5841 			213	10652				100CT95 5817.4 ACFT HOURS/6,165 LANDING CYCLES. FLAP SPINDLE GEARBOX, STA 4155 (RT) HAS METAL PARTICLES IN OIL DRAINED 	FROM GEARBOX IN ONLY 821 CYCLES SINCE OVERHAUL NORMAL TBO, 5,000 LANDING CYCLES. VISUAL INSPECTION REVEALED 0.035 INCH 	AXIAL MOVEMENT IN OUTPUT SHAFT CONNECTED TO FLAP JACKSCREW. INTERNAL INSPECTION REVEALED EXCESSIVE WEAR ON BEVEL GEAR T	EETH. WEAR THOUGHT TO BE FROM IMPROPER SHIMMING OF SHAFT THRUST BEARING AND AIR LOADS ON AIRCRAFT FLAPS BEING TRANSFERR	ED TO BEVEL GEAR TEETH INSTEAD OF THRUST BEARING. THRUST BEARING RACES DO NOT SHOW SIGNS OF LOSS OF METAL.		2	H	7	2 	4T				A817 					 
1995110600631	19951106	00631	EU 	1995	11	6	95ZZZX6047 	1	19951010	G	2750	3803007011	BEVEL GEAR 		3803008401 	FOKKER	F27 	F27MK400 	4990626	EU 										FLAP GEARBOX	TEETH WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	08	2MIL	5841 			213	10652				100CT95 5817.4 ACFT HOURS/6,165 LANDING CYCLES. FLAP SPINDLE GEARBOX, STA 4155 (RT) HAS METAL PARTICLES IN OIL DRAINED 	FROM GEARBOX IN ONLY 821 CYCLES SINCE OVERHAUL NORMAL TBO, 5,000 LANDING CYCLES. VISUAL INSPECTION REVEALED 0.035 INCH 	AXIAL MOVEMENT IN OUTPUT SHAFT CONNECTED TO FLAP JACKSCREW. INTERNAL INSPECTION REVEALED EXCESSIVE WEAR ON BEVEL GEAR T	EETH. WEAR THOUGHT TO BE FROM IMPROPER SHIMMING OF SHAFT THRUST BEARING AND AIR LOADS ON AIRCRAFT FLAPS BEING TRANSFERR	ED TO BEVEL GEAR TEETH INSTEAD OF THRUST BEARING. THRUST BEARING RACES DO NOT SHOW SIGNS OF LOSS OF METAL.		2	H	7	2 	4T				A817 					 
1995110600632	19951106	00632	CE 	1995	11	6	95ZZZX6048 	1	19951019	G	2700		CABLES 			CESSNA	501 	551 	2076605	CE 										FLAP/ELEV AIL	FRAYED 	B		A	LX4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	551CF					5510021				FOUND FLAP FOLLOW-UP CABLE, ELEVATOR CABLE, AND AILERON CABLE AT CONTROL LOCK ASSY FRAYED WITH 4 BROKEN STRAINS. FOUND 	RUDDER CABLES UNDER PILOTS FLOORBOARDS FRAYED AT FAIRLEADS. PART NUMBERS INVOLVED, 6565007-188, 6565007-193CR, 6565007-	3, AND 6565007-135. SUBMITTER RECOMMENDS A CLOSER INSPECTION OF THESE CABLES DURING THE REGULAR INSPECTION PROGRAM. A	IRCRAFT SKIN WAS BEING REPLACED AT TIME OF DISCOVERY.			1	L	7	2 	4F				A27CE 					 
1995110600633	19951106	00633	NE 	1995	11	6	95ZZZX6049 	2	19951012	G	7261	31017251	GEARBOX FITTING 			MTSBSI	MU2 	MU2B36 	5780412	CE 	GARRTT	TPE331	TPE3316252M 	01514	NE 					OIL SCAVENGE	DEFECT 	E		A		E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			J			WARNING INDICATION 			CR	CRUISE 	1			SW	99	103RC					673	P20371C			IN CRUISE FLIGHT, LEFT ENGINE OIL PRESSURE STARTED TO FLUCTUATE. A PRECAUTIONARY SHUT DOWN WAS MADE AND THE AIRCRAFT HA	D AN UNEVENTFUL LANDING. TROUBLESHOOTING FOUND THE GEARBOX SCAVENGE OIL LINE FITTING IN THE GEARBOX HAD STARTED BACKING	 OUT. THE THREADS IN THE GEARBOX WERE PARTIALLY RUINED. ENGINE WAS REMOVED AND SENT OUT FOR REPAIR. SUBMITTER RECOMME	NDS TORQUE CHECK OF ALL FITTINGS ON GEARBOX EVERY 200 HOURS OF ENGINE OPERATION.			1	H	7	2 	3T			RT	A10SW 	E2WE				 
1995021000209	19950210	00209	SO 	1995	2	10	95ZZZX605 	2	19950121	G	8530		VALVE 			CESSNA	182 	182F 	2072714	CE 	CONT 	O470 	O470R 	17026	SO 					ENG EXHAUST	EXCESS WEAR 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19							275731R			CONTINENTAL O470F ENGINE WITH ONLY 165 HOURS SINCE FACTORY REMANUFACTURE. EXHAUST VALVE STEMS SHOW EXTREME WEAR. FOUND	 VALVE GUIDES TO BE NITRALLOY.					1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1995111300001	19951113	00001	CE 	1995	11	13	95ZZZX6050 	1	19951010	G	7602	98620103	CONTROL 			CESSNA	150 	150L 	2071826	CE 										MIXTURE	DEFECTIVE 	B			BXSR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	09										NEW MIXTURE CONTROL WAS RECEIVED FROM CESSNA WITH AN FAA FORM 8130-3, WITH A DEFECT. THE INTERNAL WIRE WOULD PULL OUT W	ITH NO STOP, AND THE RELEASE BUTTON LOCK WAS INOPERABLE.					1	H	7	1 	3O				3A19 					 
1995111300002	19951113	00002	NE 	1995	11	13	95ZZZX6051 	2	19951002	G	8530		CYLINDER 			DOUG 	DC3 	DC3C 	3021457	WP 	PWA 	R1830 	R183092 	52020	NE 					NR 4	HEAD SEPARATED 	E				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SW	11	59316		743 			18986	BP429393			LEFT ENGINE STARTED TO RUN ROUGH IN-FLIGHT. UPON TROUBLESHOOTING, FOUND CYLINDER NR 4 HEAD HAD SEPARATED FROM THE BARRE	L. CYLINDER WAS REPLACED WITH AN OVERHAULED UNIT.					2	L	7	2 	4R	4	R		A669 	5E4				 
1995111300003	19951113	00003	SW 	1995	11	13	95ZZZX6052 	1	19951012	G	7922	75944	VALVE 			MOONEY	M20 	M20C 	5870208	SW 	LYC 	O360 	O360A1D 	41514	EA 					THERMO BYPASS	LOOSE CRIMP NUT 	B			WIZR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	68KH					680074	L1231736A			DURING INSPECTION OF THERMOSTATIC BYPASS VALVE PER LYC SB518C, THE RETAINING NUT WAS FOUND LOOSE AND THE SPRING PRESSURE	 WAS NOTICEABLY LESS THAN OTHER VALVES PREVIOUSLY INSPECTED. ENGINE TSMOH, 320.0 HOURS.					1	L	7	1 	3O	3	O		2A3 	E286				 
1995111300004	19951113	00004	SO 	1995	11	13	95ZZZX6053 	2	19951017	G	8520		CRANKCASE 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520L 	17032	SO 					RIGHT SIDE	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	6834C	1540 				421C0476	241181R			INSPECTION FOUND CRACK IN CRANKCASE STARTING AT TOP CASE FLANGE BOLT DOWN UNDER ENGINE DATA PLATE, THEN DOWN BETWEEN NR 	3 AND NR 5 CYLINDERS. CRACK IS 8 INCHES LONG. LEFT ENGINE HAD A CRACK SAME AREA 96 HOURS AGO.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995111300005	19951113	00005	CE 	1995	11	13	95ZZZX6054 	1	19950928	G	2910		HOSE 			CESSNA	404 	404CESSNA 	2075901	CE 										LT MLG UP LINE	RUPTURED 	B			APCR	A	O			UNSCHED LANDING 	OTHER 			K			FLUID LOSS 			NR	NOT REPORTED 	1			NM	01	48SA	65 				4040417				LEFT MAIN GEAR 'UP' HYDRAULIC LINE HOSE SEPARATED FROM END FITTING. HYDRAULIC FLUID DUMPED OVERBOARD. PILOT BLEW GEAR 	'DOWN' WITH NITROGEN BOTTLE. HOSE HAD BEEN FABRICATED FROM NEW PARTS 65 HOURS PREVIOUSLY.					1	L	7	2 	3O				A25CE 					 
1995111300006	19951113	00006	SO 	1995	11	13	95ZZZX6055 	1	19950928	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	LOOSE CRIMP NUT 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	3582X				57761	318052105				VERNATHERM VALVE WAS REMOVED FROM ENGINE, RETAINING NUT WAS FOUND LOOSE. THIS VERNATHERM DID NOT APPLY TO SB 518C BY SE	RIAL NUMBER. IT WAS INSPECTED DUE TO PREVIOUS REPORTS OF VERNATHERM FAILURES WHICH MET SB 518C CRITERIA. SUBMITTER STA	TED POOR DESIGN, RE-DESIGN PART.				1	L	7	2 	3O				A20SO 					 
1995111300007	19951113	00007	SO 	1995	11	13	95ZZZX6056 	1	19950925	G	8120	60051004	TURBOCHARGER 	ROTOMASTER 		PIPER 	PA34 	PA34200T 	7103406	SO 										ENGINE	HOUSING CRACKED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	5384F		1612 		WBL0177	347770013				FOUND TURBINE HOUSING CRACKED. HOUSING IS DEFECTIVE EXACTLY AS IDENTIFIED IN AD 82-27-03, EVEN THOUGH IT IS LATEST (GOO	D) PART NUMBER. THESE HOUSINGS CRACK JUST LIKE THE ORIGINAL AND ARE REALLY NOT ANY BETTER (THIS IS THE 'DN' HOUSING).					1	L	7	2 	3O				A7SO 					 
1995111300008	19951113	00008	SO 	1995	11	13	95ZZZX6057 	1	19950925	G	3230	AN546	PIVOT BOLT 			PIPER 	PA31 	PA31350 	7103110	SO 										RT MLG DOWNLOCK	REQUIRED LUBE 	B			APCR	O				OTHER 				J	P		WARNING INDICATION 	NO WARNING INDICATION 		AP	APPROACH 	1			NM	01	27594					317852070				PILOT EXTENDED LANDING GEAR, BUT RIGHT MAIN 'DOWN' LIGHT DID NOT ILLUMINATE AND 'IN-TRANSIT' LIGHT STAYED ON. PILOT WAS	 CIRCLING FIELD AND TALKING OVER PROBLEM WITH D.D.M., WHEN 'DOWN' LIGHT CAME ON AND GEAR HYDRAULIC SYSTEM COMPLETED ITS 	CYCLE. AIRCRAFT LANDED WITHOUT INCIDENT. FOUND THAT DOWNLOCK HOOK WOULD BEND IN RELEASED (UNLOCKED) POSITION DUE TO LA	CK OF LUBRICATION BETWEEN HOOK AND BOLT. NO FACTORY PROVISION FOR LUBING. NO ZERK FITTING, ETC.			1	L	7	2 	3O				A20SO 					 
1995111300009	19951113	00009	SO 	1995	11	13	95ZZZX6058 	1	19951008	G	5553	63501004	FITTING 			PIPER 	PA34 	PA34200T 	7103406	SO 										V-FIN ATTACH	RIVETS LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	5384F	10300				347770013				FOUND 3 RIVETS WERE LOOSE ON THE LOWER AFT VERTICAL FIN-TO-FUSELAGE ATTACHMENT FITTING. THE RIVETS THAT ARE LOOSE ARE T	HE LOWER OUTBOARD CORNER RIVETS.					1	L	7	2 	3O				A7SO 					 
1995111300010	19951113	00010	CE 	1995	11	13	95ZZZX6059 	1	19951010	G	6121	213100	ACTUATOR 	WOODWARD 		CESSNA	421 	421B 	2076014	CE 										RT PROP SYNC	PIN SHEARED 	B		A	QY5R	O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			NE	01	1950G				1493721A	421B0849				PILOT EXPERIENCED RAPID RPM INCREASE ON THE RIGHT ENGINE WHEN PROP SYNC ENGAGED. PILOT THEN SHUT OFF PROP SYNC AND CONT	ROLLED RPM MANUALLY, BUT REPORTED THE RIGHT PROP LEVER TO BE OUT OF RIG WITH THE LEFT AND WOULD NOT GO FULL TRAVEL. INV	ESTIGATION REVEALED THE STOP PIN ON THE PROP SYNC ACTUATOR HAD SHEARED AND THE STOP ACTUATOR ARM REMAINED ENGAGED TO THE	 INCREASE RPM MICROSWITCH. THIS CAUSED THE PROP SYNC TRIMMER TO GO FULLY EXTENDED AND CAUSED MIS-RIGGING OF THE RIGHT P	ROP GOVERNOR.		1	L	7	2 	3O				A7CE 					 
1995021000210	19950210	00210	CE 	1995	2	10	95ZZZX606 	1	19950109	G	5410	45A349833	DOUBLER 			BEECH 	MU300 	400BEECH 		CE 										RT ENG PYLON	CORRODED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	46FE	1247 				RK0016				DURING INSPECTION, UPPER SKIN DOUBLER FOR THE RIGHT ENGINE PYLON WAS FOUND HEAVILY CORRODED. THIS PART IS MADE OF 4130 	STEEL AND IS SUSCEPTIBLE TO RUST. REMOVED TOP SKIN AND REPLACED DOUBLER.					2	H	7	2 	4F			RT	A16SW 					 
1995111300011	19951113	00011		1995	11	13	95ZZZX6060 	4	19951016	G	2562	AK450	ELT 	AMERIKING 																G-SWITCH	MALFUNCTION 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	15					4501630					WHEN REMOVED FROM BOX, THE AK-450 ELT DID NOT PERFORM ON THE BENCH AS REQUIRED. THIS IS THE 2ND ELT RECEIVED OF THE SAM	E MODEL WITH PROBLEMS. THE AUDIBLE SWEEP WOULD STICK AND ONLY A SINGLE TONE WOULD BE HEARD. WHEN TURNED ON, THE ELT WO	ULD SOMETIMES NOT OPERATE. WIGGLING THE SWITCH AND/OR ANTENNA CONNECTION WOULD HAVE INCONSISTENT RESULTS IN GETTING THE	 ELT TO OPERATE. ELT WAS NOT INSTALLED IN ACFT DUE TO THESE PROBLEMS.																 
1995111300012	19951113	00012	CE 	1995	11	13	95ZZZX6061 	1	19951013	G	3240	300500	BRAKE ASSY 			PIPER 	PA23 	PA23150 	7102303	CE 										BACK PLATE	DEFECTIVE 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	05	1093P					23102				UPON RIVETING BRAKE LININGS ONTO BACK PLATES, SOME RIVETS WOULD NOT TIGHTEN. SOME PLATES WERE FOUND BRONZE, SOME STEEL,	 BUT DIFFERENT DIMENSIONS. OWNER DID NOT KNOW OF A DUAL BRAKE STC BEING INSTALLED ON THIS AIRCRAFT. THIS WAS OF A NON-	ORIGINAL MANUFACTURE TYPE ALTHOUGH THE BRAKES LOOKED IDENTICAL WHEN DIRTY. THE ORIGINATOR OF THE STC COULD NO LONGER BE	 LOCATED TO PURCHASE PARTS.			1	L	7	2 	3O			RT	1A10 					 
1995111300013	19951113	00013	CE 	1995	11	13	95ZZZX6062 	1	19951012	G	2750	12527Y6331	FLEX CABLE 			BEECH 	33 	F33A 	1151425	CE 										LT FLAP DRIVE	FAILED 	D		A		O				OTHER 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			NE	05	625JP	776 				CE1503				END OF FLAP DRIVE CABLE BROKE OFF AT WOODRUFF KEY AREA WHERE CABLE ENTERS GEARBOX. SINCE IT WAS LEFT CABLE, THE RIGHT F	LAP EXTENDED UNTIL IT BOTTOMED OUT IN FLAP TRACK. DAMAGE APPEARS TO HAVE STARTED FROM PREVIOUS OVER EXTENSION DUE TO SW	ITCH FAILURES. SUBMITTER RECOMMENDS INSPECTION OR REPLACMENT ANY TIME OVER EXTENSION OCCURS.				1	L	7	1 	3O				3A15 					 
1995111300014	19951113	00014	CE 	1995	11	13	95ZZZX6063 	1	19951013	G	5753	35165050606	FLAP RIB 			BEECH 	33 	F33A 	1151425	CE 										RT FLAP	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	625JP	776 				CE1503				DURING INSPECTION OF FLAP SYSTEM, NOSE RIB IN RIGHT FLAP WHERE FLAP ACTUATOR CONNECTS WAS FOUND CRACKED AND FLAP SKIN WA	S DEFORMED. SUBMITTER SUGGESTS IT APPEARS TO BE CAUSED BY FLAP BEING OUT OF RIG AND BOTTOMING OUT IN FLAP TRACK.					1	L	7	1 	3O				3A15 					 
1995111300015	19951113	00015	CE 	1995	11	13	95ZZZX6064 	1	19951002	G	7810	K99102995	ELBOW 			CESSNA	414 	414 	2075908	CE 										EXH WYE	BROKE 	B			SJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	28901					4140353				FOUND ELBOW BROKEN AT CONNECTION END TO WYE PIPE CONNECTOR UNDER WASTEGATE.						1	L	7	2 	3O			RT	A7CE 					 
1995111300016	19951113	00016	CE 	1995	11	13	95ZZZX6065 	1	19951002	G	7810	99102998	WYE PIPE 			CESSNA	414 	414 	2075908	CE 										WASTEGATE OUTLET	FLANGE BROKEN 	B			SJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	28901					4140353				FOUND FLANGE BROKEN AT CONNECTION TO WASTEGATE OUTLET.						1	L	7	2 	3O			RT	A7CE 					 
1995111300017	19951113	00017	NE 	1995	11	13	95ZZZX6066 	2	19950922	G	7414	SB9RU3	MAGNETO 	BOSCH 		DHAV 	DHC2 	DHC2MK1 	2800102	EA 	PWA 	R985 	R985AN14B 	52008	NE 					LT MAG	GEAR FLATED 	B			NZBR	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			R			PARTIAL RPM/PWR LOSS 			TO	TAKEOFF 	1			AL	05	2738G		444 		BB2769	1511	JP210889			PILOT REPORTED PARTIAL LOSS OF POWER ON TAKEOFF. TROUBLESHOT TO LEFT MAGNETO, STRIPPED DISTRIBUTOR GEAR. REPLACED LEFT	 MAGNETO WITH OVERHAULED UNIT. GROUND RUN AND OPERATIONAL CHECK GOOD.					1	H	7	1 	3R	3	R		A806 	5E1				 
1995111300018	19951113	00018	SO 	1995	11	13	95ZZZX6067 	1	19951018	G	7810	NH100583410	CLAMP 			PIPER 	PA31 	PA31325 	7103105	SO 										EXHAUST ELBOW	BROKEN 	D	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	11SB	459 			R34448T	317612062				REMOVED EXHAUST CLAMP FOR MAINTENANCE. FOUND CLAMP WAS BROKEN. THIS CLAMP IS THE NEW STYLE THAT IS SUPPOSED TO END REC	URRING AD 82-16-05. FOUND NO DAMAGE ON EXHAUST ELBOW FLANGE.					1	L	7	2 	3O				A20SO 					 
1995111300019	19951113	00019	SW 	1995	11	13	95ZZZX6068 	1	19950905	G	7120	501641	TUBE 			AIRTRC	AT300 	AT301 	0390103	SW 										ENG OIL TANK MT	CRACKED 	G	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	73075	3673 				3010621				DURING ANNUAL INSPECTION, THE TUBE USED TO MOUNT ENGINE OIL TANK FOUND CRACKED AT THE RIGHT REAR TANK MOUNTING POINT. T	HE CRACK ENCIRCLED THE TUBE, BUT DID NOT MEET. DURING REPAIR, NO EVIDENCE OF INTERNAL CORROSION ON TUBING OTHER THAN AT	 CRACK AREA.				1	L	7	1 	3R				A9SW 					 
1995111300020	19951113	00020	SO 	1995	11	13	95ZZZX6069 	1	19950708	G	5521		SPAR 			PIPER 	PA12 	PA12 	7101202	SO 										LT ELEV	BROKEN 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	02	3297M		30 			122153				AIRCRAFT MODIFIED TO USE BALANCED PA-18 TAIL SURFACES. AIRCRAFT WAS COMPLETELY RECOVERED APPROX 30 HOURS PRIOR. UPON E	XITING AIRCRAFT AFTER A ROUTINE FLIGHT, LEFT ELEVATOR WAS FOUND BENT DOWNWARD APPROX 35 DEGREES OUTBOARD OF THE OUTERMOS	T HINGE. UPON EXAMINATION, ELEVATOR SPAR FOUND COMPLETELY BROKEN FROM STRESS CRACKS. ALSO, FOUND OUTBOARD HINGE BRAZED	 ON WHICH IS NOT APPROVED FOR STRUCTURAL MEMBERS. IT IS POSSIBLE EXCESS HEAT FROM THE BRAZING COULD HAVE ALLOWED BRAZIN	G MATERIAL TO PENETRATE BETWEEN THE GRAINS IN THE STEEL AND CAUSE THE CRACKING. AC 43.13 IA CH 2, SECTION 1, PARA 56. B	RAZING IS NOT APPROVED FOR PRIMARY STRUCTURES WHERE WELDING WAS USED ORIGINALLY.	1	H	7	1 	3O				A780 					 
1995021000211	19950210	00211	CE 	1995	2	10	95ZZZX607 	1	19950120	G	5740	58221302	FITTING 			CESSNA	441 	441 	2076020	CE 										RT WING FWD	DAMAGED 	B	P		EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	815MC					4410263				DURING REPAIR FOR GEAR-UP LANDING, AN INSPECTION OF THE WING ATTACH POINTS WAS PERFORMED. THE RIGHT WING, FORWARD ATTAC	H FITTING, WAS FOUND BADLY DAMAGED. THIS DAMAGE WAS AROUND THE WING BOLT HOLE AND COULD NOT HAVE BEEN CAUSED BY THE GEA	R-UP LANDING. FITTING WAS REPLACED.				1	L	7	2 	3T			RT	A28CE 					 
1995111300021	19951113	00021	EA 	1995	11	13	95ZZZX6070 	2	19950912	G	7414	S4LN1227	MAGNETO 	BENDIX 		GULSTM	112 	112A 	7630302	SW 	LYC 	O360 	IO360C1D6 	41514	EA 					ENGINE	CASE CRACKED 	H	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	1457J	1420 			A150536	457				SECOND SET OF MAG'S FOUND WITH THIS CRACK PATTERN. NEW STYLE CASE HAS A FIN WEB TO STRENGTHEN CASE IN THIS AREA. CRACK	S HAVE BEEN FOUND ON BOTH SIDES THROUGH CASE HOLE.					1	L	7	1 	3O	3	O		A12SO 	1E10				 
1995111300022	19951113	00022	EA 	1995	11	13	95ZZZX6071 	2	19950912	G	7414	S4LN1209	MAGNETO 	BENDIX 		GULSTM	112 	112A 	7630302	SW 	LYC 	O360 	IO360C1D6 	41514	EA 					ENGINE	CASE CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	1457J	1420 			A148857	457				SECOND SET OF MAG'S FOUND WITH THIS CRACK PATTERN. NEW STYLE CASE HAS A FIN WEB TO STRENGTHEN CASE IN THIS AREA. CRACK	S HAVE BEEN FOUND ON BOTH SIDES THROUGH CASE HOLE.					1	L	7	1 	3O	3	O		A12SO 	1E10				 
1995111300023	19951113	00023	EA 	1995	11	13	95ZZZX6072 	2	19951009	G	8510	77579	FLYWHEEL 			PIPER 	PA28 	PA28180 	7102808	SO 	LYC 	O360 	O360A4A 	41514	EA 					STARTER RING GR	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	2049R	2026 				285445	L1413836A			AFTER STARTER FLYWHEEL REMOVAL, FOUND FLYWHEEL CRACKED FROM MOUNTING HOLE TO BOTTOM OF CONICAL STRUCTURE. COULD FIND NO	 REASON FOR CRACK. NO DAMAGE NOTED, WHEN AIRCRAFT ENGINE BALANCED YEAR BEFORE, IT CHECKED OUT GOOD.					1	L	7	1 	3O	3	O		2A13 	E286				 
1995111300024	19951113	00024	CE 	1995	11	13	95ZZZX6073 	1	19951018	G	2720	04115264	RUDDER BAR 			CESSNA	150 	152 	2071835	CE 										PILOT SIDE	BROKEN 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	4633B	7087 				15283559				RUDDER BAR BROKEN AT RIGHT PEDAL ATTACH ON PILOT'S SIDE. SUBMITTER SUGGESTS INSPECT MORE CLOSELY FOR CRACKS. THIS AREA	 IS NOT INSPECTED WELL ON MANY CESSNA AIRCRAFT BECAUSE IT IS UNDER A DIFFICULT TO REMOVE PANEL.					1	H	7	1 	3O			NT	3A19 					 
1995111300025	19951113	00025	EU 	1995	11	13	95ZZZX6074 	1	19950911	G	3222	6403010000	FORK LEG 			PILATS	PC6T 	PC6B2H2 	7090213	EU 										TAILWHEEL	WATER TRAPPED 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	2MIL	3703 				803				FOUND 2-3 OUNCES OF WATER TRAPPED IN LANDING GEAR FORK LEG. APPLIED ONLY TO ACFT WITH PILATUS SB141, EQUIPPED FOR PARAC	HUTING (PARA DROP VERSION) OR OTHERWISE HAVING TAILWHEEL DEBRIS GUARD INSTALLED. SB141 DOES NOT REQUIRE SEALANT AROUND 	RIVETS OR ANGLE BRACKETS ATTACHED TO TAILWHEEL FORK LEGS. WATER ENTERED FORK LEGS THROUGH PROTECTION PLATE MOUNTS. DAM	AGE TO FORK LEGS MAY OCCUR INSIDE OF LEGS DUE TO CORROSION (RUST) OR BY FREEZING, THE ICE WOULD EXERT PRESSURE ON THE FO	RK LEGS BY EXPANSION. SUBMITTER RECOMMENDS ISSUANCE OF SDR'S OR POSSIBLY, AN AD TO CHECK FOR PRESENCE OF WATER AT THE N	EXT 100-HOUR INSPECTION. TAILWHEEL GUARD INSTALLED 11-5-91 AT 2,622.6 ACFT HRS, ACFT HRS NOW 3,703.4.	1	H	7	1 	3T				7A15 					 
1995111300026	19951113	00026	GL 	1995	11	13	95ZZZX6075 	3	19950928	G	6111	FC84686R	BLADE 			PIPER 	PA31 	PA31350 	7103110	SO 						HARTZL	HCE3Y	HCE3YR2 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1998 			D77374			DJ8554A		INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	2 	3O				A20SO 		5	C	P33EA	 
1995111300027	19951113	00027	GL 	1995	11	13	95ZZZX6076 	3	19950928	G	6111	FC84686R	BLADE 			PIPER 	PA31 	PA31350 	7103110	SO 						HARTZL	HCE3Y	HCE3YR2 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1998 			F49813			DJ8554A		INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	2 	3O				A20SO 		5	C	P33EA	 
1995111300028	19951113	00028	GL 	1995	11	13	95ZZZX6077 	3	19950928	G	6111	FC84686R	BLADE 			PIPER 	PA31 	PA31350 	7103110	SO 						HARTZL	HCE3Y	HCE3YR2 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1998 			D8199			DJ8554A		INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	2 	3O				A20SO 		5	C	P33EA	 
1995111300029	19951113	00029	GL 	1995	11	13	95ZZZX6078 	3	19950928	G	6111	F847504	BLADE 			PIPER 	PA32 	PA32300 	7103212	SO 						HARTZL	HCC2Y	HCC2YK1 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1990 						D92837		INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	1 	3O				A3SO 		5	C	P920	 
1995111300030	19951113	00030	GL 	1995	11	13	95ZZZX6079 	3	19950928	G	6111	F847504	BLADE 			PIPER 	PA32 	PA32300 	7103212	SO 						HARTZL	HCC2Y	HCC2YK1 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1990 						D96625		INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	1 	3O				A3SO 		5	C	P920	 
1995111300031	19951113	00031	GL 	1995	11	13	95ZZZX6080 	3	19950928	G	6111	F847504	BLADE 			PIPER 	PA32 	PA32300 	7103212	SO 						HARTZL	HCC2Y	HCC2YK1 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1996 						H40586		INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	1 	3O				A3SO 		5	C	P920	 
1995111300032	19951113	00032	GL 	1995	11	13	95ZZZX6081 	3	19950928	G	6111	F847504	BLADE 			PIPER 	PA32 	PA32300 	7103212	SO 						HARTZL	HCC2Y	HCC2YK1 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1996 						H40587		INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	1 	3O				A3SO 		5	C	P920	 
1995111300033	19951113	00033	GL 	1995	11	13	95ZZZX6082 	3	19950928	G	6111	FJC84686R	BLADE 			PIPER 	PA32 	PA32300 	7103212	SO 						HARTZL	HCE3Y	HCE3YR2 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1999 			EF59149					INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	1 	3O				A3SO 		5	C	P33EA	 
1995111300034	19951113	00034	GL 	1995	11	13	95ZZZX6083 	3	19950928	G	6111	FJC84686R	BLADE 			PIPER 	PA32 	PA32300 	7103212	SO 						HARTZL	HCE3Y	HCE3YR2 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1999 			E55162					INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	1 	3O				A3SO 		5	C	P33EA	 
1995111300035	19951113	00035	GL 	1995	11	13	95ZZZX6084 	3	19950928	G	6111	FJC84686R	BLADE 			PIPER 	PA32 	PA32300 	7103212	SO 						HARTZL	HCE3Y	HCE3YR2 	GL 	PROPELLER	BELOW WIDTH 	B			AF4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01		1999 			E56980					INSPECTION FOUND BLADE WIDTH BELOW MINIMUM SPECIFICATIONS.						1	L	7	1 	3O				A3SO 		5	C	P33EA	 
1995111300036	19951113	00036	GL 	1995	11	13	95ZZZX6085 	3	19950919	G	6114		HUB 			CESSNA	206 	U206G 	2073356	CE 						MCAULY	3A32C	D3A32C90 	GL 	NR 1 SOCKET	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	2FOR		1514 					712411		PROPELLER INSPECTION FOUND CRACK IN BLADE SOCKET NR 1, 4TH THREAD.						1	H	7	1 	3O				A4CE 		5	C	P21EA	 
1995111300037	19951113	00037	SW 	1995	11	13	95ZZZX6086 	1	19950712	G	6320	476206283	BEARING 		4762060029 	BELL 	47 	47G5A 	1181034	SW 										M/R XMSN	MAKING METAL 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	615BH				BBV10013	25126				UPON FINDING METAL IN OIL SCREEN, TEAR DOWN INSPECTION OF MAIN TRANSMISSION WAS PERFORMED. LOWER SUNGEAR BEARING WAS FO	UND TO BE THE CAUSE OF THE METAL CONTAMINATION. THIS HAS BEEN THE FIFTH BEARING FAILURE. EACH BEARING HAS HAD LESS THA	N 200 HOURS TOTAL TIME. THIS BEARING SHOULD LAST AT LEAST 2,400 HOURS. SUBMITTER SUSPECTS A MANUFACTURE DEFECT. THE M	ANUFACTURER, MRC, SHOULD LOOK MORE CLOSELY AT THIS MATTER. BELL HELICOPTERS HAS BEEN INFORMED NUMEROUS TIMES AND NO REA	L ACTION HAS BEEN TAKEN IN THE PAST YEAR.		1	G	7	1 	3O				2H3 					 
1995111300039	19951113	00039	WP 	1995	11	13	95ZZZX6088 	1	19950923	G	6210	369D21100513M	BLADE 			HUGHES	369 	369D 	4470706	WP 										M/R	DELAMINATED 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V	3303 	126 		C808	490487D				ON PRE-FLIGHT, THE ABRASION STRIP WAS FOUND DELAMINATING. FOUND A BUBBLE, .75 INCH WIDE RUNNING AT AN ANGLE FROM THE LE	ADING EDGE AT STA 135.0 TO THE TRAILING EDGE OF THE ABRASION STRIP AT STA 145.0. PART REMOVED AND SENT IN FOR REPAIR (T	HIS IS ON THE BOTTOM OF THE BLADE).				1	G	7	1 	3U				H3WE 					 
1995111300064	19951113	00064	SW 	1995	11	13	95ZZZX6089 	1	19950920	G	2910	MS21910D6	TEE FITTING 			BELL 	230 	230 	1182149	SW 										NR 2 HYD SYSTEM	LEAKING 	B			SL3R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NE	01	230TX	448 				23014				TEE FITTING, LOCATED ON TOP DECK FOR HYDRAULIC SYSTEM 2, LEAKING. FOUND CRACKED FITTING. INSTALLED NEW FITTING.						1	G	7	2 	3U			NC	H9SW 					 
1995111300066	19951113	00066	EU 	1995	11	13	95ZZZX6091 	1	19950823	G	6710	MB1015DU	BUSHING 		10545028 	BOLKMS	105 	BO105S 	5626006	EU 										SERVO ACTUATOR	BINDING 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4572V					S665				DURING TEST FLIGHT AFTER INSTALLATION OF BOOSTER PACK, LATERAL M/R CONTROL BECAME SPONGY/SLUGGISH, MUSHING AND SLOW TO R	ESPOND. LATERAL FEEDBACK IN CONTROLS. SHOP INSPECTION REVEALED BINDING IN SYS I AND SYS II LATERIAL CONTROL SERVO ACTU	ATORS OF BOOSTER PACK. SERVO VALVE BUSHINGS, PN MB1015DU, SUPPORTING SERVO VALVE COUPLING BOLTS, PN 105-46666.07, WERE 	FOUND BINDING CAUSING HIGH INPUT FORCES TO SERVO VALVE. CAUSE OF SUDDEN BUSHING TIGHTNESS IS UNKNOWN. BUSHINGS WERE BU	RNISHED TO REDUCE FRICTION ON COUPLING BOLTS TO NORMAL LIMITS. NOTE: LATERAL ACTUATORS SYMMETRY WAS OUT OF LIMITS AND 	RETURNED TO WITHIN LIMITS AFTER REPAIR WAS MADE BY BURNISHING TIGHT BUSHINGS.	1	G	7	2 	3U				H3EU 					 
1995111300067	19951113	00067	SW 	1995	11	13	95ZZZX6092 	1	19950824	G	6220	206010191001	SUPPORT 		206011117003	BELL 	206 	206B 	1181511	SW 										FLAP RESTRAINT	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3896W					3197				DURING NDT INSPECTION FOR OVERHAUL, FOUND CRACK ON EARS OF SUPPORT FOR FLAP RESTRAINT.						1	G	7	1 	3U				H2SW 					 
1995111300068	19951113	00068	SW 	1995	11	13	95ZZZX6093 	1	19950808	G	6230	206010338001	BEARING 			BELL 	206 	206B 	1181511	SW 										SWASHPLATE	WORN 	B			WG3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	33TV	780 				4306				REMOVED SWASHPLATE DRIVE LINK BEARINGS DUE TO WEAR AT 779.7 HRS TSN. INSTALLED NEW DRIVE LINK BEARINGS, PN 206-010-338-	001, 4 EACH, AND PN 206-010-337-001, 4 EACH.					1	G	7	1 	3U				H2SW 					 
1995111300069	19951113	00069	SW 	1995	11	13	95ZZZX6094 	1	19950808	G	6230	206010337001	BEARING 			BELL 	206 	206B 	1181511	SW 										SWASHPLATE	WORN 	B			WG3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	33TV	780 				4306				REMOVED SWASHPLATE DRIVE LINK BEARINGS DUE TO WEAR AT 779.7 HRS TSN. INSTALLED NEW DRIVE LINK BEARINGS, PN 206-010-338-	001, 4 EACH, AND PN 206-010-337-001, 4 EACH.					1	G	7	1 	3U				H2SW 					 
1995111300072	19951113	00072	SW 	1995	11	13	95ZZZX6097 	1	19950814	G	6410	206016201127	BLADE BEARING 			BELL 	206 	206L1 	1182107	SW 										T/R	WORN 	B			ZV1R	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5007F	1204 			CS5442	45186				PILOT COMPLAINED OF HIGH FREQUENCY VIBRATION. FOUND INBOARD BEARING CRACKED. TOTAL TIME OF BEARINGS, 663.9 HOURS.						1	G	7	1 	3U				H2SW 					 
1995111300073	19951113	00073	SW 	1995	11	13	95ZZZX6098 	1	19950814	G	6410	206016201127	BLADE BEARING 			BELL 	206 	206L1 	1182107	SW 										T/R	WORN 	B			ZV1R	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5007F	1204 			CS5445	45186				PILOT COMPLAINED OF HIGH FREQUENCY VIBRATION. FOUND INBOARD BEARING CRACKED. TOTAL TIME OF BEARINGS, 663.9 HOURS.						1	G	7	1 	3U				H2SW 					 
1995111300076	19951113	00076	NE 	1995	11	13	95ZZZX6101 	1	19950610	G	2435	6854424	SEAL 			SKRSKY	S76 	S76 	8143010	NE 										START/GENERATOR	FAILED 	E		A		E				ENGINE SHUTDOWN 				K	J		FLUID LOSS 	WARNING INDICATION 		CR	CRUISE 	1			SW	03	5128					760181				ON 6-10-95, NR 2 ENGINE OIL PRESSURE FLUCTUATED IN-FLIGHT. SECURED ENGINE, MADE SINGLE ENGINE LANDING. FOUND NR 2 ENGI	NE STARTER/GENERATOR SEAL HAD 'POPPED' OUT. SEAL HAD BEEN INSTALLED 30 MINUTES PRIOR. SUSPECT DAMAGED DURING INSTALLAT	ION. 250-C30 IPC, CHAPTER 72-60-00, FIG 7, ITEM 31.				1	G	7	2 	3U				H1NE 					 
1995111300186	19951113	00186	EA 	1995	11	13	95ZZZX6141 	2	19950425	G	8520	76220	THROUGH-BOLT 			MOONEY	M20 	M20F 	5870214	SW 	LYC 	O360 	IO360A1A 	41514	EA 					NR 1 CYLINDER	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	7112V	2763 	1788 			220047	L12C245A			SUBJECT NR 1 CYLINDER UPPER THROUGH-BOLT FOUND BROKEN DURING PREFLIGHT. DETECTED AS THE MAJOR REMAINING PORTION AND HOL	D-DOWN NUT FOUND BACKED OUT OF POSITION AND LODGED AGAINST CYL FINS. INSTALLED NEW BOLT, SPACER, AND NUT. TORQUED PER 	LYC SERVICE LETTER 1029C. BOLT THREADED END BROKE OFF FLUSH WITH NUT'S SEATING SURFACE. INDICATIONS WERE A CRACK ABOVE	 50 PERCENT ACROSS DIAMETER HAD EXISTED FOR SOME TIME & BOLT ULTIMATELY FAILED IN A TYPICAL TENSILE FRACTURE. MISSING S	PACER HAD MIGRATED THROUGH CABIN HEATER SCAT TUBING & FOUND LODGED IN MUFFLER OPENING. NUT WITH SHEARED OFF END WAS LOD	GED BETWEEN NR 2 AND NR 4 ROCKER BOXES. ENGINE HAD BEEN ASSEMBLED 27 HRS PREVIOUSLY.	1	L	7	1 	3O	3	O		2A3 	1E10				 
1995111300187	19951113	00187	EA 	1995	11	13	95ZZZX6142 	2	19950424	G	8530	78743	PIPE 			MOONEY	M20 	M20F 	5870214	SW 	LYC 	O360 	IO360A1A 	41514	EA 					NR 3 CYLINDER	CRACKED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	7112V	1680 	678 			220047	L1262451A			REPLACED PARTS RECEIVED BACK FROM OVERHAUL AGENCY FOLLOWING PROP STRIKE DISASSEMBLY INSPECTIONS, INCLUDED A PN SL-1024J 	PISTON AND SUBJECT NR 3 CYL INTAKE PIPE. PISTON EXHIBITED EARLY STAGES OF TYPICAL DETONATION DAMAGE ON THE HEAD, ADJACE	NT TO ITS O.D., AT THE 12 O'CLOCK POSITION AS INSTALLED. TPT 678 HRS. CAUSE APPARENTLY DUE TO EXCESSIVELY LEAN MIXTURE	S RESULTING FROM AMBIENT AIR ENTERING SUBJECT CRACKED INTAKE PIPE AND ADJ TO ITS CYL MATING END. CRACK WAS IN THE PIPE'	S ATTACHMENT FLARE RADIUS, WAS CLEARLY VISIBLE, & EXTENDED AROUND APPROX 40 PERCENT OF THE PIPE'S DIAMETER. CYL HAD BEE	N REPLACED 67 HRS PREVIOUSLY.	1	L	7	1 	3O	3	O		2A3 	1E10				 
1995111300188	19951113	00188	EA 	1995	11	13	95ZZZX6143 	2	19950424	G	8550	75167	OIL LINE 			MOONEY	M20 	M20F 	5870214	SW 	LYC 	O360 	IO360A1A 	41514	EA 					PROP GOVERNOR	CHAFED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	7112V	678 				220047	L1262451A			INSPECTION FOLLOWING ENGINE REMOVAL REVEALED EXTREME CHAFING/WEAR DAMAGE TO PROP GOVERNOR EXTERNAL OIL LINE AT GOV END A	PPROX 5 INCHES AWAY FROM B-NUT ATTACH. DAMAGED AREA APPROX .25 INCH BY .50 INCH & WEAR WAS NEARLY THROUGH TUBE WALL THI	CKNESS. OIL LOSS WAS IMMINENT. AD NOTE 90-04-06 WAS ACCOMPLISHED 678 HRS PREVIOUSLY. ACFT HAD BEEN ANNUALED 5 TIMES S	INCE. THE AD LYC REQUIRED CLAMPING WAS PRESENT AND INTACT. ENG MOUNT TUBE WAS SIMILIARY DAMAGED, REQUIRING WELD REPAIR	. EXTREME WEAR PRESENT INDICATES PARTS HAD BEEN IN CONSTANT CONTACT AS OPPOSED TO START-UP/SHUT-DOWN MOTION.		1	L	7	1 	3O	3	O		2A3 	1E10				 
1995111300190	19951113	00190	CE 	1995	11	13	95ZZZX6145 	1	19950824	G	3233	98820152	ACTUATOR 			CESSNA	172 	172RG 	2072438	CE 										MLG	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	9639B	7476 			9267	172RG0937				THE RADIUS OF THE ACTUATOR APPEARED TO BE CRACKED, THE PART WAS REMOVED AND DYE PENETRANT INSPECTION PERFORMED. FOUND N	UMEROUS CRACKS AROUND THE RADIUS WHERE THE MAIN GEAR ACTUATING GEAR IS BOLTED TO THE ACTUATOR. THE BOSS FOR THE SHAFT A	ND BEARING WHICH ALIGN THE JACK WAS CRACKED ALMOST ALL THE WAY AROUND. FURTHER INVESTIGATION SHOWED SIMILAR CRACKS ON T	HE OTHER MAIN GEAR ACTUATOR. SUBMITTER SUGGESTS THESE PARTS BE INSPECTED WITH DYE PENETRANT AT 5,000 HRS AND THEN EACH	 1,000 HRS THEREAFTER OR ANY TIME THE GEAR CONTACTS THE GROUND IN OTHER THAN FULLY EXTENDED OR FULLY RETRACTED POSITION.		1	H	7	1 	3O				3A17 					 
1995111300194	19951113	00194	CE 	1995	11	13	95ZZZX6149 	1	19950913	G	2150	10138470037	CONDENSER 			BEECH 	200 	200BEECH 	1152920	CE 										ACFT AIR COND	EXPLODED 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	40RA	4460 				BB104				LOUD BANG OCCURRED DURING GROUND RUN. FOUND FREON SYSTEM DEPLETED. FURTHER TROUBLESHOOTING REVEALED ACFT CONDENSER HAD	 'EXPLODED', AND HAD TORN AWAY FROM ITS MOUNTING STRUCTURE. LOOKING FOR THE CAUSE OF THE EXPLOSION, DISCOVERED THE CLUT	CH ON THE FREON COMPRESSOR, WHICH HAD BEEN INSTALLED 2.5 HRS PREVIOUSLY, WAS SEIZED IN THE ON POSITION. THIS SYSTEM IS 	EQUIPPED WITH A HIGH PRESSURE CUT-OFF SWITCH, BUT SINCE THE CLUTCH WAS ON CONTINUOUSLY, THERE WAS NO PROTECTION FROM AN 	OVERPRESSURE SITUATION.		1	L	7	2 	4T				A24CE 					 
1995111300195	19951113	00195	SO 	1995	11	13	95ZZZX6150 	1	19950926	G	2720	96212000	TORQUE TUBE 			PIPER 	PA34 	PA34200T 	7103406	SO 										RUDDER	ELONGATED HOLES 	B		A	APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	666HL	11400				347770235				RUDDER LOWER TORQUE TUBE HAS MOTION IN RELATION TO END FITTING. HOLES IN TORQUE TUBE ELONGATED. AD 92-08-04 PREVIOUSLY	 C/W BY INSPECTION, HOWEVER, FIX AS CALLED OUT IN AD NOTE DOES NOT CURE PROBLEM. SUBMITTER STATED WALL THICKNESS OF RUD	DER TORQUE TUBE IS INSUFFICIENT TO SUPPORT TORQUE LOADS. RECURRING PROBLEM EVEN AFTER 'AD' COMPLIANCE. SUGGEST MANUFAC	TURER BUILD TORQUE TUBE TWICE AS THICK.			1	L	7	2 	3O				A7SO 					 
1995111300197	19951113	00197	SO 	1995	11	13	95ZZZX6152 	2	19951002	G	8530		PISTON 			CESSNA	172 	172F 	2072414	CE 	CONT 	O300 	O300C 	17022	SO 					NR 1 CYLINDER	BROKEN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	8636U		177 			17252538	31849D40			LOW COMPRESSION ON NR 1 CYLINDER (80/60) FOUND DURING ANNUAL INSPECTION. DISCOVERED OIL RING MISSING AND PISTON SKIRT B	ROKEN OFF. SUBMITTER SUSPECTS CAUSED BY IMPROPER CYLINDER INSTALLATION METHODS.					1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995111300198	19951113	00198	SO 	1995	11	13	95ZZZX6153 	1	19951004	G	7810	EL099005191	MUFFLER 			GULSTM	AA5 	AA5B 	3960105	SO 										CARBURETOR HEAT	CRACKED 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			SW	09	4546J	1466 				AA5B1283				CRACKS UNDER THE CARBURETOR HEAT SHROUD CAUSED RECIRCULATION OF EXHAUST GASSES AROUND THE CARBURETOR HEAT VALVE, THEREBY	, CAUSING A PARTIAL POWER LOSS. SUBMITTER STATED ROUTINE INSPECTION OF THIS AREA WILL REVEAL HEAT WARPAGE PRIOR TO FAIL	URE.				1	L	7	1 	3O				A16EA 					 
1995111300199	19951113	00199	CE 	1995	11	13	95ZZZX6154 	1	19950817	G	2750	0706127	DRIVE ASSY 			CESSNA	182 	TR182 	2072735	CE 										LT FLAP	BROKEN 	D				O				OTHER 				F	W		FLT CONT AFFECTED 	INADEQUATE Q C 		LD	LANDING 	1			SW	17	9349R	2225 				R18200694				DURING A LANDING, PILOT NOTICED THE LT FLAP DID NOT COME DOWN. AN INSPECTION REVEALED THE FLAP DRIVE ASSY WAS BROKEN BE	TWEEN THE STEEL SHAFT AND THE BELLCRANK. FURTHER INSPECTION REVEALED THE WELD BETWEEN THE TWO PARTS WAS DONE POORLY. T	HE WELD WAS ONLY ONE-QUARTER OF THE WAY AROUND THE SHAFT, AND, ALSO, IN AN ANGLE WHICH PUT THE DRIVE FLAP ASSY IN A POSI	TION WHICH COULD NOT HANDLE MUCH STRESS.			1	H	7	1 	3O				3A13 					 
1995111300200	19951113	00200	SO 	1995	11	13	95ZZZX6155 	1	19950816	G	5102	3301	REGULATOR 			BALWKS	FIREFY	FIREFLY8B 	1050110	SO 										PILOT LIGHT	INTERMITTENT 	D				O				OTHER 				O			OTHER 			CR	CRUISE 	1			WP	09	9024R	374 				F3B180				FUEL FLOW TO THE BURNER PILOT LIGHTS FAILED IN THE OFF POSITION DURING FLIGHT. INITIAL RE-LIGHT ATTEMPTS WERE UNSUCCESS	FUL. FIRE 2 SYSTEM USED TO SUBSTITUTE FOR THE PILOT LIGHTS UNTIL LANDING WAS COMPLETED. AFTER LANDING, PILOT LIGHT OPE	RATION WAS NORMAL. WHEN CHECKED BY MECHANIC, REGULATOR FLOW AND PRESSURE OUTPUT WERE NORMAL. TWO FLIGHTS WERE MADE WIT	H NO RECURRENCE OF PROBLEM. ON 3RD FLIGHT, PILOT LIGHTS FAILED AGAIN. AFTER LANDING, PILOT LIGHT SYSTEM OPERATION WAS 	NORMAL. REPLACEMENT OF THE SUSPECT REGULATOR CURED PROBLEM.		1	B	0	0 					A14SO 					 
1995111300201	19951113	00201	SO 	1995	11	13	95ZZZX6156 	1	19950901	G	5711	6676200	SPAR PLATE 		6205300 	PIPER 	PA28 	PA28140 	7102802	SO 										RT WING	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	1942Z	7000 				2822849				FOUND DISSIMILAR METAL CORROSION BETWEEN AFT WING SPAR AND SPAR ATTACH PLATE. SUBMTTER SUGGESTED TO REMOVE PLATE AND PU	T INSULATOR COMPOUND BETWEEN PLATE AND SPAR. ALSO, FOUND DISSIMILAR METAL CORROSION BETWEEN STABILATOR ATTACH FITTING S	TEEL CHANNELS AND REAR BULKHEAD.				1	L	7	1 	3O				2A13 					 
1995111300202	19951113	00202	SO 	1995	11	13	95ZZZX6157 	1	19950901	G	5711	6676200	SPAR PLATE 		6205300 	PIPER 	PA28 	PA28140 	7102802	SO 										LT WING	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	1942Z	7000 				2822849				FOUND DISSIMILAR METAL CORROSION BETWEEN AFT WING SPAR AND SPAR ATTACH PLATE. SUBMTTER SUGGESTED TO REMOVE PLATE AND PU	T INSULATOR COMPOUND BETWEEN PLATE AND SPAR. ALSO, FOUND DISSIMILAR METAL CORROSION BETWEEN STABILATOR ATTACH FITTING S	TEEL CHANNELS AND REAR BULKHEAD.				1	L	7	1 	3O				2A13 					 
1995111300203	19951113	00203	GL 	1995	11	13	95ZZZX6158 	3	19951024	G	6114		HUB 			BEECH 	35 	V35 	1151538	CE 						HARTZL	HCA3V	PHCA3VF4 	GL 	HUB ARMS	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	5915S		465 			D8120		BL164		PROPELLER WAS LAST OVERHAULED 7-21-91. WAS SENT IN FOR OVERHAUL. AFTER TEAR DOWN AND CLEANING, FOUND TO HAVE EXCESSIVE	 CORROSION ON THE HUB PILOT TUBES AND AROUND THE HUB SPIDER ARMS INBOARD OF THE BEARINGS SEAT. CORROSION ON THE SPIDER 	ARMS COULD RESULT IN A CRACK AND CAUSE BLADE SEPARATION FROM HUB.				1	L	7	1 	3O				3A15 		5	C	P6EA	 
1995111300204	19951113	00204		1995	11	13	95ZZZX6159 	3	19950903	G	6111		BLADE 			AMTR 	LNCAIR	235LANCAIR 	05612ML	GL 										PROPELLER	FAILED 	D		A		E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			E			VIBRATION/BUFFET 			CR	CRUISE 	1			SW	15	53RM	180 				182				AFTER TAKEOFF AND CLIMB TO 8,500 FEET ALTITUDE, LEVELED OFF IN NORMAL CRUISE FLIGHT. I.A.S. 220 MPH. WTH NO PRIOR WARN	ING, SEVERE VIBRATION OCCURRED. SHUT DOWN ENGINE AND DECLARED EMERGENCY AND MADE A SUCCESSFUL FORCED LANDING. GROUND I	NSPECTION DISCLOSED THE WOODEN PROPELLER FAILED. ONE-THIRD OF ONE BLADE TRAILING EDGE PARTED IN-FLIGHT.				1	L	7	1 	30			RT	EXPA1L71					 
1995111300205	19951113	00205	GL 	1995	11	13	95ZZZX6160 	3	19951024	G	6111		BLADE 			BBAVIA	8 	8KCAB 	2110612	CE 						HARTZL	HCC2Y	HCC2YK1 	GL 	SHANK	SEAL FAILED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	03	5036J		348 		E83260	47479		DN1558		PROPELLER WAS INSIDE OF OVERHAUL TIMES. IT WAS LEAKING GREASE. AFTER DISASSEMBLY, THE TEFLON TAPE AROUND THE SHANK THA	T THE BLADE SEAL RIDES ON HAD FALLEN OFF; THUS, CAUSING THE LEAK. ALSO, THE BLADE SEAL HAD STARTED CUTTING INTO THE BLA	DE SHANK. ALSO, NOTICED THERE WAS BAD CORROSION AROUND THE SAME AREA. POSSIBLY CAUSED BY THE GREASE WHICH APPEARED TO 	BE ONE THAT IS NOT APPROVED BY HARTZELL SB 159A. THE ABOVE CONDITION MAY HAVE RESULTED IN BLADE FAILURE.			1	H	7	1 	3O				A21CE 		5	C	P920	 
1995111300206	19951113	00206	GL 	1995	11	13	95ZZZX6161 	3	19951024	G	6111		BLADE 			BBAVIA	8 	8KCAB 	2110612	CE 						HARTZL	HCC2Y	HCC2YK1 	GL 	SHANK	SEAL FAILED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	03	5036J		348 		E84429	47479		DN1558		PROPELLER WAS INSIDE OF OVERHAUL TIMES. IT WAS LEAKING GREASE. AFTER DISASSEMBLY, THE TEFLON TAPE AROUND THE SHANK THA	T THE BLADE SEAL RIDES ON HAD FALLEN OFF; THUS, CAUSING THE LEAK. ALSO, THE BLADE SEAL HAD STARTED CUTTING INTO THE BLA	DE SHANK. ALSO, NOTICED THERE WAS BAD CORROSION AROUND THE SAME AREA. POSSIBLY CAUSED BY THE GREASE WHICH APPEARED TO 	BE ONE THAT IS NOT APPROVED BY HARTZELL SB 159A. THE ABOVE CONDITION MAY HAVE RESULTED IN BLADE FAILURE.			1	H	7	1 	3O				A21CE 		5	C	P920	 
1995111300207	19951113	00207	SO 	1995	11	13	95ZZZX6162 	2	19950903	G	8530	6674	CYLINDER 			CESSNA	150 	150F 	2071814	CE 	CONT 	O200 	O200A 	17020	SO 					ROCKER BOSS	FRACTURED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			EA	05	6495F	3519 	1359 		A50222	15063095	682888A			ALL ROCKER SHAFT BOSSES FRACTURED DUE TO FATIGUE ALLOWING ROCKER SHAFT AND ROCKER ARMS TO FALL AWAY FROM CYLINDER. ENGI	NE RAN EXTREMELY ROUGH AND EMERGENCY LANDING WAS COMPLETED WITHOUT INCIDENT.					1	H	7	1 	3O	3	O		3A19 	E252				 
1995111300208	19951113	00208	EA 	1995	11	13	95ZZZX6163 	2	19951010	G	8530		CYLINDER 			CESSNA	172 	172RG 	2072438	CE 	LYC 	O360 	O360F1A6 	41514	EA 					NR 4	CRACKED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			GL	03	6105V					172RG0580	L2878136A			ENGINE BECAME ROUGH DURING FLIGHT. UPON LANDING AND INSPECTION, IT WAS DETERMINED THAT CYLINDER NR 4 WOULD NOT PASS CYL	INDER LEAKAGE TEST. AFTER FURTHER INSPECTION, CYLINDER WAS FOUND TO BE CRACKED ONE-HALF WAY AROUND CIRCUMFERENCE BETWEE	N FINS AT JUNCTION OF HEAD-TO-BARREL. CYLINDER WAS REPLACED AND ENGINE WAS RETURNED TO SERVICE. CYLINDER WAS BORED .01	0 INCH. ENGINE TT, 2,344.8 HRS. ENG SMOH, 319.8 HRS.			1	H	7	1 	3O	3	O		3A17 	E286				 
1995111300209	19951113	00209	CE 	1995	11	13	95ZZZX6164 	1	19951011	G	2430	6041A190	RELAY 			BEECH 	36 	A36 	1151604	CE 										BATTERY	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	03	3143M	164 				E2881				ELECTRICAL SYSTEM WOULD MOMENTARILY DROP OFF-LINE WHEN GEAR WAS RETRACTED. FOUND BATTERY AND STARTER RELAY TYPES REVERS	ED, INTERMITTENT DUTY RELAY INSTALLED IN BATTERY POSITION. INSTALLED NEW CORRECT P/N RELAYS IN BATTERY AND STARTER POSI	TIONS. NEW DIODES FOR BATTERY BUS AND NEW BATTERY. COMPLETED GEAR RETRACTION AND ELECTRICAL SYSTEM CHECK OUT. SYSTEM 	NOW OPERATES NORMALLY. IT APPEARS RELAYS WERE INCORRECTLY INSTALLED AT MANUFACTURER, NO LOG ENTRIES REFLECT ANY RELAY C	HANGES.		1	L	7	1 	3O				3A15 					 
1995111300210	19951113	00210	CE 	1995	11	13	95ZZZX6165 	1	19951018	G	5312	24130013	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD BAR ATTACH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	6105V	3734 				172RG0580				DURING ANNUAL INSPECTION, DETERMINED THAT UPPER AND LOWER BULKHEADS NEAR RUDDER BAR ATTACH POINTS WERE CRACKED. ALL BUL	KHEADS WERE REPLACED. SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS AREA DURING INSPECTION, WITH POSSIBLE REINFORCEMENT A	DDED.				1	H	7	1 	3O				3A17 					 
1995111300211	19951113	00211	CE 	1995	11	13	95ZZZX6166 	1	19951018	G	5312	24130014	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD BAR ATTACH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	6105V	3734 				172RG0580				DURING ANNUAL INSPECTION, DETERMINED THAT UPPER AND LOWER BULKHEADS NEAR RUDDER BAR ATTACH POINTS WERE CRACKED. ALL BUL	KHEADS WERE REPLACED. SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS AREA DURING INSPECTION, WITH POSSIBLE REINFORCEMENT A	DDED.				1	H	7	1 	3O				3A17 					 
1995111300212	19951113	00212	CE 	1995	11	13	95ZZZX6167 	1	19951018	G	5312	24130015	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD BAR ATTACH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	6105V	3734 				172RG0580				DURING ANNUAL INSPECTION, DETERMINED THAT UPPER AND LOWER BULKHEADS NEAR RUDDER BAR ATTACH POINTS WERE CRACKED. ALL BUL	KHEADS WERE REPLACED. SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS AREA DURING INSPECTION, WITH POSSIBLE REINFORCEMENT A	DDED.				1	H	7	1 	3O				3A17 					 
1995111300213	19951113	00213	CE 	1995	11	13	95ZZZX6168 	1	19951018	G	5312	24130016	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD BAR ATTACH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	6105V	3734 				172RG0580				DURING ANNUAL INSPECTION, DETERMINED THAT UPPER AND LOWER BULKHEADS NEAR RUDDER BAR ATTACH POINTS WERE CRACKED. ALL BUL	KHEADS WERE REPLACED. SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS AREA DURING INSPECTION, WITH POSSIBLE REINFORCEMENT A	DDED.				1	H	7	1 	3O				3A17 					 
1995111300214	19951113	00214	CE 	1995	11	13	95ZZZX6169 	1	19950912	G	5314	105420000191	KEEL 			BEECH 	76 	76 	1153005	CE 										RUD BAR ATTACH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	18929	3497 				ME6				DURING ANNUAL INSPECTION, KEEL WAS FOUND CRACKED AT RUDDER BAR ATTACH POINTS. KEEL WAS REPLACED AND ACFT RETURNED TO SE	RVICE. SUGGEST CLOSE INSPECTION OF THIS AREA AT INSPECTIONS. POSSIBLE REINFORCEMENT IS SUGGESTED.					1	L	7	2 	3O				A29CE 					 
1995111300215	19951113	00215	CE 	1995	11	13	95ZZZX6170 	1	19951023	G	3213	50411082	BEARING 			CESSNA	414 	414A 	2075907	CE 										MLG STRUT	WRONG PART 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	05	111KR	3120 				414A0429				AD 90-02-13 MLG INNER BEARING, AD IS APPLICABLE TO CESSNA 414-0001 THROUGH 414-A0340. WHEN RESEALING MAIN GEAR STRUT ON	 414-A0429, FOUND P/N 5041108-2 INSTALLED. THIS IS THE SECOND AIRCRAFT THAT THE AD IS NOT APPLICABLE BY S/N AND HAD THE	 WRONG P/N INNER BEARING INSTALLED. SEE M OR D DATED SEPTEMBER, 1995, ON CESSNA 340A0973, NC340HH. AD AND CESSNA SB NE	EDS TO BE REVISED TO INCLUDE ALL SERIAL NUMBERS.			1	L	7	2 	3O				A7CE 					 
1995111300216	19951113	00216	CE 	1995	11	13	95ZZZX6171 	1	19951011	G	3252		DAMPENER 			CESSNA	182 	182Q 	2072732	CE 										NOSEWHEEL	MISREPAIRED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	03	4468N					18267639				PILOT COMPLAINED OF EXCESSIVE NOSEWHEEL SHIMMY. EXAMINATION FOUND SHIMMY DAMPENER WAS EMPTY, HAD PREVIOUSLY BEEN FILLED	 WITH MOTOR OIL INSTEAD OF 5606 AND FILL PORT HAD BEEN TAPPED OVERSIZE, THREADS TAPPED CROOKED (ON AN ANGLE), AND AN OVE	RSIZED BOLT INSTALLED (OBVIOUSLY TOO LONG AND CUT SHORTER). SINCE THE STAT-O-SEAL WOULD NOT FIT ON LARGER BOLT, A PLAIN	 WASHER WITH AN O-RING INSTALLED. THIS, ALONG WITH CROOKED THREADS, CAUSED SHIMMY DAMPENER TO BE PUMPED EMPTY. THE BOL	T HEAD HAD OBVIOUSLY BEEN HAND-DRILLED. THIS 'REPAIR' HAD BEEN PERFORMED AT AN OWNER-ASSISTED ANNUAL.		1	H	7	1 	3O			NT	3A13 					 
1995111300217	19951113	00217	CE 	1995	11	13	95ZZZX6172 	1	19951013	G	7931	9638405811	INDICATOR 			BEECH 	58 	58P 	1152744	CE 										ENG OIL PRESS	MALFUNCTION 	D				E				ENGINE SHUTDOWN 				N			FALSE WARNING 			CL	CLIMB 	1			SW	15	584DP					TJ76				APPROXIMATELY 5 MINUTES AFTER TAKEOFF, LT ENGINE OIL PRESSURE INDICATION DECREASED TO ZERO, THEN BELOW ZERO WITHIN 2 MIN	UTES. SINCE OIL TEMP WAS STILL INCREASING AFTER DEPARTURE, NO RELIABLE MEANS OF DETERMINING ENGINE OIL CONDITION WAS AV	AILABLE. ENGINE WAS SHUT DOWN IN-FLIGHT TO PRECLUDE POSSIBLE DAMAGE. DIAGNOSIS OF 3 IN 1 INSTRUMENT REVEALED THE OIL P	RESSURE NEEDLE WAS LOOSE ON SHAFT.			1	L	7	2 	3O				A23CE 					 
1995111300218	19951113	00218	SO 	1995	11	13	95ZZZX6173 	1	19951021	G	3213	400761	BOLT 		9564307 	PIPER 	PA28 	PA28R200 	7102811	SO 										MLG TRUSS	MISINSTALLED 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	4564F					28R7635454				INSPECTION FOUND AN AN26-25 BOLT IN RIGHT MAIN GEAR TRUSS BRACKET INSTALLED UPSIDE DOWN.						1	L	7	1 	3O				2A13 					 
1995111300219	19951113	00219	SO 	1995	11	13	95ZZZX6174 	1	19951026	G	3230	400218	BOLT 			PIPER 	PA28 	PA28R200 	7102811	SO 										NLG DRAG LINK	MISINSTALLED 	G				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	25	4564F					28R7635454				FOUND BOTH UPPER NLG DRAG LINKS TO ENGINE MOUNT ATTACHMENT BOLTS INSTALLED BACKWARDS TO PICTURE AND DRAWING CONTAINED IN	 AC4316 6/93 ISSUE AND/OR PIPER SM 720-816, FIGURE 7A-2.					1	L	7	1 	3O				2A13 					 
1995111300418	19951113	00418	CE 	1995	11	13	95ZZZX6176 	1	19951002	G	5510	0532001202	STABILIZER 			CESSNA	172 	172N 	2072434	CE 										HORIZ	CORRODED 	H		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	5138K	2410 				17273982				DURING THE ANNUAL INSPECTION, THE HORIZONTAL STABILIZER ASSEMBLY WAS FOUND CORRODED BEYOND ECONOMICAL REPAIR LIMITS. IN	TERNAL PORTION OF STABILIZER ASSY IS VERY DIFFICULT TO INSPECT WITH THE ELEVATOR ASSY INSTALLED. SUBMITTER RECOMMENDS E	XTRA EFFORT TO THOROUGHLY INSPECT THE INTERNAL PORTION OF THE STABILIZER ASSY DURING ANNUAL INSPECTIONS.				1	H	7	1 	3O			NT	3A12 					 
1995111300419	19951113	00419	SO 	1995	11	13	95ZZZX6177 	1	19951002	G	5711		SPAR 			AMRGEN	AG5B 	AG5B 	3990100	SO 										RT WING BOLTS	HOLES ELONGATED 	H		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	1193A	791 				10021				PILOT SQUAWKED THAT AT CERTAIN POWER SETTINGS AND FLIGHT ATTITUDE, THE RT WING WOULD DEMONSTRATE A SLIGHT FORE AND AFT M	OVEMENT. INSPECTED WING ATTACH SHOULDER BOLTS IAW AM GEN SB 185. FOUND THE RT WING FORWARD WING SPAR BOLT HOLE ENLARGE	D BEYOND LIMITS. WING AND SPAR REPAIRED IAW AM GEN SM. FLIGHT CHK OK.				1	L	7	1 	3O			NT	1L71 					 
1995111300420	19951113	00420	CE 	1995	11	13	95ZZZX6178 	1	19950901	G	7810	77551	WYE ASSY 		2450200 	BEECH 	60 	60 	1153602	CE 										EXHAUST SYSTEM	CRACKED 	G		A		O				OTHER 				A			FLAME/FIRE 			CR	CRUISE 	1			GL	05	612WB	2160 				P393				AN INTENSE IN-FLIGHT FIRE OCCURRED WHEN A CRACK IN THE LEFT ENGINE WYE EXHAUST ASSY DEVELOPED AND ALLOWED HOT EXHAUST GA	S TO LEAK THROUGH LOOSE COUPLING INTO ACCESSORY SECTION. THE CRACK IN THE WYE ASSY COULD NOT BE DETECTED UNTIL AIR PRES	SURE WAS FORCED INTO EXHAUST SYSTEM BY BLOCKING OFF PORTS. SUBMITTER SUGGESTS THIS PROCEDURE BE ACCOMPLISHED AT LEAST O	N ANNUAL INSPECTIONS.			1	L	7	2 	3O				A12CE 					 
1995111300421	19951113	00421	SW 	1995	11	13	95ZZZX6179 	1	19951018	G	2720	500012251	CONTROL CABLE 			GULSTM	690TP 	690A 	0141722	SW 										RUDDER AFT	FRAYED 	B		A	FB2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	66GW					11174				DURING C/W TWIN COMMANDER SB 195B, FOUND ONE AFT RUDDER CABLE TO HAVE NUMEROUS STRANDS BROKEN. THE INSTRUCTIONS IN THE 	SB DO NOT ADDRESS THE REMOVAL AND INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14. THIS IS	 THE ONLY WAY TO PROPERLY INSPECT THESE CABLES. HAVE FOUND MANY AIRCRAFT WITH CABLE STRANDS BROKEN BEYOND THE LIMITS IN	 THE SB WHILE INSPECTING CABLES IN THIS MANNER. SUBMITTER SUGGESTS OWNERS COMPLY WITH SI-199, WHICH INSTALLS LARGER PUL	LEYS AT THIS LOCATION.		1	H	7	2 	3T			 	2A4 					 
1995111300422	19951113	00422	SW 	1995	11	13	95ZZZX6180 	1	19951018	G	2720	500012253	CONTROL CABLE 			GULSTM	690TP 	690A 	0141722	SW 										RUDDER AFT	FRAYED 	B		A	FB2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	66GW					11174				DURING C/W TWIN COMMANDER SB 195B, FOUND ONE AFT RUDDER CABLE TO HAVE NUMEROUS STRANDS BROKEN. THE INSTRUCTIONS IN THE 	SB DO NOT ADDRESS THE REMOVAL AND INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14. THIS IS	 THE ONLY WAY TO PROPERLY INSPECT THESE CABLES. HAVE FOUND MANY AIRCRAFT WITH CABLE STRANDS BROKEN BEYOND THE LIMITS IN	 THE SB WHILE INSPECTING CABLES IN THIS MANNER. SUBMITTER SUGGESTS OWNERS COMPLY WITH SI-199, WHICH INSTALLS LARGER PUL	LEYS AT THIS LOCATION.		1	H	7	2 	3T			 	2A4 					 
1995111300423	19951113	00423	CE 	1995	11	13	95ZZZX6181 	1	19951014	G	3230	08421224	DRAG LINK 			CESSNA	310 	310R 	2074245	CE 										NLG LOWER	WRONG PART 	D	L			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	07	4086C					310R1367				DURING ANNUAL INSPECTION, FOUND NOSE GEAR LOWER DRAG LINK ASSY TO HAVE INCORRECT PART NUMBER. FOUND THAT PART HAD BEEN 	REPLACED 3 YEARS PREVIOUSLY DURING REPAIR FOR NOSE GEAR COLLAPSE. LOG BOOK ENTRY SHOWED CORRECT PART NUMBER, BUT PART I	NSTALLED WAS A DIFFERENT DASH NUMBER. WHILE NOT NOTED AS SUCH IN LOG, PART APPEARED TO BE A USED PART. THIS PART DID N	OT FIT PROPERLY AND SHOULD HAVE BEEN EASY TO SEE UPON INSTALLATION AND DURING SUBSEQUENT INSPECTIONS.			1	L	7	2 	3O				3A10 					 
1995111300424	19951113	00424	EA 	1995	11	13	95ZZZX6182 	2	19950912	G	7414		CONTACT POINTS 	BENDIX 	S6LN20 	PIPER 	PA25 	PA25235 	7102504	SO 	LYC 	O540 	O540G1A5 	41532	EA 					LT MAG	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	13	8566L					254990				CONTACT POINTS' SOFT PLASTIC THAT RIDES THE CAM WORE DOWN UNTIL THERE WAS NO CONTACT POINT OPENING (MAG FAILURE). THE R	OTATING MAGNET CONTINUED TO MAKE ELECTRIC ENERGY, SENDING IT TO THE CAPACITOR, OVERLOADING THE CAPACITOR, CAUSING IT TO 	BURN ITSELF OUT. THIS HAPPENED TO BOTH MAGS 1-21 HRS SMOH AND 1-23 HRS. ALL PARTS WERE TCM, NEW MFG, PURCHASED AUG, 19	95.			1	L	7	1 	3O	3	O		2A10 	E295				 
1995111300425	19951113	00425	EA 	1995	11	13	95ZZZX6183 	2	19950912	G	7414		CONTACT POINTS 	BENDIX 	S6LN21 	PIPER 	PA25 	PA25235 	7102504	SO 	LYC 	O540 	O540G1A5 	41532	EA 					RT MAG	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	13	8566L					254990				CONTACT POINTS' SOFT PLASTIC THAT RIDES THE CAM WORE DOWN UNTIL THERE WAS NO CONTACT POINT OPENING (MAG FAILURE). THE R	OTATING MAGNET CONTINUED TO MAKE ELECTRIC ENERGY, SENDING IT TO THE CAPACITOR, OVERLOADING THE CAPACITOR, CAUSING IT TO 	BURN ITSELF OUT. THIS HAPPENED TO BOTH MAGS 1-21 HRS SMOH AND 1-23 HRS. ALL PARTS WERE TCM, NEW MFG, PURCHASED AUG, 19	95.			1	L	7	1 	3O	3	O		2A10 	E295				 
1995111300426	19951113	00426	EA 	1995	11	13	95ZZZX6184 	2	19951016	G	7414	ES10391584	DISTRIBUTOR BLK 	BENDIX 	S4LN1209 	PIPER 	PA28 	PA28R201 	7102816	SO 	LYC 	O360 	IO360C1C6 	41514	EA 					RT MAG	LOOSE BUSHING 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	11562	332 			A199911	28R7837194	L1870651A			DURING PREFLIGHT RUN-UP, FOUND RIGHT MAGNETO INOPERATIVE. REMOVED AND DISASSEMBLED MAG. FOUND DISTRIBUTOR BLOCK CENTER	 BUSHING LOOSE. THIS CAUSED TIMING GEAR TO SHIFT POSITION AND CHANGE INTERNAL TIMING. OTHER DAMAGE NOTED WAS DEFORMED 	TIMING GEAR. TIMING GEAR SPARK FINGER SHEARED SPARK TOWERS FROM DISTRIBUTOR BLOCK AND CONTAMINATED MAG WITH BRONZE SHAV	INGS.			1	L	7	1 	3O	3	O		2A13 	1E10				 
1995111300427	19951113	00427	CE 	1995	11	13	95ZZZX6185 	1	19951018	G	5711		SPAR 			CESSNA	150 	152 	2071835	CE 										LT WING REAR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	714YE	4086 				15279531				DURING ANNUAL INSPECTION, A CRACK 3.25 INCHES LONG WAS FOUND IN LT WING REAR SPAR. THE CRACK STARTED AT FLAP PULLEY BRA	CKET, P/N 0460205-102, AND EXTENDED OUTBOARD, RUNNING HORIZONTALLY 3.25 INCHES. INBOARD HALF OF SPAR WAS REPLACED AND A	CFT RETURNED TO SERVICE. CRACK POSSIBLY CAUSED DUE TO COLD WORKING OF THE SPAR BY THE FLEXING OF THE BRACKET DURING FLA	P CYCLES.			1	H	7	1 	3O			NT	3A19 					 
1995111300428	19951113	00428	CE 	1995	11	13	95ZZZX6186 	1	19951018	G	2750	6560261	PUSH ROD TUBE 			CESSNA	500 	S550 	2076607	CE 										FLAP	RUSTED THROUGH 	B		A	IW1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	29AU	3356 				S5500019				DURING COURSE OF ROUTINE INSPECTION, SUSPICIOUS 'BUBBLES' ON PUSH/PULL TUBE WERE POKED AT WITH SCRIBE AND WENT THROUGH T	UBE. AFTER SCRAPING AWAY PAINT AND SCALE, FOUND LARGE OBLONG HOLE RUSTED THROUGH BOTTOM OF PUSH/PULL ROD NEAR INBOARD E	ND OF RIGHT INBD FLAP PUSH/PULL ROD. HOLE APPROX .3750 INCH BY 2.25 INCHES. REPLACED WITH NEW PART. RECOMMEND A ONE-T	IME ALERT SERVICE INFO LETTER ADDRESSING S550 AND 560 AIRCRAFT FOR ONE TIME INSPECTION AND POSSIBLE INTERNAL EXAMINATION	 OF TUBE.		1	L	7	2 	4F			RT	A22CE 					 
1995111300429	19951113	00429	EU 	1995	11	13	95ZZZX6187 	1	19951016	G	7714	430121302	HARNESS 			BOLKMS	117 	BK117A3 	5626015	EU 										N1 SPEED	PIN CORROSION 	B			BAQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	932CJ					7024				PILOT REPORTED N1 SPEED FLUCTUATIONS AND ENGINE LOW LIGHT ILLUMINATED. REMOVED FORWARD ELECTRICAL HARNESS AND CLEANED C	ORROSION OFF PINS AND CONNECTOR. GROUND RUN AND FLEW AIRCRAFT, COULD NOT DUPLICATE REPORTED MALFUNCTION.					1	G	7	2 	3U				H13EU 					 
1995111300430	19951113	00430	SW 	1995	11	13	95ZZZX6188 	1	19951010	G	2916	206076022101	RESERVOIR 			BELL 	206 	206B 	1181511	SW 										HYD SYSTEM	FLUID LOSS 	B			DFUR	A				UNSCHED LANDING 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SO	09	67605	525 				5176				PRECAUTIONARY LANDING WAS MADE DUE TO LOSE OF HYDRAULIC FLUID. MAINTENANCE INSPECTION REVEALED THAT WATER HAD GOTTEN IN	TO THE RESERVOIR WHICH IN TURN CAUSED FOAM AND SIPHONING OF FLUID THAT DRAINED THE TANK THROUGH THE OVERFLOW LINE.					1	G	7	1 	3U				H2SW 					 
1995111300431	19951113	00431	SW 	1995	11	13	95ZZZX6189 	1	19950918	G	5553	206033426033	SUPPORT FITTING 			BELL 	206 	206B 	1181511	SW 										VERTICAL FIN	SHEARED 	B			DFUR	O				OTHER 				O			OTHER 			LD	LANDING 	1			SO	09	67641	433 				5182				TAIL SKID CONTACTED GROUND IN SLOW REARWARD DRIFT. VERTICAL FIN CAME OFF. SUPPORT FITTING ON TAIL BOOM SHEARED ALLOWIN	G VERTICAL FIN TO COME OFF.					1	G	7	1 	3U				H2SW 					 
1995111300432	19951113	00432	EU 	1995	11	13	95ZZZX6190 	1	19950612	G	5400	4210205	PULLEY DRUM 		42103 	AMD 	FALC50	FALCON50MYST	2730106	EU 										ENGINE WINCH	FAILED 	B		A	QK2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	86AK				170	052				DURING ENGINE REMOVAL, NR 2 CENTER POSITION USING THE MFR INSTALLED AVIAC HOISTING WINCH, HOIST FAILED ALLOWING ENG TO R	APIDLY DROP BREAKING CABLE AND HITTING FLOOR. CABLE STOW TORQUE WAS CHECKED USING HOIST WINCH TORQUE TOOL. AFTER PROPE	R STOW, TORQUE WAS ESTABLISHED. ENGINE MOUNT BOLTS WERE REMOVED. ENGINE WAS THEN LOWERED MANUALLY A SMALL AMOUNT TO AI	D AND EASE ENGINE REMOVAL. A .25 INCH DRIVE AIR RATCHET WAS ADAPTED TO WINCH DRIVE SOCKET. AT THE INSTANT OR SHORTLY A	FTER, AS ENGINE WAS LOWERED, A SCREAMING NOISE WAS HEARD. THE RATCHET WAS PULLED OFF THE DRIVE AND SECONDS LATER, THE E	NGINE WAS LAYING ON THE FLOOR. THE HOIST CABLE SNAPPED.	2	L	7	3 	4F				A46EU 					 
1995111300434	19951113	00434	CE 	1995	11	13	95ZZZX6192 	1	19951019	G	3610	555230012	JOINT 			CESSNA	500 	550 	2076604	CE 										RT NACELLE	CRACKED 	B			HIMR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	57AJ					5500085				INSPECTION REVEALED BLEED AIR JOINT WITH A CRACK APPROX 1 INCH BEYOND LIMITS. POSSIBLY CAUSED BY UNINTENTIONAL FORCE AP	PLIED TO AIR JOINT.					1	L	7	2 	4F				A22CE 					 
1995111300435	19951113	00435	CE 	1995	11	13	95ZZZX6193 	1	19950929	G	2810		LINE 			CESSNA	500 	550 	2076604	CE 										FUEL VENT	BOGUS 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	15	2FOR					5500219				REMOVED RUBBER HOSE (GARDEN HOSE) FROM THE FUEL VENT LINE AND INSTALLED PROPER PLUMBING PER CITATION PARTS MANUAL.						1	L	7	2 	4F				A22CE 					 
1995111300436	19951113	00436	CE 	1995	11	13	95ZZZX6194 	1	19951001	G	2820	60160165	CHECK VALVE 			LEAR 	60 	60LEAR 	5170707	CE 										FUEL CELL	DETACHED 	B	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	26011	87 				013				THE FUSELAGE FUEL CELL LOWER CHECK VALVES - 3 OF 4 WERE FOUND LOOSE HANGING FROM THE BONDING WIRE. THE CLAMPS WERE NOT 	LOOSE, THEY JUST FELL OUT OF THE BLADDER NIPPLE.					2	L	7	2 	4F			RT	A10CE 					 
1995111300437	19951113	00437	SW 	1995	11	13	95ZZZX6195 	1	19951016	G	7120	47612171123	MOUNT 			BELL 	47 	47G5A 	1181034	SW 										ENG LT MOUNT	IMPROPER WELD 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	17	4348P	290 			AF130	25059				ENGINE MOUNT PAINT STRIPPED AND CLEANED FOR MAGNAFLUX TO PERFORM 1,200-HOUR INSPECTION. WELD JOINING TUBE TO LT MOUNT F	ITTING INCOMPLETE (MISSING .50 INCH OF WELD). REPAIRED BY WELDING.					1	G	7	1 	3O				2H3 					 
1995111300438	19951113	00438	WP 	1995	11	13	95ZZZX6196 	1	19951016	G	7921	8544171	COOLER 			HUGHES	369 	369D 	4470706	WP 										ENGINE OIL	LEAKING 	B			EOOR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	4571V					490487D				OIL COOLER WAS FOUND LEAKING IN CORE AREA. REMOVED AND REPLACED OIL COOLER. PART SENT IN FOR OVERHAUL.						1	G	7	1 	3U				H3WE 					 
1995111300439	19951113	00439	GL 	1995	11	13	95ZZZX6197 	2	19951019	G	7313	6890917	NOZZLE 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE FUEL	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y		1016 		2843	500716D	CAE830348			PILOT COMPLAINED OF POWER/N2 FLUCTUATING WITH COLLECTIVE INPUT. SUBSEQUENT INSPECTION REVEALED THE FUEL NOZZLE WAS AT F	AULT. REMOVED AND REPLACED NOZZLE AND PROBLEM WAS CURED. NOZZLE SENT IN FOR REWORK.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995111300440	19951113	00440	GL 	1995	11	13	95ZZZX6198 	2	19951005	G	7240	6870992K	COMBUSTION CASE 			BELL 	206 	206L 	1181522	SW 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	CRACKED 	B	S		LX5R	K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			GL	19	781LL	1318 			31292	45079	CAE835862			INVESTIGATION FOR LOSS OF POWER AND HIGH T.O.T., FOUND COMBUSTION CASE CRACKED.						1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995111300441	19951113	00441	GL 	1995	11	13	95ZZZX6199 	1	19950513	G	2430	X16799	CONTROL 	PRESTOLITE 		ENSTRM	F28 	280C 	3300505	GL 										OVERVOLTS	NOT INSTALLED 	D		A		A				UNSCHED LANDING 				B	W		SMOKE/FUMES/ODORS/SPARKS 	INADEQUATE Q C 		NR	NOT REPORTED 	1			EA	17	613LG					1145				FOLLOWING REBUILD, HELICOPTER WAS RETURNED TO SERVICE WITHOUT THE OVERVOLTAGE CONTROL INSTALLED. REGULATOR SPIKED AND C	OOKED RADIOS AND GYROS. CABIN FILLED WITH SMOKE. AIRCRAFT SUBSTANTIALLY DAMAGED IN SUBSEQUENT EMERGENCY LANDINGS. SUB	MITTER RECOMMENDS INSPECTION OF ALL ENSTROM WITH PRESTOLITE VOLTAGE REGULATORS AND LAMAR REGULATORS WITH YELLOW FIELD WI	RE BE INSPECTED FOR PRESENCE OF OVERVOLTAGE CONTROLS.			1	G	7	1 	3O				H1CE 					 
1995111700122	19951117	00122	NE 	1995	11	17	95ZZZX6201 	1	19951015	G	6510	S163561202002	COUPLING 			SKRSKY	S58T 	S58ET 	8141803	NE 										NR 8 COUPLING	DEFECTIVE 	A			NYBA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	47781		1722 		CHP001	58855				DURING A SAFETY INSPECTION, A MECHANIC NOTED NUMEROUS RUBBER SEGMENTS (CHUNKS) MISSING FROM EVERY OTHER SEGMENT ON THIS 	NEW FAA/PMA PART. THIS COUPLING WAS IN THE NR 8 POSITION DIRECTLY UNDER THE TAIL ROTOR GEARBOX ATTACHED TO THE TAIL ROT	OR GEARBOX INPUT. SUBMITTER STATED INADEQUATE RUBBER ON THIS NEW FAA/PMA PART. REPLACED FLEX COUPLING IAW S-58T MM.				2	G	7	2 	4U				1H11 					 
1995111700124	19951117	00124	EU 	1995	11	17	95ZZZX6203 	1	19950929	G	6220	11211418206	RING 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R HEAD	MISMFG 	B			DYRR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	07	527SF					7111				RINGS RECEIVED IN UNACCEPTABLE CONDITION. OUTSIDE CIRCUMFERENCE HAS EXCESSIVE MACHINE CHATTER MARKS. SOME MARKS CAN BE	 FELT BY RUNNING FINGER ACROSS THE OUTER RING SURFACE. REPLACED WITH NEW UNITS, CORRECTED PROBLEM.					1	G	7	2 	3U				H13EU 					 
1995111700125	19951117	00125	GL 	1995	11	17	95ZZZX6204 	2	19950911	G	7230	A6889093	BEARING 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					NR 2	MAKING METAL 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	911BH	277 			042	685	CAC40409			BEARING MAKING METAL. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995122800004	19951228	00004	EU 	1995	12	28	95ZZZX6205 	1	19950915	G	6320	4619201011	HOUSING 			BOLKMS	105 	BO105S 	5626006	EU 										M/R GEARBOX	FLANGE DAMAGE 	B			CZ4R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	01	491HL	5575 			2109180	S664				DURING DISASSEMBLY, THE RIGHT OIL PASSAGE O-RING FLANGE WAS FOUND DAMAGED. THE DAMAGE WAS OBVIOUSLY NOTED DURING LAST O	VERHAUL DUE TO THE INSTALLATION OF 2 O-RINGS TO MAKE IT SEAL.					1	G	7	2 	3U				H3EU 					 
1995111700126	19951117	00126	SW 	1995	11	17	95ZZZX6206 	1	19951030	G	6210	214015291103	EROSION SHIELD 		214015300107	BELL 	214 	214ST 	1182106	SW 										M/R BLADE	SEPARATED 	A	S	A	ALGA	A				UNSCHED LANDING 				D	E		INFLIGHT SEPARATION 	VIBRATION/BUFFET 		CR	CRUISE 	1			SW	03	390AL	3410 			A197	28198				IN CRUISE FLIGHT OVER THE GULF OF MEXICO, THE AIRCRAFT DEVELOPED A SEVERE VIBRATION. THE PILOT MADE AN IMMEDIATE PRECAU	TIONARY LANDING TO AN OFFSHORE DRILLING PLATFORM. EXAMINATION OF THE AIRCRAFT REVEALED THE LOWER EROSION SHIELD ON A MA	IN ROTOR BLADE HAD SEPARATED FROM THE BLADE.				2	G	7	2 	4U				H10SW 					 
1995111700127	19951117	00127	EU 	1995	11	17	95ZZZX6207 	1	19951020	G	5551	453005501	SPLICE ASSY 			ISRAEL	1124 	1124 	4500102	EU 										RT HORIZ STAB	CRACKED 	A			WJCA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	719CC					290				.25 INCH LONG WORKING CRACK .015 INCH DEEP. FOUND ON LOWER SPLICE ASSY HORIZONTAL STABILIZER, RT LOWER ATTACH FITTING. 	 HORIZONTAL STABILIZER BEING REMOVED TO BE SENT OUT TO REPLACE SPLICE ASSY. AIRCRAFT TT, 5,392 HRS. LANDINGS, 4,280.					2	M	7	2 	4F				A2SW 					 
1995111700128	19951117	00128	WP 	1995	11	17	95ZZZX6208 	1	19951025	G	6710	369A7010501	UNILOCK 			HUGHES	369 	369D 	4470706	WP 										CYCLIC	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R		934 		0125	1151D				PILOT COMPLAINED THE CYCLIC WOULD DRIFT AFT EVEN WITH TRIM SET. REPLACED UNILOCK, CURED THE PROBLEM. UNIT SENT IN FOR 	OVERHAUL.					1	G	7	1 	3U				H3WE 					 
1995111700129	19951117	00129	SW 	1995	11	17	95ZZZX6209 	1	19950922	G	6520	206340103101	SEAL 		2060404005 	BELL 	206 	206B 	1181511	SW 										T/R GEARBOX	LEAKING 	B		A	KUVR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	161BH	293 			AL010230	1675				INSTALLED NEW SEAL AND REVERSED WEAR SLEEVE TO FRESH RUNNING SURFACE TO REPAIR LEAK AT INPUT SEAL. NEW SEAL IS LEAKING 	AGAIN AFTER VERY SHORT TIME IN SERVICE. A COMMON PROBLEM, BUT NOT AFTER SO LITTLE TIME. INSPECTION INTERVAL FOR GEARBO	X IS 3,000 HRS. CHANGING SEAL SO OFTEN IS NOT DESIRABLE. SEAL IS OF NEW STYLE AND PART NUMBER, POSSIBLY NEW MANUFACTUR	ER. ADVISED BHT OF THIS PROBLEM.			1	G	7	1 	3U				H2SW 					 
1995111700130	19951117	00130	SW 	1995	11	17	95ZZZX6210 	1	19950922	G	6310	289052017	SEAL 		2060402703 	BELL 	206 	206B 	1181511	SW 										FREEWHEEL	LEAKING 	B		A	KUVR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	161BH	44 			B1261	1675				INSTALLED NEW SEAL AFTER OVERHAUL OF UNIT. STARTED LEAKING OIL AFTER VERY SHORT TIME IN SERVICE. NOT REALLY A COMMON P	ROBLEM. SUBMITTER STATED BELL SEEMS TO HAVE CHANGED MANUFACTURERS. SEAL IS BLACK INSTEAD OF USUAL ORANGE COLOR AND IS 	GARLOCK TYPE. SOMETHING SEEMS UNUSUAL ABOUT THE LIP, BUT CANNOT BE CONFIRMED AT THIS TIME. NOTIFIED BHT OF THIS PROBLE	M. AWAITING ADVICE.			1	G	7	1 	3U				H2SW 					 
1995111700131	19951117	00131	NE 	1995	11	17	95ZZZX6211 	2	19950926	G	7321	0164348670	FCU 		E2 	BOLKMS	BK117 	BK117C1 	5626025	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					ANTICIPATOR	DEFECTIVE 	D				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			EA	03	911TG	1378 			C555B	7506	18019			IN CRUISE FLIGHT, 60 PERCENT TORQUE WHEN ENGINE IS BEEPED TO 100 PERCENT, N2 TORQUE DROPS OFF 40 PERCENT, AND N1 DROPS O	FF 10-15 PERCENT. SEEMS TO OPERATE NORMALLY WHEN N2 IS AT 98-99 PERCENT.					1	G	7	2 	3U	3	U	NC	H13EU 	E19EU				 
1995021000226	19950210	00226	CE 	1995	2	10	95ZZZX622 	1	19950106	G	3246	40138A	WHEEL ASSY 			CESSNA	425 	425 	2076018	CE 										MLG	BEARING FAILED 	B			CSLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	410WA	1969 				4250221				FAILURE OF THE OUTER (SMALL) WHEEL BEARING RACE HAS BEEN NOTED AT APPROXIMATELY 2,000 HOUR INTERVALS ON THIS AIRCRAFT. B	EARING FAILURE IS INDICATED BY BLACK STREAKS COMING FROM THE CENTER OF THE WHEEL AND FROM UNDER THE DUST CAP. THREE WHE	ELS OF THIS TYPE HAVE FAILED IN THIS MANNER ON THIS AIRCRAFT. CYCLES, 3,557.				1	L	7	2 	3T			RT	A7CE 					 
1995111700143	19951117	00143	CE 	1995	11	17	95ZZZX6223 	1	19951009	G	2910		RESERVOIR 			BEECH 	99 	C99 	1154006	CE 										HYD SYSTEM	REQD SERVICE 	A			GUUA	O				OTHER 				O			OTHER 			CL	CLIMB 	1			SO	19	7209W					U224				APF/MIA - FLT 416B - PILOT REPORT: LANDING GEAR SLOW TO RETRACT. MAINTENANCE: BLED HYDRAULIC SYSTEM, PERFORMED GEAR S	WINGS. OPS/LEAKS GOOD. AIRCRAFT RELEASED.					1	L	7	2 	3T				A14CE 					 
1995111700144	19951117	00144	CE 	1995	11	17	95ZZZX6224 	1	19951001	G	7603	MS252534	THROTTLE SWITCH 			BEECH 	99 	C99 	1154006	CE 										RT POWER LEVER	OUT OF ADJUST 	A			GUUA	O				OTHER 				N			FALSE WARNING 			NR	NOT REPORTED 	1			SO	19	7209W					U224				FLL/MIA - FLT 174B - PILOT REPORT: GEAR HORN DOES NOT SOUND. MAINTENANCE: TROUBLESHOT AND DETERMINED RIGHT POWER LEVE	R NOT ACTUATING SWITCH. ADJUSTED RIGHT POWER LEVER SWITCH. RELEASED AIRCRAFT.					1	L	7	2 	3T				A14CE 					 
1995111700145	19951117	00145	CE 	1995	11	17	95ZZZX6225 	1	19951022	G	2911	1013880095	HYD ACCUMULATOR 			BEECH 	99 	C99 	1154006	CE 										LANDING GEAR	LOW CHARGE 	A			GUUA	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			SO	19	7209W					U224				MIA/FLL - FLT 470 - PILOT REPORT: LANDING GEAR DOES NOT RETRACT DURING TAKEOFF. MAINTENANCE SERVICED HYDRAULIC ACCUMUL	ATOR. OPS CHECK GOOD, AIRCRAFT RELEASED.					1	L	7	2 	3T				A14CE 					 
1995021000227	19950210	00227	CE 	1995	2	10	95ZZZX623 	1	19950118	G	2435	03601015	BEARING 	LEARSIEGLER 	23080025 	BEECH 	MU300 	400BEECH 		CE 										START/GEN	FAULTY 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	46FE	164 			7833	RK0016				DURING 500-HOUR BRUSH INSPECTION, FOUND BOTH END BEARINGS WOULD NOT PASS INSPECTION. THESE ARE THE NEW 1,000-HOUR BEARI	NGS. TOTAL TIME ON THEM WAS 163.8 HOURS.					2	H	7	2 	4F			RT	A16SW 					 
1995111700619	19951117	00619	SO 	1995	11	17	95ZZZX6238 	1	19951025	G	5412	5008906	BULKHEAD 			PIPER 	PA31T 	PA31T1 	7103126	SO 										NAC LT ENG INBD	CRACKED 	B			VIB6	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	6182	5923 				31T7904006				LEFT ENGINE NACELLE INBOARD LONGITUDINAL BULKHEAD IS CRACKED AT THE INBOARD UPPER BIRDCAGE MOUNT. CRACK IS LOCATED AT T	HE AFT RIVET HOLE. CRACK WAS DISCOVERED DURING A ROUTINE INSPECTION.					1	L	7	2 	3T				A8EA 					 
1995111700620	19951117	00620	SO 	1995	11	17	95ZZZX6239 	1	19951025	G	5412	5008906	BULKHEAD 			PIPER 	PA31T 	PA31T2 	7103127	SO 										LT ENG NACELLE	CRACKED 	B			VIB6	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	37SR	2741 				31T816051				LEFT ENGINE NACELLE INBOARD LONGITUDINAL BULKHEAD IS CRACKED AT INBOARD UPPER BIRDCAGE MOUNT. CRACK IS AT AFT RIVET HOL	E. CRACK WAS DISCOVERED DURING ROUTINE INSPECTION.					1	L	7	2 	3T			RT	A8EA 					 
1995021000228	19950210	00228	CE 	1995	2	10	95ZZZX624 	1	19950118	G	2435	03601015	BEARING 	LEARSIEGLER 	23080025 	BEECH 	MU300 	400BEECH 		CE 										START/GEN	FAULTY 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	46FE	164 			7839	RK0016				DURING 500-HOUR BRUSH INSPECTION, FOUND BOTH END BEARINGS WOULD NOT PASS INSPECTION. THESE ARE THE NEW 1,000-HOUR BEARI	NGS. TOTAL TIME ON THEM WAS 163.8 HOURS.					2	H	7	2 	4F			RT	A16SW 					 
1995111700621	19951117	00621	GL 	1995	11	17	95ZZZX6240 	2	19951016	G	7532	23053176	BLEED VALVE 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					COMPRESSOR	STICKS 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V		508 		FF32235	490487D	CAE830976			PILOT COMPLAINED THE POWER CHECK WAS INCONSISTENT. SUBSEQUENT INSPECTION REVEALED THE BLEED VALVE WAS STICKY. UNIT SEN	T IN FOR REPAIR ON ALLISON 250 REPORT NR A159719.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995111700622	19951117	00622	SW 	1995	11	17	95ZZZX6241 	1	19951017	G	6320	47620628003	BEARING 		4762060029 	BELL 	47 	47G5A 	1181034	SW 										TRANSMISSION	FAILED 	G		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	615BH	177 			BBU10013	25126				OPERATOR REPORTS 5 TRANSMISSION BEARING FAILURES WITHIN THE LAST YEAR. SUSPECT IMPROPERLY MANUFACTURED BEARINGS, AND, A	S A RESULT, IMPROPER INSTALLATION. AN ACCIDENT PREVENTION RECOMMENDATION WAS SUBMITTED TO AAI-200.					1	G	7	1 	3O				2H3 					 
1995111700623	19951117	00623	NE 	1995	11	17	95ZZZX6242 	2	19950918	G	7230	1100078004	IMPELLER 			BELL 	204 	UH1L 	118141G	SW 	LYC 	T53 	T5313B 	41549	NE 					COMPRESSOR	FAILED 	C		A	M5WL	A				UNSCHED LANDING 				T			ENGINE CASE PENETRATION 			NR	NOT REPORTED 	1			NM	07	70410	3158 	2548 		M346379	157855	LE18722B			DURING ENGINE OPERATION, CENTRIFUGAL COMPRESSOR IMPELLER FAILED CAUSING UNCONTAINED PARTS EXITING FROM ENGINE COMPRESSOR	 SPOOL CORE DURING FLIGHT. THIS UNCONTAINED FAILURE RESULTED IN POWERPLANT POWER SHUT DOWN WITH RESULTANT HARD LANDING 	OF AIRCRAFT. RECOMMEND THAT PART 91 RESTRICTED CATAGORY AIRCRAFT AND POWERPLANTS BE BOUND TO 'LIKE' CIVILIAN COUNTERPAR	T LIMITATIONS, I.E., OPERATE HOURS TO CYCLE LIMIT. BOUND TO MANUFACTURER'S CIVILIAN SERVICE BULLETINS IN ADDITION TO AI	RWORTHINESS DIRECTIVES.		1	G	7	1 	4U	4	U		EXPA1G71	E17EA				 
1995111700624	19951117	00624	SW 	1995	11	17	95ZZZX6243 	1	19950922	G	6310	289052017	SEAL 		2060402703 	BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20B 	03013	GL 					FREEWHEEL	LEAKING 	B		A	KUVR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	167BH	99 			BMB10321	1961	CAE831086			INSTALLED NEW SEAL AFTER INSPECTION OF UNIT. STARTED LEAKING OIL AFTER VERY LITTLE TIME IN SERVICE. SUBMITTER STATED B	ELL SEEMS TO HAVE CHANGED MANUFACTURERS. SEAL IS GARLOCK TYPE, BUT BLACK INSTEAD OF USUAL ORANGE COLOR. APPEARS TO BE 	OF DIFFERENT MATERIAL, HARDER THAN PREVIOUS STYLE.				1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995111700625	19951117	00625	SW 	1995	11	17	95ZZZX6244 	1	19950922	G	6520	206040103101	SEAL 		2060404009 	BELL 	206 	206B 	1181511	SW 										T/R GEARBOX	LEAKING 	B		A	KUVR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	167BH	294 			AL011082	1961				INSTALLED NEW SEAL AND WEAR SLEEVE FOR REPAIR LEAK AT INPUT SEAL. NEW SEAL IS LEAKING AGAIN AFTER VERY SHORT TIME IN SE	RVICE. A COMMON PROBLEM, BUT NOT SO SOON. INSPECTION INTERVAL FOR GEARBOX IS 3,000 HOURS. CHANGING SEAL 10 TIMES NOT 	DESIRABLE. SEAL IS OF NEW STYLE AND PART NUMBER. SUBMITTER STATED POSSIBLY A NEW MANUFACTURER. ADVISED BHT OF THIS PR	OBLEM.			1	G	7	1 	3U				H2SW 					 
1995111700626	19951117	00626	NE 	1995	11	17	95ZZZX6245 	2	19950731	G	7322	76081	DRIVE SHAFT 		106500A2 	KAMAN 	K1200 	K1200 	05625F6	SW 	LYC 	T53 	T5317A 	41549	NE 					FUEL CONTROL	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03			692 		9ADS1682					TA-7 FUEL CONTROL, TIP SEAL PUMP EQUIPPED, WAS FOUND TO HAVE WORN SPLINES. PUMP SECONDARY FUEL FLOW REDUCED TO ZERO PPH	. PRIMARY PUMP FLOW REMAINED FULLY FUNCTIONAL. DRIVE SHAFT AND MATING PUMP GEAR SET WERE REPLACED WHILE CONTROL WAS RE	TURNED REPAIRED.				1	G	7	1 	4F	4	U	NT	TR7BO 	E17EA				 
1995111700627	19951117	00627	EA 	1995	11	17	95ZZZX6246 	1	19951023	G	2750	60093000103	ASYMMETRY BRAKE 			CNDAIR	CL601 	CL6013A 	8070802	EA 										RT FLAP	FAILED 	C				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			EA	25	399SW		1 		10773	5009				FLAPS FAILED AT 18 DEGREES. REPLACED DEFECTIVE RT FLAP ASYMMETRY BRAKE. OPS CHECK NORMAL. COMPLIED IAW 27-50-26.						2	L	7	2 	4F			RT	A21EA 					 
1995111700628	19951117	00628	NE 	1995	11	17	95ZZZX6247 	2	19951023	G	7200		ENGINE 			CNDAIR	CL601 	CL6013A 	8070802	EA 	GE 	CF34 	CF343A 	30015	NE 					RT POSITION	VIBRATION 	C				O				OTHER 				E			VIBRATION/BUFFET 			TO	TAKEOFF 	1			EA	25	399SW	3482 	482 			5009	350246RH			NR 2 ENGINE ON TAKEOFF EXPERIENCED HIGH VIBRATION LIGHT AND READING OF 2.1. PERFORMED ENGINE RUN WITH ANTI-ICE SELECTED	 AND VIBES AT 1.8. PERFORMED BORESCOE OF RT ENGINE. NO ABNORMALTIES. NOTIFIED GE PER MM 72-00-00, PAGE 517, WITHIN OP	S LIMITS. AS PRECAUTIONARY, DELIVERED AIRCRAFT TO GE FOR INSPECTION. FOUND PARTIAL FLAKING OF COATING FROM COMB GEAR. 	 INSTALLED LOANER ENGINE. OPS NORMAL.			2	L	7	2 	4F	4	F	RT	A21EA 	E15NE				 
1995111700629	19951117	00629	EA 	1995	11	17	95ZZZX6248 	1	19951023	G	2752	6009300082	ACTUATOR 			CNDAIR	CL601 	CL6013A 	8070802	EA 										RT OTBD FLAP	FAILED 	C				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			EA	25	1812C	3740 			96439	5010				FLAPS FAILED AT 32 DEGREES. FOUND RT OUTBOARD FLAP INBOARD ACTUATOR AT FAULT. REPLACED ACTUATOR IAW MM 27-50-16 AND MM	 27-50-00. OPS CHECK NORMAL.					2	L	7	2 	4F			RT	A21EA 					 
1995111700630	19951117	00630	EU 	1995	11	17	95ZZZX6249 	1	19951016	G	5320	HC537H0651004	INTERCOSTAL 			BAG 	BAE146	BAE146200A 	1500266	EU 										LT FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND 2ND INTECOSTAL FROM OUTBOARD IN LT FORWARD VESTIBULE BETWEEN FRAMES 15 AND 18 CORROD	ED. ALSO, FOUND SUPPORT MEMBER ATTACHED TO INTERCOSTAL CORRODED. REPLACED INTERCOSTAL AND SUPPORT MEMBER. REFERENCE O	PERATOR CONTROL NR A6WR95024.				2	H	7	4 	4F			RT	A49EU 					 
1995021000229	19950210	00229	CE 	1995	2	10	95ZZZX625 	1	19950120	G	5610	99100499	WINDSHIELD 			CESSNA	425 	425 	2076018	CE 										PILOTS	SHATTERED 	B			EBVR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	09	404EW	4640 				4250099				AIRCRAFT ARRIVED 1-8-95 WITH PILOT'S WINDSHIELD SHATTERED. REMOVED WINDSHIELD AND REPLACED WITH NEW, SN 94199H9537. NE	W RETAINERS WERE FIT AND INSTALLED.					1	L	7	2 	3T			RT	A7CE 					 
1995111700631	19951117	00631	EU 	1995	11	17	95ZZZX6250 	1	19951012	G	5320	HC537H0655008	GUSSET 			BAG 	BAE146	BAE146200A 	1500266	EU 										FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND 2 GUSSET PLATES IN FORWARD VESTIBULE/LAVATORY AREA CORRODED. REPLACED GUSSET PLATES	 IAW BAE SRM.					2	H	7	4 	4F			RT	A49EU 					 
1995111700632	19951117	00632	EU 	1995	11	17	95ZZZX6251 	1	19951017	G	2711	HC270H0134016	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										LT AIL TRIM	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND LT AILERON TRIM CABLE CIRCUIT CABLES CORRODED. REPLACED CABLES.						2	H	7	4 	4F			RT	A49EU 					 
1995111700633	19951117	00633	EU 	1995	11	17	95ZZZX6252 	1	19951017	G	2730	HC270H0041040	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										LT ELEV CONTROL	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND LT ELEVATOR MAIN CONTROL CABLES CORRODED AFT OF REAR PRESSURE BULKHEAD. REPLACED CABLES. REFEREN	CE CONTROL NR A6WR95039.					2	H	7	4 	4F			RT	A49EU 					 
1995111700634	19951117	00634	EU 	1995	11	17	95ZZZX6253 	1	19951017	G	2730	HC270H0041028	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										RT ELEV CONTROL	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND RT ELEVATOR MAIN CONTROL CABLES CORRODED AFT OF REAR PRESSURE BULKHEAD. REPLACED CABLES. REFEREN	CE CONTROL NR A6WR95038.					2	H	7	4 	4F			RT	A49EU 					 
1995111700635	19951117	00635	EU 	1995	11	17	95ZZZX6254 	1	19951017	G	2720	HC270H0041054	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										RUDDER CONTROL	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND MAIN RUDDER CONTROL CABLES CORRODED AFT OF REAR PRESSURE BULKHEAD. REPLACED CABLES. REFERENCE OP	ERATOR CONTROL NR A6WR95037.					2	H	7	4 	4F			RT	A49EU 					 
1995111700636	19951117	00636	EU 	1995	11	17	95ZZZX6255 	1	19951017	G	2897	HC760H0003038	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 2	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 2 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT AT CENTER AREA OF LT WING CORRODED. REPLACED CAB	LES. REFERENCE CONTROL NR A6WR95036, NR 95ZZZX6256, AND NR 95ZZZX6257.					2	H	7	4 	4F			RT	A49EU 					 
1995111700637	19951117	00637	EU 	1995	11	17	95ZZZX6256 	1	19951017	G	2897	HC760H0003140	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 2	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 2 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT AT CENTER AREA OF LT WING CORRODED. REPLACED CAB	LES. REFERENCE CONTROL NR A6WR95036, NR 95ZZZX6255, AND NR 95ZZZX6257.					2	H	7	4 	4F			RT	A49EU 					 
1995111700638	19951117	00638	EU 	1995	11	17	95ZZZX6257 	1	19951017	G	2897	HC760H0003136	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 2	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 2 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT AT CENTER AREA OF LT WING CORRODED. REPLACED CAB	LES. REFERENCE CONTROL NR A6WR95036, NR 95ZZZX6255, AND NR 95ZZZX6256.					2	H	7	4 	4F			RT	A49EU 					 
1995111700639	19951117	00639	EU 	1995	11	17	95ZZZX6258 	1	19951017	G	2897	HC760H000C032	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 1	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 1 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. ALL FOUR CABLES FROM FUSELAGE FRAME 18	 TO L.P. COCK. REPLACED CABLES. REFERENCE OPERATOR CONTROL NR A6WR95035, NR 95ZZZX6259, AND NR 95ZZZX6260.					2	H	7	4 	4F			RT	A49EU 					 
1995111700640	19951117	00640	EU 	1995	11	17	95ZZZX6259 	1	19951017	G	2897	HC760H0003142	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 1	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 1 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. ALL FOUR CABLES FROM FUSELAGE FRAME 18	 TO L.P. COCK. REPLACED CABLES. REFERENCE OPERATOR CONTROL NR A6WR95035, NR 95ZZZX6258, AND NR 95ZZZX6260.					2	H	7	4 	4F			RT	A49EU 					 
1995111700641	19951117	00641	EU 	1995	11	17	95ZZZX6260 	1	19951017	G	2897	HC760H0003144	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 1	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 1 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. ALL FOUR CABLES FROM FUSELAGE FRAME 18	 TO L.P. COCK. REPLACED CABLES. REFERENCE OPERATOR CONTROL NR A6WR95035, NR 95ZZZX6258, AND NR 95ZZZX6259.					2	H	7	4 	4F			RT	A49EU 					 
1995111700642	19951117	00642	EU 	1995	11	17	95ZZZX6261 	1	19951017	G	2721	HC70H0042044	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										RUDDER TRIM	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND RUDDER TRIM CABLES AT CENTER WING ROOT AREA CORRODED. REPLACED CABLES. REFERENCE OPERATOR CONTRO	L NR A6WR95034.					2	H	7	4 	4F			RT	A49EU 					 
1995111700643	19951117	00643	EU 	1995	11	17	95ZZZX6262 	1	19951017	G	2711	HC270H0134010	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										RT AIL TRIM	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND RT AILERON TRIM CABLES CORRODED AT CENTER WING ROOT AREA. REPLACED CABLES. REFERENCE CONTROL NR 	A6WR95033.					2	H	7	4 	4F			RT	A49EU 					 
1995111700644	19951117	00644	EU 	1995	11	17	95ZZZX6263 	1	19951017	G	2897	HC760H0003010	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 3	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 3 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. FOUR CABLES FROM FUSELAGE FRAME 18 TO 	L.P. COCK. REPLACED CABLES. REFERENCE CONTROL A6WR95040, NR 95ZZZX6264, AND NR 95ZZZX6265.					2	H	7	4 	4F			RT	A49EU 					 
1995111700645	19951117	00645	EU 	1995	11	17	95ZZZX6264 	1	19951017	G	2897	HC760H0003132	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 3	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 3 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. FOUR CABLES FROM FUSELAGE FRAME 18 TO 	L.P. COCK. REPLACED CABLES. REFERENCE CONTROL A6WR95040, NR 95ZZZX6263, AND NR 95ZZZX6265.					2	H	7	4 	4F			RT	A49EU 					 
1995111700646	19951117	00646	EU 	1995	11	17	95ZZZX6265 	1	19951017	G	2897	HC760H0003130	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 3	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 3 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. FOUR CABLES FROM FUSELAGE FRAME 18 TO 	L.P. COCK. REPLACED CABLES. REFERENCE CONTROL A6WR95040, NR 95ZZZX6263, AND NR 95ZZZX6264.					2	H	7	4 	4F			RT	A49EU 					 
1995111700647	19951117	00647	EU 	1995	11	17	95ZZZX6266 	1	19951017	G	2897	HC760H0003012	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 4	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 4 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. FOUR CABLES FROM FUSELAGE FRAME 18 TO 	L.P. COCK. REPLACED CABLES. REFERENCE CONTROL A6WR95046, NR 95ZZZX6267, AND NR 95ZZZX6268.					2	H	7	4 	4F			RT	A49EU 					 
1995111700648	19951117	00648	EU 	1995	11	17	95ZZZX6267 	1	19951017	G	2897	HC760H0003134	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 4	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 4 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. FOUR CABLES FROM FUSELAGE FRAME 18 TO 	L.P. COCK. REPLACED CABLES. REFERENCE CONTROL A6WR95046, NR 95ZZZX6266, AND NR 95ZZZX6268.					2	H	7	4 	4F			RT	A49EU 					 
1995111700649	19951117	00649	EU 	1995	11	17	95ZZZX6268 	1	19951017	G	2897	HC760H0003136	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 4	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 4 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. FOUR CABLES FROM FUSELAGE FRAME 18 TO 	L.P. COCK. REPLACED CABLES. REFERENCE CONTROL A6WR95046, NR 95ZZZX6266, AND NR 95ZZZX6267.					2	H	7	4 	4F			RT	A49EU 					 
1995111700650	19951117	00650	EU 	1995	11	17	95ZZZX6269 	1	19951017	G	2731	HC270H0042008	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										ELEVATOR TRIM	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND ELEVATOR TRIM CABLE CIRCUIT IN CENTER WING AREA CORRODED. REPLACED CABLES. REFERENCE OPERATOR CO	NTROL NR A6WR95047.					2	H	7	4 	4F			RT	A49EU 					 
1995021000231	19950210	00231	CE 	1995	2	10	95ZZZX627 	1	19950123	G	2750	45AS6101513	SWITCH 		45A610062 	BEECH 	MU300 	400BEECH 		CE 										RT FLAP	MALFUNCTIONED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	553PF	783 			30K38	RK32				FLAP CONTRTOL INTERMITTENT. SOMETIMES WILL GO DOWN PAST SELECTED AND NOT MOVE AGAIN. SPOKE TO REP AT BEECHCRAFT WHO SU	SPECTED A COLD SOAK PROBLEM IN THE RT FLAP FOLLOW-UP SWITCH. FOLLOWED ADVISE AND PLACED RT FLAP FOLLOW-UP SWITCH IN FRE	EZER. REMOVED FROM FREEZER AND QUICKLY REINSTALLED. FLAPS STUCK AT 12 DEGREES WHILE SELECTING 30 DEGREES DOWN. FLAPS 	WOULD NOT MOVE. AFTER 4 MINUTES OF REPOSITIONING FLAP LEVER, RESET THE AIRCRAFT MASTER SWITCH. FLAPS WERE NOW OPERATIO	NAL.		2	H	7	2 	4F			RT	A16SW 					 
1995112400032	19951124	00032	NM 	1995	11	24	95ZZZX6270 	1	19950911	G	5400	6553553152	FAIRING 		6585378388 	BOEING	737 	737247 	138448D	NM 										UPPER NOSE COWL	WORN 	B			IX3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	302VA				0302	20126				MAINTENANCE REPORT, NR 2 ENGINE NOSE COWL WORN 50 PERCENT OF DEPTH IN .040 INCH 2024T3 SKIN UNDER MATING SURFACE OF FORW	ARD WING TO NACELLE FAIRING. FABRICATED DOUBLER .040 INCH 2024T3, 2 FASTENER ROWS WIDER THAN EXISTING DAMAGE AND REPAIR	ED PER SHIVA ENT., INC., E.O. 354E004 AND APPROVED FAA FORM 8110-3, REPORT 95-9, DATED SEPTEMBER 14, 1995. A/C TOTAL TI	ME, 51,945.9 HOURS. TOTAL CYCLES, 60,051.			2	L	7	2 	4F				A16WE 					 
1995112400033	19951124	00033	NM 	1995	11	24	95ZZZX6271 	1	19950911	G	5246		SKIN 			BOEING	737 	737247 	138448D	NM 										FWD LAV SRV PNL	CORRODED 	B			IX3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	309VA	58387				19614				MAINTENANCE REPORT OF CORROSION AT FORWARD LAV SERVICE PANEL SKIN AND REINFORCING DOUBLER, STA 257 TO STA 277, BETWEEN S	TR 23R AND STR 24R. AFTER CORROSION REMOVAL, FOUND REMAINING SKIN TO BE WITHIN LIMITS IAW 737 SRM 53-30-1. FABBED SKIN	 AND REINFORCING DOUBLER IAW 737 SRM 51-10-1 AND SRM 53-30-3, AND REPAIRED SAME IAW SHIVA ENT. ENGINEERING ORDER 353E021	, REPORT 95-8, DATED SEPTEMBER 14, 1995, ON FORM (FAA) 8110-3. A/C TOTAL TIME 58,386.8 HOURS. TOTAL CYCLES, 65,586.			2	L	7	2 	4F				A16WE 					 
1995021000234	19950210	00234	NE 	1995	2	10	95ZZZX628 	3	19950110	G	6111	7863504	BLADE 		SK112331 											HAMSTD	5500	65500F1 	NE 	BUTT AREA	SCORED 	B			H2SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		3200 	802 		863620					SUBJECT BLADE WAS RECEIVED WITH SCORING DAMAGE AROUND THE OUTSIDE DIAMETER OF THE BLADE BUTT AREA. DAMAGE IS LOCATED 36	0 DEGREES AROUND THE BUTT, AND IS APPROXIMATELY .020 INCH DEEP BY .300 INCH HIGH. THE DAMAGE APPEARS TO POSSIBLY HAVE B	EEN CAUSED BY RESIDUAL PEENING SHOT BALLS INSIDE THE HUB.														6	C	P13NE	 
1995021000235	19950210	00235	NE 	1995	2	10	95ZZZX629 	3	19950110	G	6111	7863504	BLADE 													HAMSTD	5500	65500F1 	NE 	BUTT AREA	SCORED 	B			H2SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		4334 	1177 		863261					SUB JECT BLADE WAS RECEIVED WITH SCORING DAMAGE AROUND THE OUTSIDE DIAMETER OF THE BLADE BUTT AREA. DAMAGE IS INTERSPER	SED 360 DEGREES AROUND THE BUTT, AND IS APPROXIMATELY .010 INCH DEEP BY .200 INCH HIGH. THE DAMAGE APPEARS TO POSSIBLY 	HAVE BEEN CAUSED BY RESIDUAL PEENING SHOT BALLS INSIDE THE HUB.														6	C	P13NE	 
1995112400243	19951124	00243	GL 	1995	11	24	95ZZZX6299 	1	19951008	G	3213	GM1	GEAR WELDMENT 			AMTR 	LANCAR	LANCAIR 	05616TS	GL 										RT MLG	BENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	164Q	50 				341349				FOUND RT MLG WELDMENT BENT 2 INCHES FORWARD OF REAR TRUNNION. SUBMITTER STATES BEND IS RESULT OF HARD LANDING. LANDING	S, 65.					1	L	7	1 	3O			RT	EXPA1L71					 
1995021000236	19950210	00236		1995	2	10	95ZZZX630 	1	19950104	G	6120	7757101	TRANSFER TUBE 	HAMSTD 	78249024 											HAMSTD	14RF	14RF9 	NE 	PROP CONTROL	BLOCKED 	B			H2SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		4136 	146 		900529					THE PROP CONTROL WAS RETURNED FOR INABILITY TO COMMAND THE PROPELLER TO FEATHER. UPON DISASSEMBLY, A SMALL ROUND METAL 	PLATE WAS FOUND TO BE PARTIALLY BLOCKING AN OIL TRANSFER TUBE. THE ROUND PLATE WAS SUBSEQUENTLY DETERMINED TO BE PART O	F THE INLET TRANSFER FILTER. LIGHT SURFACE DAMAGE WAS NOTED ON THE OIL TRANSFER TUBE AND PCU HOUSING.														6	C	P11NE	 
1995112400244	19951124	00244	GL 	1995	11	24	95ZZZX6300 	1	19951026	G	3260	91MPM6L	CONNECTOR 			BLANCA	17 	1730A 	1220433	GL 										GEAR WARNING	SHORTED 	D				K				NONE 				N			FALSE WARNING 			NR	NOT REPORTED 	1			SO	09	286SV	58 				95301022				LANDING GEAR MOTOR AND WARNING LIGHT WOULD NOT GO OFF IN THE DOWN MODE, BUT DID HAVE THREE GREEN DOWN LIGHTS. FOUND AMP	HENOL CONNECTOR WHICH CONTAINS LIGHT DIODES SHORTED WITH METAL SHAVINGS.					1	L	7	1 	3O				A18CE 					 
1995112400246	19951124	00246	EA 	1995	11	24	95ZZZX6302 	2	19951017	G	8530	SL73806	PUSHROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					NR 1 CYL INTAKE	LOOSE 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	6449M	1112 				15284733	L217711			DURING ROUTINE INSPECTION, A VALVE GUIDE CLEARANCE CHECK WAS DONE. THE NR 1 CYLINDER INTAKE PUSHROD WAS FOUND TO HAVE T	HE STEM LOOSE. IT COULD EASILY BE REMOVED BY HAND. THIS PART IS NORMALLY A PRESS-FIT AND IS NOT REMOVABLE. REPLACED W	ITH NEW.				1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995112400247	19951124	00247	SO 	1995	11	24	95ZZZX6303 	2	19950925	G	8540	643259A2	ADAPTER ASSY 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520N 	17032	SO 					STARTER	FAILED 	B			PAIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	2683Y		506 			421C1218	277061R			THE OPERATOR INCURRED A STARTER ADAPTER FAILURE THAT CONTAMINATED THE ENGINE. DISASSEMBLY OF THE ENGINE REVEALED THAT B	EARING, PN 537721, HAD FAILED FIRST CAUSING THE STARTER ADAPTER TO BIND AS IT ROTATED WHICH CAUSED IT TO FAIL. THE ADAP	TER HAD BEEN REMOVED AND REINSTALLED PRIOR TO THIS FAILURE TO C/W SB. DURING INSTALLATION OF THE STARTER ADAPTER, THE B	EARING WAS PROBABLY DAMAGED CAUSING THE CHAIN OF EVENTS TO OCCUR.			1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995112400248	19951124	00248	CE 	1995	11	24	95ZZZX6304 	1	19951027	G	2751	58364027601	PC BOARD 			BEECH 	58 	58 	1152740	CE 										FLAP POSITION	SHORTED 	B			WC7R	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			GL	25	858LG					TH518				FLAP POSITION INDICATION PC BOARD CAPACITOR SHORTED CAUSING GLOW IN PEDESTAL. REMOVED AND REPLACED PC BOARD AND INDICAT	OR. OPS CHECKS GOOD.					1	L	7	2 	3O				3A16 					 
1995112400249	19951124	00249	CE 	1995	11	24	95ZZZX6305 	1	19951031	G	2751	58364027601	PC BOARD 			BEECH 	58 	58 	1152740	CE 										FLAP POSITION	BURNED 	B			WC7R	K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			GL	25	858LG					TH518				PILOT REPORTED A RED GLOW AND BURNING SMELL BEHIND THROTTLE QUADRANT. FOUND CIRCUIT BOARD FOR FLAP POSITION INDICATOR B	URNED. CIRCUIT BOARD IS MOUNTED TO AN ALUMINUM RAIL BEHIND THROTTLE QUADRANT. RESISTOR ON CIRCUIT BOARD WAS CHARRED. S	USPECT FAILURE OF RESISTOR. NO OTHER DAMAGE OR DEFECTS NOTED. INSTALLED NEW CIRCUIT BOARD AND FLAP POSITION INDICATOR.	 OPERATIONAL CHECK GOOD.			1	L	7	2 	3O				3A16 					 
1995112400250	19951124	00250	CE 	1995	11	24	95ZZZX6306 	1	19951001	G	2820	601601612	CHECK VALVE 			LEAR 	60 	60LEAR 	5170707	CE 										AFT FUEL CELL	DISCONNECTED 	B		A	TR1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4031A	51 				033				THE CHECK VALVES IN THE MAIN BODY AFT FUEL CELL WERE FOUND DISCONNECTED AND HANGING ON THEIR BONDING WIRES. TWO OF THE 	FOUR AND ONE WAS ALMOST READY TO FALL DOWN ALSO. ONLY ONE OF THE FOUR WAS STILL AIRWORTHY. SUBMITTER SUGGESTS A REDESI	GN OF THE MOUNTING OF THESE VALVES SEEMS TO BE INDICATED.				2	L	7	2 	4F			RT	A10CE 					 
1995112400251	19951124	00251	SW 	1995	11	24	95ZZZX6307 	1	19951025	G	3260	65930087	SWITCH 			GULSTM	560 	560 	0141402	SW 										NLG UPLOCK	FAILED 	B	L		AC1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	70TG	2235 				560069				WHILE PERFORMING A GEAR RETRACTION CHECK PER A PHASE 2 INSPECTION, THE FOLLOWING PROBLEM WAS NOTED. UPON SELECTION OF G	EAR UP, MAIN GEAR WENT UP AND LOCKED, BUT NOSE GEAR DID NOT. NOSE GEAR DID COME OFF OF DOWNLOCK, BUT WHEN MAINS WENT UP	 AND LOCKED, NOSE GEAR STOPPED WHERE IT WAS. APPARENTLY, THE CONTROL CIRCUIT CONTACTS SHUT OFF BECAUSE THE NOSE UPLOCK 	SWITCH WAS ALREADY INDICATING UP AND LOCKED EVEN THOUGH NOSE GEAR WAS NOT UP AND LOCKED. A NEW SWITCH WAS INSTALLED AND	 THE SYSTEM WORKED NORMALLY.		1	H	7	2 	3O				6A1 					 
1995112400252	19951124	00252		1995	11	24	95ZZZX6308 	4	19950327	G	2565	D30546101	SLIDE 			AIRBUS	310 	A310324 	3930206	EU 										NR 1 LT DOOR	MALFUNCTION 	B			XBUZ	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	33	813PA				123	449				DURING SLIDE SAMPLING OPERATION IAW ITEM 256120-06-1 ON NR 1 LEFT DOOR, NORMAL OPERATION FOR DOOR DAMPER, PN 70S5097000,	 PRESSURE 1,750 PSI (14 DEGREES CELSIUS), THE DOOR FAILED, STICKING IN MIDDLE OPENING POSITION WITH SLIDE INFLATION. AF	TER 10 SECONDS, THE BLOCKING BETWEEN DOOR THRESHOLD, SLIDE AND SLIDE COVER GOT FREE DUE TO SLIDE DEPLOYMENT. NORMAL SLI	DE OPERATION AFTER. OPERATOR CONTROL NR 95/0BAH5/3.			2	L	7	2 	4F			RT	A35EU 					 
1995112400253	19951124	00253		1995	11	24	95ZZZX6309 	4	19950411	G	2565	D30540101	SLIDE 			AIRBUS	310 	A310324 	3930206	EU 										NR 1 RT DOOR	MALFUNCTIONED 	B			XBUZ	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	33	811PA				0379	439				DURING ESCAPE SLIDE OPENING OPERATION IAW ITEM 256120.06.1, NORMAL SEQUENCE, BUT TOTAL DEPLOYEMENT TOO LONG. FOUND CENT	RAL SCRATCH TWISTED WITH THE SLIDE. OPERATOR CONTROL NR 95/0BAH6/1.					2	L	7	2 	4F			RT	A35EU 					 
1995021000237	19950210	00237	SO 	1995	2	10	95ZZZX631 	1	19950113	G	7810	6879300	STACK 			PIPER 	PA32 	PA32300 	7103212	SO 										RT EXHAUST	CRACKED 	B			MJ7R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	6868D					3240608				PILOT REPORTED A HOLE BURNED IN RIGHT SIDE OF THE LOWER ENGINE COWL. UPON FURTHER INVESTIGATION, FOUND RIGHT SIDE EXHAU	ST STACK HAD A 1 INCH BY 1.50 INCH HOLE IN IT WITH A CRACK EXTENDING FROM THE HOLE. THE CRACK EXTENDED APPROXIMATELY HA	LF OF THE CIRCUMFERENCE OF THE STACK. THE HOLE WAS ON THE OUTSIDE PORTION OF THE STACK AT THE POINT WHERE IT BENDS TOWA	RDS THE MUFFLER.			1	L	7	1 	3O				A3SO 					 
1995112400254	19951124	00254		1995	11	24	95ZZZX6310 	4	19950327	G	2565	D30546101	SLIDE 			AIRBUS	310 	A310324 	3930206	EU 										NR 1 RT DOOR	MALFUNCTIONED 	B			XBUZ	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	33	813PA				0091	449				DURING SLIDE SAMPLING OPERATION IAW ITEM 256120-06-1, ON NR 1 RIGHT DOOR, NORMAL OPERATION FOR DAMPER, PN 7010597000, PR	ESSURE 1,750 PSI (14 DEGREES CELSIUS), THE DOOR FAILED, STICKING IN MIDDLE OPENING POSITION WITH SLIDE INFLATION. THE G	IRT BAR WAS IN NORMAL LOCKED POSITION ON THE DOOR THRESHOLD. OPERATOR CONTROL NR 95/0BAH5/2.				2	L	7	2 	4F			RT	A35EU 					 
1995112400255	19951124	00255	EU 	1995	11	24	95ZZZX6311 	1	19950411	G	2560	A5211060100400	GIRT BAR 			AIRBUS	310 	A310324 	3930206	EU 										NR 3 LT DOOR	BROKEN 	B			XBUZ	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	33	811PA					639				DURING ESCAPE OPENING OPERATION IAW ITEM 256120.06.1, FOUND NORMAL FUNCTION OF DOOR DAMPER, BUT AFTER DOOR OPENING, THE 	ESCAPE SLIDE FALLS DOWN, NO INFLATION, NO DEPLOYMENT. AFTER CHECK, FOUND SPRING GIRT BAR BROKEN. IPC 52.11.11, PAGE 23	, FIGURE 23, REP 207. OPERATOR CONTROL NR 95/0BAH6/3.				2	L	7	2 	4F			RT	A35EU 					 
1995112400256	19951124	00256		1995	11	24	95ZZZX6312 	4	19950411	G	2565	D31022102	SLIDE 			AIRBUS	310 	A310324 	3930206	EU 										NR 2 RT DOOR	MALFUNCTIONED 	B			XBUZ	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	33	811PA				0074	439				DURING ESCAPE SLIDE OPENING OPERATION IAW ITEM 256120.06.1, FOUND NORMAL INFLATION UNTIL DOOR REACHES THE WING. FOUND Q	UICK DISCONNECT AIR BOTTLE WAS NOT FITTED TO THE SLIDE PIPE. PRESSURE GOES OUT, NO DEPLOYMENT. OPERATOR CONTROL NR 95/	0BAH6/2.				2	L	7	2 	4F			RT	A35EU 					 
1995112400257	19951124	00257	EU 	1995	11	24	95ZZZX6313 	1	19950327	G	5210	7015097000	DOOR 			AIRBUS	310 	A310324 	3930206	EU 										NR 3 LT DOOR	DAMPER FAILED 	B			XBUZ	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	33	813PA				2057	449				DURING SLIDE SAMPLING OPERATION IAW ITEM 256120.06.1, ON NR 3 LEFT DOOR, THE DOOR DAMPER WITH NORMAL PRESSURE OF 1,750 P	SI (14 DEGREES CELSIUS) DID NOT OPERATE DURING DOOR OPENING. THE INFLATION APPEARED DURING DOOR MOVEMENT TO CLOSE POSIT	ION. OPERATOR CONTROL NR 95/0BAH5/1.				2	L	7	2 	4F			RT	A35EU 					 
1995112400258	19951124	00258	NE 	1995	11	24	95ZZZX6314 	2	19951017	G	7250	3032649	BEARING 			BEECH 	1900 	1900D 	1154162	CE 	PWA 	PT6 	PT6A67D 		NE 					NR 6	FAILED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	17YV	6843 			84C421	UE17	114026			NR 6 BEARING IN THE POWER SECTION FAILED. THE INVESTIGATION IS LOOKING AT ELECTRICAL DISCHARGE AS THE SUSPECTED CAUSE O	F THE M.I.O. NR 6 BEARING HAS BEEN SENT TO PW & C FOR INVESTIGATION.					2	L	7	2 	4T	4	T	RT	A24CE 	E26NE				 
1995112400259	19951124	00259	NE 	1995	11	24	95ZZZX6315 	2	19951003	G	7250	310835601	SUN GEAR 			BEECH 	1900 	1900D 	1154162	CE 	PWA 	PT6 	PT6A67D 		NE 					POWER SECTION	FAILED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	23YV	76335			21C610	UE23	11407			POWER SECTION FAILURE WAS CAUSED BY THE SUN GEAR FAILURE. THE SUN GEAR, CARRIER, CARRIER GEARS, PT SHAFT, AND THE RING 	GEAR WERE SENT TO PW & C FOR INVESTIGATION.					2	L	7	2 	4T	4	T	RT	A24CE 	E26NE				 
1995112400260	19951124	00260	SW 	1995	11	24	95ZZZX6316 	1	19951030	G	2720	500012251	CONTROL CABLE 			GULSTM	690TP 	690B 	7630516	SW 										AFT RUDDER LT-RT	FRAYED 	B		A	FB2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	45AZ					11383				DURING C/W TWIN COMMANDER SB NR 195B, FOUND BOTH AFT RUDDER CABLES TO HAVE NUMEROUS CABLE STRANDS BROKEN. THE INSTRUCTI	ONS IN THE SB DO NOT ADDRESS THE REMOVAL OR INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14	. THE SB PROCEDURE IS THE ONLY WAY TO PROPERLY INSPECT THESE CABLES. HAVE FOUND MANY AIRCRAFT WITH CABLE STRANDS BROKE	N BEYOND THE LIMITS IN THE SB WHILE INSPECTING THE CABLES IN THIS MANNER. SUBMITTER SUGGESTS OWNERS C/W SI-199, WHICH I	NSTALLS LARGER PULLEYS AT THIS LOCATION.		1	H	7	2 	3T			 	2A4 					 
1995112400261	19951124	00261	SW 	1995	11	24	95ZZZX6317 	1	19951030	G	2720	500012253	CONTROL CABLE 			GULSTM	690TP 	690B 	7630516	SW 										AFT RUDDER LT-RT	FRAYED 	B			FB2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	45AZ					11383				DURING C/W TWIN COMMANDER SB NR 195B, FOUND BOTH AFT RUDDER CABLES TO HAVE NUMEROUS CABLE STRANDS BROKEN. THE INSTRUCTI	ONS IN THE SB DO NOT ADDRESS THE REMOVAL OR INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14	. THE SB PROCEDURE IS THE ONLY WAY TO PROPERLY INSPECT THESE CABLES. HAVE FOUND MANY AIRCRAFT WITH CABLE STRANDS BROKE	N BEYOND THE LIMITS IN THE SB WHILE INSPECTING THE CABLES IN THIS MANNER. SUBMITTER SUGGESTS OWNERS C/W SI-199, WHICH I	NSTALLS LARGER PULLEYS AT THIS LOCATION.		1	H	7	2 	3T			 	2A4 					 
1995112400262	19951124	00262	NE 	1995	11	24	95ZZZX6318 	2	19951027	G	7210	7757591	BEARING 	HAMSTD 	GC49 	SAAB 	SF340 	340B 	7860101	EU 	GE 	CT7TP 	CT79B 	30030	NE 					PROP SHAFT	SPALLED 	B			SI3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	587MA	11298	371 		9129	340B166				GEAR CASE RETURNED FROM FIELD DUE TO 'MAKING METAL'. DISASSEMBLY REVEALED THE BALL BEARING, PN 775759-1, ON THE MAIN PRO	PELLER SHAFT HAD FAILED. REFERENCE CMM 72-11-02.					2	L	7	2 	4T	4	T	RT	A52EU 	E8NE				 
1995112400263	19951124	00263	NE 	1995	11	24	95ZZZX6319 	2	19951027	G	7210	7895781	TAB WASHER 	HAMSTD 	GC49 	SAAB 	SF340 	SF340A 	7850100	EU 	GE 	CT7TP 	CT79B 	30030	NE 					GEAR CASE	FAILED 	B			SI3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03		7552 	6747 		UDA60542		GEE785360			GEAR CASE WAS RECEIVED DUE TO IDLER GEAR SHIFTED FORWARD WHICH RESULTED IN WEARING A HOLE THROUGH THE FORWARD GEAR CASE 	HOUSING. DISASSEMBLY REVEALED THE RIGHT IDLER GEAR NUT, PN 775770-1, HAD COME OFF THE RT IDLER GEAR, PN 775754-5. THE 	TABS ON THE TAB WASHER HAD FAILED ALLOWING THE NUT TO COME OFF THE IDLER GEAR. REFERENCE CMM 72-11-02.				2	L	7	2 	4T	4	T	RT	A52EU 	E8NE				 
1995021000238	19950210	00238	SO 	1995	2	10	95ZZZX632 	1	19950124	G	3201	63370004	BRACKET 			PIPER 	PA28 	PA28140 	7102802	SO 										RT MLG FAIRING	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	506FL	3647 				287125327				DURING AN INSPECTION, FOUND RT MLG FAIRING BRACKET CRACKED. THE FAIRING BRACKET HAD A CRACK .75 INCH LONG ABOVE THE AXL	E BOLT HOLE.					1	L	7	1 	3O				2A13 					 
1995112400264	19951124	00264	EU 	1995	11	24	95ZZZX6320 	1	19951011	G	3610	DE25413	CLAMP 			BAC 	111 	111419EP 	1480280	EU 										NR 1 STUB WING	FAILED 	B			AMCR	K				NONE 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			GL	09	524AC	8533 				BAC120				THE CREW EXPERIENCED A NR 1 STUB DUCT OVERHEAT WITH SUBSEQUENT PACK TRIP. INSPECTION REVEALED THE CLAMP BETWEEN THE ISO	LATION VALVE AND THE PRESSURE REDUCING VALVE HAD FAILED. THE STUD ON ONE SIDE OF THE CLAMP BROKE AND THE CLAMP CAME LOO	SE. THIS CLAMP IS BELIEVED TO BE ORIGINAL WHICH WOULD DATE IT ALMOST 30 YEARS OLD. THIS CLAMP HAS BEEN REMOVED AND INS	TALLED MANY TIMES OVER THE YEARS AND FAILED DUE TO FATIGUE. THE NEWER REPLACEMENT CLAMPS, PN DE25479, HAVE A LARGER STU	D. SUBMITTER RECOMMENDS DISCARDING THE OLDER STYLE CLAMPS WHEN REMOVED AND AUTOMATICALLY UPGRADING TO THE BETTER CLAMP.		2	L	7	2 	4F				A5EU 					 
1995112400265	19951124	00265	NM 	1995	11	24	95ZZZX6321 	1	19951002	G	5313		STRINGER 			BOEING	737 	737291 	138448W	NM 										FS 500 STR 19L	CRACKED 	B			S5WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	7376F					20364				FUSELAGE STRINGER CRACKED AT STA 500, STR 19L. DETECTED DURING ROUTINE C-CHECK INSPECTION. SUSPECT CAUSE BY STRESS LOA	DS FROM BAGGAGE LOADING. ROUTINE MAINTENANCE INSPECTIONS SHOULD DETECT ANY FURTHER DAMAGE. CONTROL NR 9519RI625.					2	L	7	2 	4F				A16WE 					 
1995112400266	19951124	00266	SW 	1995	11	24	95ZZZX6322 	1	19951030	G	6320	476209617	SPIDER SET 		4762060029 	BELL 	47 	47G5A 	1181034	SW 										TRANSMISSION	MISMANUFACTURED 	B			OUGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	17	4348P					25059				RECEIVED SPIDER GEAR SET AS NEW REPLACEMENT PART FROM BELL. DURING RECEIVING INSPECTION, NOTED PINION PIN HOLE FINISH V	ERY ROUGH AND CHAMFER ROUGH AND ECCENTRIC. ALSO, TOO DEEP IN SPOTS. RETURNED TO BELL FOR REPLACEMENT.					1	G	7	1 	3O				2H3 					 
1995112400267	19951124	00267	GL 	1995	11	24	95ZZZX6323 	2	19951103	G	7230	6877410	CASE HALF 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					COMPRESSOR	CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V		559 		13287	490487D	CAE830976			INSPECTED CASE HALVES AT ANNUAL, FOUND PLASTIC CRACKED BEYOND LIMITS WITH SOME MATERIAL MISSING.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995112400268	19951124	00268	SW 	1995	11	24	95ZZZX6324 	1	19950922	G	2430	2050756421	RELAY 			BELL 	206 	206B 	1181511	SW 										REVERSE CURRENT	FAILED 	B			DFUR	O				OTHER 				B	H		SMOKE/FUMES/ODORS/SPARKS 	ELECT. POWER LOSS-50 PC 		AP	APPROACH 	1			SO	09	6777	72 			CL44478	5206				ON SHORT FINAL, MAIN GENERATOR WENT OFF-LINE. PILOT IN AFT SEAT COULD SMELL BURNING ELECTRICAL WIRING. GROUND TEST REV	EALED REVERSE CURRENT RELAY WAS DEFECTIVE.					1	G	7	1 	3U				H2SW 					 
1995112400269	19951124	00269	GL 	1995	11	24	95ZZZX6325 	2	19951024	G	7200		ENGINE 			BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20J 	03013	GL 					POWER SECTION	MAKING METAL 	B			DFUR	A				UNSCHED LANDING 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SO	09	67773	72 				5205	CAE272716			PILOT REPORTED ENGINE CHIP LIGHT. PRECAUTIONARY LANDING COMPLETED OK. EVALUATION OF ENGINE REVEALED EXCESSIVE METAL IN	 SCREEN AND CHIP PLUG.					1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995112400270	19951124	00270	WP 	1995	11	24	95ZZZX6326 	1	19951031	G	6320	269A5104	GEAR TOOTH 			HUGHES	269 	269C 	4470504	WP 										M/R XMSN	TOOTH FAILED 	B			FW7R	A				UNSCHED LANDING 				J			WARNING INDICATION 			CL	CLIMB 	1			EA	07	6129Q	1900 			S0445	S1629				THE ACFT RETURNED SHORTLY AFTER TAKEOFF WITH THE PILOT REPORTING NO TRANSMISSION OIL PRESSURE OR ROTOR TACH READING. FA	ILURE OF THE XMSN OIL PUMP WAS SUSPECTED. UPON REMOVAL OF THE PUMP, A CHUNK OF A TOOTH FROM THE RING GEAR ASSY WAS FOUN	D IN THE XMSN SUMP. THE XMSN WAS SENT BACK TO THE MFG FOR REPAIR. THE MFG INFORMED CUSTOMER THEY WERE AWARE OF THIS PR	OBLEM OCCURRING WITH THESE RING GEARS.			1	G	7	1 	3O				4H12 					 
1995112400289	19951124	00289	GL 	1995	11	24	95ZZZX6327 	3	19951101	G	6111	S90AT8	BLADE 			CESSNA	182 	182 	2072702	CE 						MCAULY	2A34C	2A34C66 	GL 	THREADS	CORRODED 	B			WN1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	19					C99656YS			720757		FOUND SEVERE CORROSION IN BLADE THREADS. SUBMITTER RECOMMENDS ALL PART 91 OPERATORS HAVE MANDATORY 5-YEAR INSPECTIONS O	N ANY MODEL PROPELLERS.					1	H	7	1 	3O			NT	3A13 		5	C	P3EA	 
1995112400291	19951124	00291	EU 	1995	11	24	95ZZZX6329 	1	19951020	G	5551	21224152061	ATTACH FITTING 			CASA 	C212 	C212200 	2410304	EU 										HORIZ STABILIZER	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	424CA	8729 				242				CORROSION FOUND ON C-212 51D AT BEARING AREA. BEARING MATERIAL IS DISSIMILAR. SUBMITTER STATED THAT POSSIBLY A BEARING	 WAS INSTALLED DRY AT INSTALLATION BY MFG. OPERATORS SHOULD PERFORM CLOSE INSPECTION AT 1,600 FLIGHTS.					2	H	7	2 	4T				A43EU 					 
1995021000239	19950210	00239	SO 	1995	2	10	95ZZZX633 	1	19950125	G	2821	750268	BAIL 			PIPER 	PA12 	PA12 	7101202	SO 										GASCOLATOR	BROKE 	D	S			K				NONE 				K			FLUID LOSS 			CR	CRUISE 	1			SW	09	2820M	1542 			7230200	121172				THE BAIL, WHICH HOLDS THE GASCOLATOR BOWL ON, BROKE IN-FLIGHT FROM POSSIBLY A CRACK THAT DEVELOPED AT THE T-SECTION. TH	IS CRACK COULD NOT BE SEEN BECAUSE OF ITS PLACEMENT. RECOMMENDATION IS TO REPLACE BAIL WITH A BETTER ENGINEERED PART OR	 REPLACE EVERY 30 YEARS.				1	H	7	1 	3O				A780 					 
1995112400292	19951124	00292	EU 	1995	11	24	95ZZZX6330 	1	19951026	G	5551	21224154042	ATTACH FITTING 			CASA 	C212 	C212200 	2410304	EU 										HORIZ STABILIZER	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	424CA	8729 				242				CORROSION FOUND ON C-212 5ID AT BEARING AREA. BEARING MATERIAL IS DISSIMILAR. SUBMITTER STATED THAT POSSIBLY A BEARING	 WAS INSTALLED DRY AT INSTALLATION BY MFG. OPERATORS SHOULD PERFORM CLOSE INSPECTION AT 1,600 FLIGHTS.					2	H	7	2 	4T				A43EU 					 
1995112400293	19951124	00293	EA 	1995	11	24	95ZZZX6331 	2	19950915	G	7230	310830101	BLADE 		3031811 						PWA 	PT6 	PT6A65B 	52043	EA 					CT DISK	MISMANUFACTURED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01										FIFTY-NINE EACH CT BLADES RECEIVED FROM PWC. INSPECTION OF BLADES REVEALED 1 EACH BLADE MISSING THE CHAMFER ON THE TRAI	LING EDGE OF RIVET SLOT. BLADE RETURNED TO PWC FOR CREDIT.										4	T			E4EA				 
1995112400294	19951124	00294	EU 	1995	11	24	95ZZZX6332 	1	19951026	G	5551	21224152041	ATTACH FITTING 			CASA 	C212 	C212200 	2410304	EU 										HORIZ STAB	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	424CA	8729 				242				CORROSION FOUND ON C-212 51D AT BEARING AREA. BEARING MATERIAL IS DISSIMILAR. SUBMITTER STATED THAT POSSIBLY A BEARING	 WAS INSTALLED DRY AT INSTALLATION BY MFG. OPERATORS SHOULD PERFORM CLOSE INSPECTION AT 1,600 FLIGHTS.					2	H	7	2 	4T				A43EU 					 
1995112400295	19951124	00295	NE 	1995	11	24	95ZZZX6333 	2	19951012	G	7210	310709001	BEARING 								PWA 	118 	PW118 		NE 					RED GEARBOX	SPALLED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05		17940	1317 				RGB115071			THE REDUCTION GEARBOX HAD REPORTED METAL IN OIL. REDUCTION GEARBOX WAS REMOVED FROM SERVICE AND SENT TO AVIALL FOR OVER	HAUL. CAUSE OF MIO WAS SPALLED NR 19 BEARING.										4	T			E20NE				 
1995112400296	19951124	00296	CE 	1995	11	24	95ZZZX6334 	1	19951020	G	2913	939155	VALVE 			BEECH 	200 	B200 	1152922	CE 										HYDRAULIC PACK	SCREWS FAILED 	D				A	O			UNSCHED LANDING 	OTHER 			K			FLUID LOSS 			CR	CRUISE 	1			SW	01	38V	1955 				BB1412				IN-FLIGHT LOSS OF HYDRAULIC FLUID. LANDING GEAR EXTENDED DUE TO LOSS OF FLUID. AIRCRAFT DIVERTED FOR LANDING. INSPECT	ION REVEALED SOLENOID VALVE LOCATED ON HYDRAULIC POWER PACK HAD LOOSE CAP. OF THE SIX SCREWS, ONE WAS BROKEN, TWO MISSI	NG, AND THREE LOOSE. THERE IS NO LOCKING DEVISES USED ON ANY SCREWS IN THIS VALVE. SUBMITTER SUGGESTS SCREWS WTH SAFET	Y WIRE OR LOCKWASHERS BE INSTALLED TO PREVENT THIS FROM HAPPENING AGAIN.			1	L	7	2 	4T				A24CE 					 
1995112400297	19951124	00297	EA 	1995	11	24	95ZZZX6335 	2	19951020	G	8520	77416	PLUG 			HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HIO360C1A 	41514	EA 					CRANKSHAFT	MISSING 	B			HIAR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	27	61463					0003	L3448336A			LOWER PULLEY (CRANK) PLUG MISSING. STANDARD OIL PLUG INSTALLED IN ENGINE. LYCOMING P/N 77416 SHOULD BE INSTALLED IN EN	GINES ON 269 SERIES HELICOPTERS PER LYCOMING SI 1180B. INSTALLED SCHWEIZER PLUG, PN 269A5513.					1	G	7	1 	3O	3	O		4H12 	1E10				 
1995112400298	19951124	00298	EA 	1995	11	24	95ZZZX6336 	2	19951020	G	8520	77416	PLUG 			HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HIO360C1A 	41514	EA 					CRANKSHAFT	MISSING 	B			HIAR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	27	61484					0004	L3448436A			LOWER PULLEY (CRANK) PLUG MISSING. STANDARD OIL PLUG INSTALLED IN ENGINE. LYCOMING P/N 77416 SHOULD BE INSTALLED IN EN	GINES ON 269 SERIES HELICOPTERS PER LYCOMING SI 1180B. INSTALLED SCHWEIZER PLUG, PN 269A5513.					1	G	7	1 	3O	3	O		4H12 	1E10				 
1995112400299	19951124	00299	EA 	1995	11	24	95ZZZX6337 	2	19951020	G	8520	77416	PLUG 			HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HIO360C1A 	41514	EA 					CRANKSHAFT	MISSING 	B			HIAR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	27	61495					0005	L3448636A			LOWER PULLEY (CRANK) PLUG MISSING. STANDARD OIL PLUG INSTALLED IN ENGINE. LYCOMING P/N 77416 SHOULD BE INSTALLED IN EN	GINES ON 269 SERIES HELICOPTERS PER LYCOMING SI 1180B. INSTALLED SCHWEIZER PLUG, PN 269A5513.					1	G	7	1 	3O	3	O		4H12 	1E10				 
1995112400300	19951124	00300	EA 	1995	11	24	95ZZZX6338 	2	19951020	G	8520	77416	PLUG 			HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HIO360C1A 	41514	EA 					CRANKSHAFT	MISSING 	B			HIAR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	27	61416					0006	L3448536A			LOWER PULLEY (CRANK) PLUG MISSING. STANDARD OIL PLUG INSTALLED IN ENGINE. LYCOMING P/N 77416 SHOULD BE INSTALLED IN EN	GINES ON 269 SERIES HELICOPTERS PER LYCOMING SI 1180B. INSTALLED SCHWEIZER PLUG, PN 269A5513.					1	G	7	1 	3O	3	O		4H12 	1E10				 
1995112400301	19951124	00301	EA 	1995	11	24	95ZZZX6339 	2	19951020	G	8520	77416	PLUG 			HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HIO360C1A 	41514	EA 					CRANKSHAFT	MISSING 	B			HIAR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	27	61447					0007	L3448736A			LOWER PULLEY (CRANK) PLUG MISSING. STANDARD OIL PLUG INSTALLED IN ENGINE. LYCOMING P/N 77416 SHOULD BE INSTALLED IN EN	GINES ON 269 SERIES HELICOPTERS PER LYCOMING SI 1180B. INSTALLED SCHWEIZER PLUG, PN 269A5513.					1	G	7	1 	3O	3	O		4H12 	1E10				 
1995021000240	19950210	00240	CE 	1995	2	10	95ZZZX634 	1	19950129	G	2810	C1560030101	FUEL CAP 			CESSNA	182 	182A 	2072704	CE 										WING TANK	FAILED 	D				O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			CE	03	4850D	1 				34950				FUEL CAP FAILURE, RETAINING TAB, BROKE AFTER LESS THAN ONE HOUR IN SERVICE. PART RETURNED TO CESSNA FOR INSPECTION. TH	IS FAILURE LED TO THE LOSS OF FUEL IN THE TANK DURING FLIGHT.					1	H	7	1 	3O			NT	3A13 					 
1995112400302	19951124	00302	EA 	1995	11	24	95ZZZX6340 	2	19951020	G	8520	77416	PLUG 			HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HIO360C1A 	41514	EA 					CRANKSHAFT	MISSING 	B			HIAR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	27	61458					0008	L3447736A			LOWER PULLEY (CRANK) PLUG MISSING. STANDARD OIL PLUG INSTALLED IN ENGINE. LYCOMING P/N 77416 SHOULD BE INSTALLED IN EN	GINES ON 269 SERIES HELICOPTERS PER LYCOMING SI 1180B. INSTALLED SCHWEIZER PLUG, PN 269A5513.					1	G	7	1 	3O	3	O		4H12 	1E10				 
1995112400303	19951124	00303	EA 	1995	11	24	95ZZZX6341 	2	19951020	G	8520	77416	PLUG 			HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HIO360C1A 	41514	EA 					CRANKSHAFT	MISSING 	B			HIAR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	27	61439					0009	L3449136A			LOWER PULLEY (CRANK) PLUG MISSING. STANDARD OIL PLUG INSTALLED IN ENGINE. LYCOMING P/N 77416 SHOULD BE INSTALLED IN EN	GINES ON 269 SERIES HELICOPTERS PER LYCOMING SI 1180B. INSTALLED SCHWEIZER PLUG, PN 269A5513.					1	G	7	1 	3O	3	O		4H12 	1E10				 
1995112400304	19951124	00304	EU 	1995	11	24	95ZZZX6342 	1	19951017	G	2913	S40	COUPLER 		704A34310006	SNIAS 	350 	AS350B 	8680801	EU 										HYDRAULIC PUMP	WORN 	D				A				UNSCHED LANDING 				O			OTHER 			NR	NOT REPORTED 	1			SO	15	888TV				20142708	2007				PILOT EXPERIENCED CONTROL FEEDBACK IN CYCLIC STICK. MADE UNEVENTFUL PRECAUTIONARY LANDING. HYDRAULIC PUMP INSPECTION R	EVEALED DRIVE SPLINES ON PUMP AND COUPLING SLEEVE SEVERELY WORN CAUSING PUMP TO OPERATE INTERMITTENTLY. REPLACED PUMP A	ND COUPLING SLEEVE AND NO FURTHER PROBLEM NOTED. SUBMITTER RECOMMENDS PUMP DRIVE INSPECTION EACH 100 HOURS. AIRFRAME T	OTAL TIME 3310.9 HOURS.			1	G	7	1 	3U			 	H9EU 					 
1995112400305	19951124	00305	SW 	1995	11	24	95ZZZX6343 	1	19951030	G	2916	206076022101	RESERVOIR 			BELL 	206 	206B 	1181511	SW 										HYDRAULIC SYSTEM	WATER CONTAM 	H				A				UNSCHED LANDING 				K			FLUID LOSS 			CL	CLIMB 	1			SO	15	67737	351 				5197				PRECAUTIONARY LANDING DUE TO HYDRAULIC FLUID LOST DURING START. MAINTENANCE EVALUATION REVEALED THAT WATER GETS IN RESE	RVOIR AND CAUSES FLUID TO FORM, SIPHONING FLUID OVERBOARD THROUGH VENT LINE.					1	G	7	1 	3U				H2SW 					 
1995112400306	19951124	00306	WP 	1995	11	24	95ZZZX6344 	1	19951024	G	6320	A1531	RETAINER NUT 		A0061 	ROBSIN	R22 	R22 	7640102	WP 										M/R SHAFT	UNTORQUED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	240RH	3835 	1835 		0242	0240				DURING C/W AD 95-06-03, BOTH UPPER AND LOWER M/R SHAFT RETAINER NUTS WERE FOUND FINGER-TIGHT. (BREAK-LOOSE TORQUE LESS 	THAN 2 FEET/POUND.) BOTH GEAR CARRIER DOWEL PINS SLIGHTLY DAMAGED, UPPER LOCK WASHER HOLES ELONGATED CIRCUMFERENCIALLY.					1	G	7	1 	3O				H10WE 					 
1995112400307	19951124	00307	EU 	1995	11	24	95ZZZX6345 	1	19951027	G	5311	105300521	FRAME 			BOLKMS	105 	BO105LSA3 	5626020	EU 										STROBE POWER PAC	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	93LF	753 				2038				INSP FND CRACK STARTED IN FRAME 11L LOWER LT MOUNTING BRACKET FOR STOBE POWER PACK. CRACK PROPAGATED TO LEFT & INTO OUT	ER SKIN OF TAILBOOM 2.50 INCHES FWD OF FRAME 11L. SUBMITTER STATED MTNG BKT WHERE CRACK STARTED STRESSED FRAME IN AREA 	OF POWER PACK MNT. MIDDLE OF FRAME HAS LARGE LIGHTNING HOLE THAT ELONGATES WITH CHANGING OF ANTI-TORQUE FORCES. MNT BK	T ACROSS MIDDLE OF THAT HOLE PLACES UNDUE STRESS IN AREA OF MNTING BOLTS. SUBMITTER STATED FRAME 11L SHD BE INSP EVERY 	25 HRS FOR CRACKS ADJ TO STROBE POWER PACK MNT BOLTS. TAILBOOM SKIN IN THIS AREA SHD BE INSP DAILY. SUBMITTER STATED O	THER BO105CBS ACFT DID NOT HAVE POWER SUPPLY MNT'D IN THIS AREA. SUBMITTER STATES THIS IS A BO105LS ARRANGEMENT ONLY.	1	G	7	2 	3U				H3AU 					 
1995120100046	19951201	00046	SW 	1995	12	1	95ZZZX6346 	1	19951018	G	6710	206001344001	CYCLIC STICK 			BELL 	206 	206L1 	1182107	SW 										PILOT CYCLIC	MISINSTALLED 	C		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	03	5743D	6054 				45388				WHEN PILOT'S CYCLIC STICK WAS INSTALLED AFTER INSPECTION, IT WAS RADIALLY TURNED ENOUGH OFF-CENTER TO CAUSE IT TO BE IN 	AN UNUSUAL OR UNNATURAL POSITIION DURING FLIGHT. THE SLOTS FOR THE MOUNTING BOLTS ALLOW FOR A MODERATE AMOUNT OF RADIAL	 MOVEMENT IN THE LEVER ASSEMBLY. SUBMITTER SUGGESTS THE CENTERING OF THE STICK SHOULD BE CHECKED TO PREVENT THIS CONDIT	ION. THIS COULD BE ACCOMPLISHED BY INSTALLING THE CYCLIC RIGGING BOLT IN THE PIVOT ASSEMBLY, THEN ROTATING THE STICK TO	 THE NORMAL NEUTRAL POSITION IN THE LEVER.		1	G	7	1 	3U				H2SW 					 
1995120100047	19951201	00047	NE 	1995	12	1	95ZZZX6347 	2	19950804	G	7323	25249994	GOVERNOR 	BENDIX 		BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					NR 1 ENGINE	FAILED 	A			HEEA	A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			SW	03	5736J	7897 	1742 		A61467	31140	CPPS63158			AIRCRAFT DEPARTED FOR OFFSHORE. OUTBOARD NR 1 ENGINE EXPERIENCED A LOW SIDE GOVERNOR FAILURE. RETURNED AND LANDED WITH	OUT INCIDENT. REPLACED GOVERNOR ASSY. PT6 IPC, CHAPTER 72-10-30, FIGURE 1, ITEM 20C.					1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1995120100048	19951201	00048	WP 	1995	12	1	95ZZZX6348 	1	19951109	G	6520	NAS130424H	BOLT 			HUGHES	369 	369HS 	4470728	WP 										T/R GRBOX	WRONG PART 	G	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	9110F					1190210S				ACFT WAS IN FOR A 100-HOUR INSP. MECHANIC PERFORMING TAIL ROTOR GEARBOX MOUNT RE-TORQUE, CUT THE SAFETY WIRE AND THE BO	LT PULLED OUT. IT WAS ALSO FOUND THAT 2 OTHER BOLTS WERE ONLY IN PLACE BY 2 THREADS. MECHANIC STATED BOLTS WERE INCORR	ECT, PN NAS1304-24H, AND THERE WAS A WASHER UNDER THE HEAD OF EACH OF THE 4 BOLTS. RECORDS REVEALED THE TAIL BOOM HAD B	EEN REPLACED WITH AN ALTERNATE TAIL BOOM, PN 369A3500-619. PARTS MANUAL INDICATES MODEL TAIL BOOM, BOLT, PN NAS1304-26H	 (ITEM 38) WAS TO BE INSTALLED AND NO WASHERS UNDER THE HEAD OF THE BOLT. MM ONLY MENTIONS NAS1304-24H BOLT FOR INSTALL	ATION AND DEPICTS A WASHER UNDER THE BOLT HEAD IN THE ILLUSTRATION.	1	G	7	1 	3U				H3WE 					 
1995120100049	19951201	00049	NE 	1995	12	1	95ZZZX6349 	1	19951107	G	6410	7610105020045	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	TIP WT LOST 	G	S	A		A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			SW	03	31217	10030				760229				WHILE IN CRUISE FLIGHT, PILOT EXPERIENCED SEVERE VIBRATION AND EXECUTED A PRECAUTIONARY LANDING. SUBSEQUENT INVESTIGATI	ON REVEALED ONE OF THE TAIL ROTOR BLADES LOST A BLADE TIP WEIGHT. THE WEIGHT AND COMPOSITE MATERIAL WEIGHED APPROXIMATE	LY 92 GRAMS.				1	G	7	2 	3U				H1NE 					 
1995021000241	19950210	00241	SO 	1995	2	10	95ZZZX635 	2	19950112	G	8530		CYLINDER 			BEECH 	36 	A36 	1151604	CE 	CONT 	O520 	IO520BB 	17032	SO 					1 THROUGH 6	EXCESS WEAR 	B			CCAR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	3683X	7720 				E1723	285584R			ENGINE TT SINCE FACTORY OVERHAUL, 7726 HOURS. REBUILT 1-14-92. INSTALLED 2-12-92. CYLINDER HEAD DATES 8-91, ALL 6 CYL	NDERS, LOW COMPRESSIONS ALL CYLINDERS. CYLINDERS ARE WORN BEYOND SERVICEABLE LIMITS AND SEVERE RING WEAR. ROCKER SHAFT	S ARE SEVERELY WORN, AND UNAIRWORTHY.				1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995021000242	19950210	00242	EA 	1995	2	10	95ZZZX636 	2	19950126	G	8530	5498	ROCKER ARM 			TCRAFT	BF 	BF60 	8850332	EA 	FRNKLN	4AC150	4AC150A 	27004	EA 					CYLINDER NR 2	BROKE 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			EA	07	23622	2500 				1347	2801			WHILE IN CRUISE FLIGHT, ENGINE WOULD ONLY DEVELOP APPROXIMATELY 1300 PRM. AIRCRAFT MADE PRECAUTIONARY LANDING. INVESTI	GATION SHOWED BOTH ROCKER ARMS BROKEN CYLINDER NR 2. EXHAUST ROCKER SHOWED EVIDENCE OF BEING CRACKED FOR LONG PERIODS O	F TIME. BELIEVED THAT EXHAUST ROCKER BROKE AND LOOSE PIECE JAMMED INTAKE VALVE CAUSING INTAKE ROCKER TO FAIL. SUBMITTE	R RECOMMENDS FREQUENT CLOSE INSPECTION OF ARMS.			1	H	7	1 	3O	3	O		A699 	ATC194				 
1995120100061	19951201	00061	WP 	1995	12	1	95ZZZX6361 	2	19951023	G	7230	3073330	SEAL/RING 			LEAR 	35 	35A 	5170602	CE 	GARRTT	TFE731	TFE73122B 	01518	WP 					HP COMPRESSOR	LEAKING 	A			ROSA	A				UNSCHED LANDING 				B	K		SMOKE/FUMES/ODORS/SPARKS 	FLUID LOSS 		CL	CLIMB 	1			SW	01	135DE	1466 				667	P89726			ABQ - AIRCRAFT EXPERIENCED SMOKE IN CABIN IMMEDIATELY AFTER TAKEOFF. FLIGHT CREW FOLLOWED EMERGENCY PROCEDURES AND LAND	ED WITHOUT INCIDENT. BORESCOPE INSPECTION OF RIGHT ENGINE REVEALED 4/5 BEARING SEALS LEAKING OIL INTO COMPRESSOR SECTIO	N. RIGHT ENGINE WAS REMOVED FROM SERVICE. NOTE: THIS IS A FOLLOW-UP REPORT SUBMITTED 10-23-95.				2	L	7	2 	4F	4	F		A10CE 	E6WE				 
1995021000243	19950210	00243	EA 	1995	2	10	95ZZZX637 	2	19950126	G	8520	74970	CRANKSHAFT 								LYC 	O360 	O360A3A 	41514	EA 					NR 3 JOURNAL	BROKE 	B			KG4R	O				OTHER 				O			OTHER 			CR	CRUISE 	1			SO	19	2FOR						L1926636A			WHILE IN-FLIGHT, CATASTROPHIC FAILURE -- CRANKSHAFT BROKE CLEAN IN HALF AT NR 3 CONN ROD JOURNAL. SUSPECT HEAT/FATIGUE 	CRACK, OR IMPROPER UNDERSIZING PROCESS.										3	O			E286				 
1995120100181	19951201	00181	SO 	1995	12	1	95ZZZX6379 	2	19951024	G	7414	1035716520S	COIL 		105136539 	CESSNA	172 	172G 	2072420	CE 	CONT 	O300 	O300D 	17022	SO 					ENG LT MAG	OPEN 	H				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	09	6070R	80 			K059203D	17253739	O25651R			LEFT MAGNETO FAILURE DUE TO OPEN IN SECONDARY WINDING OF THE COIL.						1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995021000244	19950210	00244	SO 	1995	2	10	95ZZZX638 	1	19950123	G	7810	8377504	TAILPIPE 			PIPER 	PA46 	PA46350P 		SO 										HEAT MUFF	FLANGE BROKE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	91734	472 				4622040				FLANGE SUPPORT FOR HEAT MUFF BROKE LOOSE AT WELD AREA AT MOUNTING FLANGE.						1	L	7	1 	3O			RT	A25SO 					 
1995120100182	19951201	00182	EA 	1995	12	1	95ZZZX6380 	2	19951024	G	7414	10391088	COIL 		103493652 	PIPER 	PA28 	PA28R200 	7102811	SO 	LYC 	O360 	IO360C1C 	41514	EA 					ENG LT MAG	FAILURE 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	09	2086T	51 			A08997	28R7135030	L760051A			LEFT MAGNETO FAILURE DUE TO COIL FAILURE (SECONDARY WINDINGS OPEN).						1	L	7	1 	3O	3	O		2A13 	1E10				 
1995120100183	19951201	00183	SO 	1995	12	1	95ZZZX6381 	2	19951017	G	8530	632585	PISTON 			CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					LT/RT ENGINE	WRONG PART 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	11	3380Q		328 			421B0264	600218			FOUND 11 OUT OF 12 CYLINDERS WITH THIS P/N PISTON WHICH IS NOT APPROVED FOR USE IN GTSIO520 ENGINES. PISTONS WERE SENT 	FROM ECI AS PART OF A GTSIO-520 CYLINDER ASSY. P/N 632585 CYLINDER IS DOMED WITH NO STEEL INSERT FOR THE TOP RING GROOV	E. THE CORRECT PISTON FOR THE GTSIO520 ENGINE IS FLAT WITH A STEEL INSERT. ONE PISTON WAS CORRECT ON LT ENGINE, BUT TH	IS WOULD CAUSE AN OUT OF BALANCE CONDITION.			1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995120100185	19951201	00185	SO 	1995	12	1	95ZZZX6383 	2	19951017	G	8530	642344RB	CYLINDER 			CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					CYLS 1,2,6	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	3380Q		328 			421B0264	600218			FOUND THREE CYLINDERS CRACKED BETWEEN THE SPARK PLUG AND INJECTOR HOLES. SUBMITTER STATED CRACKS MAY BE CAUSED BY OVERT	ORQUING THE INJECTOR NOZZLES OR POSSIBLY EXCESSIVE VIBRATION.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995120100186	19951201	00186	SO 	1995	12	1	95ZZZX6384 	1	19951024	G	7430		SWITCH 	GERDES 		PIPER 	PA28 	PA28181 	7102807	SO 										ENG IGNITION	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	2925Q					287790422				WHILE PERFORMING A PRE-INSPECTION RUN-UP WHEN IGNITION SWITCH ROTATED PAST OFF POSITION, ENGINE CONTINUED TO RUN ON RIGH	T MAG. SWITCH RETURNED TO OFF CONDITION WHEN RELEASED, BUT SWITCH SHOULD NOT ALLOW CONTINUED RUNNING WHEN IN THE AREA O	F THE OFF POSITION. SUBMITTER RECOMMENDS MAKING THIS CHECK PART OF EACH ANNUAL ON ALL KEY OR TWIST TO START TYPE IGNITI	ON SWITCHES. HAVE ALSO FOUND THIS SAME CONDITION ON 3 BENDIX SWITCHES NOT APPLICABLE TO AD NOTE 76-07-12.			1	L	7	1 	3O				2A13 					 
1995120100187	19951201	00187	EA 	1995	12	1	95ZZZX6385 	3	19951030	G	6111		BLADE 			PIPER 	PA28 	PA28180 	7102808	SO 						SNSNCH	76E	76EM8 	EA 	PROPELLER	SEPARATED 	G				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			D	E		INFLIGHT SEPARATION 	VIBRATION/BUFFET 		CR	CRUISE 	1			EA	09	477SP	570 				281210		7139		ACCIDENT INVESTIGATION REVEALED APPROXIMATELY 26 INCHES OF BLADE SEPARATED FROM PROPELLER IN-FLIGHT. FORCED LANDING MAD	E WITHOUT OCCUPANT INJURY. AIRCRAFT DESTROYED IN POST-IMPACT FIRE. SEVERE VIBRATION NOTICED BY PILOT, IN-FLIGHT SHUT D	OWN ACCOMPLISHED. PROPELLER HAD NO EVIDENCE OF PRE-EXISTING DAMAGE. PILOT STATED NONE NOTED PRIOR TO FLIGHT, 570 HOURS	 TSN, 110 HOURS SINCE LAST INSPECTION (ANNUAL). NO RECORD OF ANY PROPELLER SERVICE. SUBMITTER RECOMMENDS NDI INSPECTIO	N OF PROPELLER AT EACH ANNUAL INSPECTION AND/OR 100 HOURS TIME IN SERVICE.		1	L	7	1 	3O				2A13 		5	N	P4EA	 
1995120100188	19951201	00188	SO 	1995	12	1	95ZZZX6386 	2	19951023	G	8530		CYLINDER 		641370CP 	AMTR 	LITING	WHTLIGHTING 	05612QS	GL 	CONT 	O360 	IO360G 	17025	SO 					NR 3	SEPARATED 	D				A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			CL	CLIMB 	1			SW	11	25WL		414 		04	2	901025OH			DURING NORMAL TAKEOFF, OPERATOR EXPERIENCED SEVERE ROUGHNESS OF ENGINE. RETURNED TO AIRPORT. DURING TEAR DOWN OF ENGIN	E, FOUND NR 3 CYLINDER SEPARATED AT BARREL. CYLINDERS TORN DOWN 400 HOURS PRIOR FOR CHROME. SUBMITTER BELIEVES CYLINDE	R NOT REASSEMBLED COMPLETELY. INNERMOST THREADS FULL OF DIRT AND OIL AND NOT STRIPPED OFF WITH BARREL SEPARATION. NR 5	 CYLINDER EXIBITS SIMILAR CONDITION. REMOVED FROM SERVICE. SUBMITTER SUGGESTS MORE ATTENTION BE PAID TO FUEL STAINING 	AT BARREL AND HEAD UNION.		1	L	7	1 	3O	3	O	RC	EXPA1L71	E1CE				 
1995120100189	19951201	00189	SO 	1995	12	1	95ZZZX6387 	2	19951023	G	8520	649134	CRANKSHAFT 			CESSNA	185 	A185F 	2072821	CE 	CONT 	O520 	IO520B 	17032	SO 					NR 2 MAIN	FAILED 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			NM	08	185RM	819 				18502117	175059R			IN-FLIGHT, CRUISE SETTING, ENGINE RPM DROPPED TO ZERO, PROPELLER ROTATED 2-3 TIMES AFTER RPM GAUGE READ ZERO. PILOT EXE	CUTED EMERGENCY LANDING. UPON ENGINE TEAR-DOWN, FOUND CRANKSHAFT BROKEN AT FORWARD CHEEK OF NR 2 MAIN BEARING JOURNAL. 	 SUSPECT DEFECT (SCRATCH, NICK) STARTED IN JOURNAL RADIUS WHERE NR 2 CYLINDER CONNECTING ROD CONTACTED RADIUS POINT. SU	BMITTER RECOMMENDS PRECAUTIONS TO BE TAKEN AT ENGINE OVERHAUL TO PRECLUDE EXCESSIVE MOVEMENT OF CONNECTING RODS AGAINST 	CRANKSHAFT THROWS AT DISASSEMBLY/REASSEMBLY.		1	H	7	1 	3O	3	O		3A24 	E5CE				 
1995120100190	19951201	00190	EU 	1995	12	1	95ZZZX6388 	1	19951031	G	7921	TB0954010001	SUPPORT BAFFLE 			SOCATA	TB9 	TB9 	8680694	EU 										OIL COOLER	BROKEN 	B			DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	175ER	193 				1352				DURING SCHEDULED MAINTENANCE (100-HOUR INSPECTION), THE OIL COOLER SUPPORT BAFFLE WAS FOUND BROKEN AT 2 OF THE 4 MOUNT P	OINTS AND SEVERELY CRACKED ON THE OTHER 2 MOUNTS. THIS CONDITION COULD CAUSE OIL LOSS AND POSSIBLE ENGINE FAILURE. INS	TALLED NEW OIL COOLER BAFFLE.				1	L	7	1 	3O			NT	AS1EU 					 
1995120100191	19951201	00191	SO 	1995	12	1	95ZZZX6389 	1	19951013	G	8011	MZ422	STARTER 	ELECTROSYS 		PIPER 	PA28 	PA28151 	7102805	SO 										ENGINE	INOPERATIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	41399		40 		4091039	287415199				STARTER FAILURE COMPLAINT WAS TRACED TO HIGH RESISTANCE BETWEEN GROUND BRUSH HOLDERS AND END PLATE. APPEARS TO BE SOME 	TYPE OF COMPOUND BETWEEN END PLATE AND BRUSH HOLDERS. SPECULATION IS THAT THE COMPOUND IS CAUSING THE HIGH ELECTRICAL R	ESISTANCE.				1	L	7	1 	3O				2A13 					 
1995021000245	19950210	00245	CE 	1995	2	10	95ZZZX639 	1	19950113	G	2750	MS250261	SWITCH 			BEECH 	58 	58 	1152740	CE 										FLAP UP	DEFECTIVE 	B			ERYR	O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			SO	11	113ZM	174 				TH1716				PILOT REPORTED FLAPS WOULD NOT RETRACT UP PAST THE APPROACH SETTING. SYSTEM WAS TROUBLESHOT AND THE FLAP UP SETTING SWI	TCH WAS FOUND DEFECTIVE. REASON UNKNOWN. REPLACED SWITCH, OPS CHECK GOOD.					1	L	7	2 	3O				3A16 					 
1995120100192	19951201	00192	EA 	1995	12	1	95ZZZX6390 	2	19951026	G	7414	1068291013	MAGNETO 								LYC 	O540 	TIO540* 	41532	EA 					RETARD GAP	MISOVERHAULED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01					L149409GR					RECEIVED ZERO TIME REBUILT MAG FROM TCM. RETARD POINTS WERE SET TO BOOK SPECS OF 11 DEGREES, BUT RETARD POINTS GAP WAS 	.004 INCH. BOOK SPEC IS .016 PLUS OR MINUS .004 INCH. THIS MAG BUILT UNDER WORK ORDER NR 862174-2, AND MAINTENANCE REL	EASE IS DATED 12-14-94.									3	O			E14EA				 
1995120100193	19951201	00193	SO 	1995	12	1	95ZZZX6391 	1	19951025	G	2810	3140	TANK 			PIPER 	PA18 	PA18 	7101802	SO 										LT FUEL	LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03					601					TANK HAD SMALL LEAK AFT SEAM MID-WAY BETWEEN SIDES. FOUND SMALL CRACK, .50 INCH, WELDED SEAM FOR 4 INCHES EITHER SIDE O	F CRACK. SUBMITTER STATED NO APPARENT REASON FOR CRACK.					1	H	7	1 	3O				1A2 					 
1995120100194	19951201	00194	SO 	1995	12	1	95ZZZX6392 	2	19951013	G	8540	635050	STARTER DRIVE 								CONT 	O470 	O470L 	17026	SO 					ENGINE	HOUSING BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03			220 				691041LR			STARTER DRIVE HOUSING CRACKED. SUBMITTER SUSPECTS BACKFIRING DURING STARTING.											3	O			E273				 
1995120100196	19951201	00196	SO 	1995	12	1	95ZZZX6394 	1	19951012	G	3213	1284403	STRUT 			PIPER 	PA18 	PA18150 	7101828	SO 										RT MLG	FAILED 	G				O				OTHER 				O			OTHER 			LD	LANDING 	1			AL	03	9692P					187509036				RIGHT SHOCK STRUT FAILED ON LANDING ON A DIRT/GRAVEL RUNWAY. SUBMITTER STATED POSSIBLY A 'HARD' LANDING. NTSB IS HAVIN	G THE PART TESTED FOR FATIGUE AND/OR CORROSION.					1	H	7	1 	3O				1A2 					 
1995120100197	19951201	00197	SO 	1995	12	1	95ZZZX6395 	2	19950901	G	8520		CONNECT ROD 			CESSNA	340 	340A 	2076405	CE 	CONT 	O520 	TSIO520N 	17040	SO 					RT ENG NR 6	FAILED 	D				O				OTHER 				O			OTHER 			CR	CRUISE 	1			EA	07	4138G		1200 			340A0309	509760			RIGHT ENGINE, NR 6 CONNECTING ROD FAILED IN-FLIGHT, BROKEN AT CRANKSHAFT END. TT SMOH, APPROXIMATELY 1,200 HOURS, LOG B	OOKS INDICATE ROD WAS 'YELLOW TAGGED' FOR THAT OVERHAUL; THEREFORE, PART TT UNKNOWN. SUBMITTER RECOMMENDS ON RECIP ENGI	NES OF THIS POWER AND COMPLEXITY, NEW CONNECTING RODS SHOULD BE MANDATORY AT OVERHAUL.				1	L	7	2 	3O	3	O		3A25 	E8CE				 
1995120100198	19951201	00198	CE 	1995	12	1	95ZZZX6396 	1	19950826	G	2841		GAUGE 			CESSNA	172 	172N 	2072434	CE 										FUEL QUANTITY	DEFECTIVE 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			GL	23	738CL					17269871				SUSPECT INACCURATE FUEL GAUGES MAY HAVE BEEN A CONTRIBUTING FACTOR TO AN EMERGENCY LANDING.						1	H	7	1 	3O			NT	3A12 					 
1995120100199	19951201	00199	GL 	1995	12	1	95ZZZX6397 	3	19951022	G	6111	FC84754	BLADE 			PIPER 	PA31 	PA31 	7103102	SO 						HARTZL	HCE2Y	HCE2YR2 	GL 	NR 1 ENGINE	SEPARATED 	G		A		A				UNSCHED LANDING 				D	E		INFLIGHT SEPARATION 	VIBRATION/BUFFET 		CR	CRUISE 	1			EA	09	85DL	2085 				3123		CJ718		PROPELLER BLADE FRACTURED FULL CHORD AND SEPARATED IN-FLIGHT. FRACTURE OCCURRED APPROXIMATELY 11.5 INCHES FROM BLADE TI	P. VISUAL INSPECTION REVEALED BLADE LEADING EDGE CHIPPED AT FORWARD MOST POINT OF FRACTURE LINE. BLADE CHIPPED ON BLAD	E BACKFACE JUST AFT OF LEADING EDGE APEX. NOT VISIBLE FROM BLADE FACE. SOURCE OF CHIP UNKNOWN. TIME DEFECT EXISTED PR	IOR TO FAILURE UNKNOWN. SUBMITTER SUGGESTS INCREASED ATTENTION AT PRE-FLIGHT RECOMMENDED.			1	L	7	2 	3O				A20SO 		5	C	P9EA	 
1995120100298	19951201	00298	EU 	1995	12	1	95ZZZX6398 	1	19951027	G	7921	TB0954010001	SUPPORT BAFFLE 			SOCATA	TB9 	TB9 	8680694	EU 										ENG OIL COOLER	CRACKED 	B		A	DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	114ER	582 				1333				DURING A 100-HOUR INSPECTION, THE OIL COOLER MOUNT BAFFLE ASSY WAS FOUND SEVERELY CRACKED WITH PIECES MISSING. IF THE O	IL COOLER BECOMES COMPLETELY DETACHED, IT COULD VIBRATE AGAINST THE ENGINE MOUNT AND CAUSE THE OIL COOLER TO RUPTURE. T	HIS ENTIRE BAFFLE ASSY IS WEAK AND PROVIDES MINIMAL SUPPORT OF THE OIL COOLER. SUBMITTER STATED IN THE FLEET OF 26 AIRC	RAFT, ALL HAVE HAD BAFFLE CHANGES SEVERAL TIMES. THE AIRCRAFT MANUFACTURER HAS BEEN NOTIFIED OF THIS PROBLEM SEVERAL TI	MES. THE ENTIRE BAFFLE OR COOLER MOUNT ASSY SHOULD BE STRENGTHENED AND MADE OF HEAVIER GAUGE MATERIAL. A NEW BAFFLE AS	SY WAS INSTALLED.	1	L	7	1 	3O			NT	AS1EU 					 
1995120100299	19951201	00299	NM 	1995	12	1	95ZZZX6399 	1	19951018	G	7920	90024811	HOSE 			PIPER 	PA60 	PA60601P 	7106012	NM 										LT ENGINE COOLER	LEAKING 	D		A		K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	07	60728					61P070079633				HOSE FOUND LEAKING INSIDE FIRE SLEEVE. HOSE FOUND STIFF OR MORE RIGID THAN EXPECTED AFTER ONLY 348 HOURS IN SERVICE. T	HIS HOSE WAS AN AEROQUIP HOSE DATED 1Q92 AND WAS SECOND ONE TO FAIL ON THIS AIRCRAFT (OTHER ONE ON RIGHT ENGINE). SUBMI	TTER STATED POSSIBLE FAULTY MATERIAL.				1	M	7	2 	3O			RT	A17WE 					 
1995021000246	19950210	00246	CE 	1995	2	10	95ZZZX640 	1	19950113	G	3310	1023840391	CONTROLLER 			BEECH 	58 	58 	1152740	CE 										PANEL FLOOD	INOPERATIVE 	B			ERYR	O				OTHER 				O			OTHER 			CR	CRUISE 	1			SO	11	113ZM	174 			1326A	TH1716				INSTRUMENT PANEL FLOOD LIGHTS WENT OUT DURING NIGHT FLIGHT. TROUBLESHOT SYSTEM AND FOUND LIGHT CONTROLLER INOPERATIVE. 	 REASON UNKNOWN. REPLACED UNIT. OPS CHECK GOOD.					1	L	7	2 	3O				3A16 					 
1995120100300	19951201	00300	CE 	1995	12	1	95ZZZX6400 	1	19951025	G	3211	24411001	PIVOT 			CESSNA	172 	172RG 	2072438	CE 										RT MLG	FAILED 	D		A		O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			WP	07	6303V	4544 				172RG0615				UNABLE TO FULLY EXTEND OR RETRACT RIGHT LANDING GEAR. GEAR UP LANDING WITH NOMINAL DAMAGE. INSPECTION FOUND SPLINE BRO	KEN OFF OF PIVOT ASSEMBLY. SUBMITTER STATED IT APPEARS TO BE A FATIGUE FAILURE.					1	H	7	1 	3O				3A17 					 
1995120100301	19951201	00301	CE 	1995	12	1	95ZZZX6401 	1	19951026	G	3710	441CC	PUMP 	AIRBORNE 		CESSNA	421 	421C 	2076016	CE 										LT ENG VACUUM	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	265JJ		813 		20E181	421C0822				THE VACUUM PUMP WAS OVERHAULED BY REPAIR STA NR 766-44. THE TIME SINCE OVERHAUL WAS 813 HOURS. SUBMITTER STATES THIS I	S ABOUT NORMAL SERVICE LIFE FOR THIS TYPE OF PUMP, AND IS EVEN BETTER FOR AN OVERHAULED UNIT.					1	L	7	2 	3O				A7CE 					 
1995120100302	19951201	00302	EA 	1995	12	1	95ZZZX6402 	2	19951023	G	8530	L12215	CYLINDER 			PIPER 	PA31 	PA31P 	7103120	SO 	LYC 	O541 	TIGO541E1A 	41539	EA 					LT ENG NR 5 EXH	BOSS BROKEN 	B			EKIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	26556		326 			31P7400184	L13962			NR 5 CYLINDER ON LT ENGINE INBOARD EXHAUST ROCKER SHAFT ARM BOSS BROKE OFF CYLINDER. NO EVIDENCE OF PREVIOUS CRACK. NO	 INDICATION OF VALVE CONTACTING PISTON. SUSPECT CASTING DEFECT AT MANUFACTURER.					1	L	7	2 	3O	3	O		A8EA 	E19EA				 
1995120100303	19951201	00303	SO 	1995	12	1	95ZZZX6403 	1	19951023	G	3710	842CW	PUMP 			PIPER 	PA31 	PA31P 	7103120	SO 										ENGINE	SHAFT SHEARED 	B			EKIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	26556	163 				31P7400184				PRESSURE PUMP SHEARED DRIVE SHAFT. UNIT SEIZED.						1	L	7	2 	3O				A8EA 					 
1995120100304	19951201	00304	CE 	1995	12	1	95ZZZX6404 	1	19951025	G	3211	24411001	PIVOT 			CESSNA	172 	172RG 	2072438	CE 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	9456D	6675 				172RG1171				EXPERIENCED LOSS OF BRAKING. INSPECTION FOUND CRACK IN MAIN GEAR PIVOT ASSEMBLY AT RADIUS WHERE SHAFT JOINS SPLINE. NO	 RECORD OF PREVIOUS COMPLIANCE WITH SEB 90-1 R2.					1	H	7	1 	3O				3A17 					 
1995120100305	19951201	00305	CE 	1995	12	1	95ZZZX6405 	1	19951025	G	3211	24411001	PIVOT 			CESSNA	172 	172RG 	2072438	CE 										RT MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	518PU	7483 				172RG1135				EXPERIENCED LOSS OF BRAKING ON RT SIDE. FOUND CRACK IN PIVOT ASSEMBLY WHERE SHAFT RADIUS JOINS SPLINE. NO RECORD OF PR	EVIOUS COMPLANCE WITH SEB 90-1 R2.					1	H	7	1 	3O				3A17 					 
1995120100306	19951201	00306	SO 	1995	12	1	95ZZZX6406 	2	19951031	G	8550		OIL PUMP 			CESSNA	172 	172 	2072402	CE 	CONT 	O300 	O300A 	17022	SO 					ENGINE OIL	BUSHING DEFECT 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	27	6079A		82 			28679	1599708AR			DURING MAJOR OVERHAUL, REAR CASE/OIL PUMP ASSY AND GEARS REWORKED. ENGINE HAD GOOD OIL PRESSURE, BUT AT OIL CHANGE, PUM	P WOULD NOT PRIME ITSELF. DISSASSEMBLY REVEALED PUMP BUSHINGS WERE .004 INCH OUT OF CENTER AND ALLOWED TOO MUCH CLEARAN	CE ON ONE SIDE.				1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1996011000001	19960110	00001	SO 	1996	1	10	95ZZZX6407 	2	19951016	G	8530	653421	GUIDE 			PIPER 	J3 	PA11 	7101102	SO 	CONT 	C90 	C9012F 	17009	SO 					NR 2,4 CYLS EXH	EXCESS WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	27	4565M	98 				1168	4103688			OWNER REPORTED EXCESSIVE BLOW-BY. COMPRESSION CHECK NR 2 - 52/80 AND NR 4 - 50/80. EXHAUST VALVES LEAKING. PISTONS HE	AVY WITH CARBON BUILD-UP. EXHAUST GUIDES WORN BEYOND TCM LIMITS. SUBMITTER STATES THIS IS 4 OUT 10 CYLINDERS INSTALLED	, ALL WITH LESS THAN 100 HOURS SINCE NEW.				1	H	7	1 	3O	3	O		A691 	E252				 
1995120100307	19951201	00307	EA 	1995	12	1	95ZZZX6408 	2	19950811	G	7414	D4RN2000	MAGNETO 	BENDIX 		BEECH 	76 	76 	1153005	CE 	LYC 	O360 	LIO360A1G6 	41515	EA 					ENGINE	DEFECTIVE 	B			VT3R	K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			WP	09	6013X		360 		4071459	ME113	RL57871A			REMOVED MAGNETO DURING INSPECTION OF ROUGH ENGINE. FOUND BOTH CONTACT POINTS WORN, BOTH COILS CRACKED AT CENTER POST, L	EFT DISTRIBUTOR ARCED, IMPROPER LUBRICATION OF BEARINGS CAUSING GREASE TO BE SLUNG OUT, CAM LOBES HAVE VERY ROUGH FINISH	.				1	L	7	2 	3O	3	O		A29CE 	1E10				 
1995120100308	19951201	00308	SO 	1995	12	1	95ZZZX6409 	2	19951101	G	7414	6320	MAGNETO 			PIPER 	PA46 	PA46310P 	7104605	SO 	CONT 	O520 	TSIO520BE 	17040	SO 					LT/RT MAG	CORRODED 	B			DECR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	511PJ	144 				4608029	528437			REMOVED MAGS AND OPENED UP FOR CORROSION INSPECTION PER OWNER'S REQUEST. BOTH MAGS WERE FULL OF CORROSION OF ALL METAL 	SURFACES. MAGS WERE INSTALLED NEW 11/94 FOR SAME REASON. FILTERS CHANGED REGULARLY.					1	L	7	1 	3O	3	O		A25SO 	E8CE				 
1995120100309	19951201	00309	EA 	1995	12	1	95ZZZX6410 	2	19950928	G	8530	73806P	PUSHROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					NR 4 CYL INTAKE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	45905	1974 				15282942	L2321515			ANNUAL INSPECTION FOUND NR 4 INTAKE PUSHROD TO HAVE .75 INCH CRACK AT ROCKER ARM END. REFERENCE AD 80-25-02R2, AD 95-03	-10, LYCOMING SB 453 AND LYCOMING SI 2388A. PART TOTAL TIME, 1,973.6 HOURS.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995120100310	19951201	00310	GL 	1995	12	1	95ZZZX6411 	3	19951102	G	6114	D4239C50	HUB 			CESSNA	182 	182 	2072702	CE 						MCAULY	2A34C	2A34C50 	GL 	NR 1 SOCKET	CRACKED 	B			DJFR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23					733688			733688		DURING OVERHAUL, A CRACK WAS FOUND IN THREADS OF NR 1 BLADE SOCKET.						1	H	7	1 	3O			NT	3A13 		5	C	P3EA	 
1995120100311	19951201	00311	CE 	1995	12	1	95ZZZX6412 	1	19951003	G	8120	4708369018	CONTROLLER 			CESSNA	414 	414 	2075908	CE 	CONT 	O520 	TSIO520NB 	17040	SO 					LT ENG WASTEGATE	OIL LEAK 	B			SJ7R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	01	28901	329 			XI009705	4140353	290758R			WASTEGATE CONTROLLER OIL LEAKING FROM CENTER PISTON.						1	L	7	2 	3O	3	O	RT	A7CE 	E8CE				 
1995120100312	19951201	00312	SO 	1995	12	1	95ZZZX6413 	1	19950909	G	2913	T50P1H	POWER PACK 	ELECTROL 		PIPER 	PA23 	PA23250 	7102308	SO 										MLG	GEAR FAILED 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			EA	07	7074Z				2138	273094				MLG FAILED UPON LANDING DUE TO A GEAR FAILURE INTERNALLY IN THE HYD POWER PACK. THE MLG HAD FAILED TO FULLY DOWN AND LO	CK.					1	L	7	2 	3O				1A10 					 
1995120100313	19951201	00313	NM 	1995	12	1	95ZZZX6414 	1	19951018	G	7920	90024811	HOSE 			PIPER 	PA60 	PA60601P 	7106012	NM 										RT ENG OIL COOL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	07	60728					61P070079633				HOSE FOUND LEAKING INSIDE FIRE SLEEVE. WHEN REMOVED, THE HOSE WAS STIFF OR MORE RIGID THAN IT SHOULD HAVE BEEN. THIS H	OSE WAS AN AEROQUIP HOSE DATED 1Q92. HOSE APPEARED TO SUFFER PREMATURE AGING. HOSE HAD 259 HOURS WHEN REMOVED.					1	M	7	2 	3O			RT	A17WE 					 
1995120100314	19951201	00314	EA 	1995	12	1	95ZZZX6415 	2	19950914	G	8520	74667	CONNECT ROD 								LYC 	O320 	O320D2B 	41508	EA 					ENGINE	BOLTS CORRODED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	01							1509239			NEW BOLTS, TWO SETS. RECEIVING INSPECTION FOUND CONNECTING ROD BOLTS WITH CORROSION PRESENT.											3	O			E274				 
1995120100315	19951201	00315	SO 	1995	12	1	95ZZZX6416 	2	19951101	G	8520	6524201048	THROUGH BOLT 			PIPER 	PA34 	PA34200T 	7103406	SO 	CONT 	O360 	TSIO360EB 	17025	SO 					NR 2,3 CYLS BASE	BROKEN 	B			DECR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	19	2900D					347970341	307745			CRANKCASE 'THROUGH' BOLTS, UPPER AND LOWER FOR NR 2 AND NR 3 CYLINDERS, BROKEN AT CYLINDER BASE NUTS. LOCATED AFTER REP	ORTED OIL LEAK. ENGINE TT 3,816.90 HOURS. TSMOH, 535.63 HOURS.					1	L	7	2 	3O	3	O		A7SO 	E9CE				 
1995120100316	19951201	00316	SO 	1995	12	1	95ZZZX6417 	2	19951018	G	8530		ROCKER SHAFT 			PIPER 	PA28 	PA28RT201T 	7102817	SO 	CONT 	O360 	TSIO360FB 	17025	SO 					ENGINE	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	8277W	2413 	1305 			28R8131007	310841			DURING ROUTINE OIL CHANGE, OIL FILTER WAS FOUND CONTAMINATED WITH FERROUS MATERIAL. OIL ANALYSIS DETERMINED MATERIAL TO	 BE CASE HARDENED STEEL. UPON INSPECTION, FOUND SEVERE CORROSION IN CYLINDER WALLS, STARTER HOUSING, AND GEARS. ALSO, 	WORN ROCKER SHAFTS. ENGINE WAS THEN MAJOR OVERHAULED AND RETURNED TO SERVICE. CAUSE WAS NOT DETERMINED TO BE DUE TO IN	ACTIVE OPERATION. AIRCRAFT WAS STORED IN HANGAR HEATED TO APPROXIMATELY 40 DEGREES FAHRENHEIT WITH TANKS HEATER CONTINU	ALLY PLUGGED IN. POSSIBLE COMBINATION CAUSED CONDITIONS SUCH THAT CORROSION WOULD BE ACCELERATED.		1	L	7	1 	3O	3	O		2A13 	E9CE				 
1995120100317	19951201	00317	SW 	1995	12	1	95ZZZX6418 	1	19951031	G	2760		SPRING 			MOONEY	M20 	M20J 	5870219	SW 										RT SPEED BRAKE	BROKEN 	B		A	DY1R	O				OTHER 				F			FLT CONT AFFECTED 			CR	CRUISE 	1			EA	13	201SQ	255 				240298				WHILE USING SPEED BRAKES IN IMC CONDITION, PILOT REPORTED AIRCRAFT MADE HARD LEFT TURN. IT WAS LATER DETERMINED THE RET	URN SPRING DID NOT ALLOW THE SPEED BRAKE IN ONE WING TO FULLY RETRACT CAUSING THE TURN SITUATION. THE RETURN SPRING WAS	 BROKEN AND WOULD NOT ALLOW SPEED BRAKE RETRACTION (TO OFF, CLOSED POSITION) UNDER AIR-LOAD WITHOUT SPRING.				1	L	7	1 	3O				2A3 					 
1995120100318	19951201	00318	SW 	1995	12	1	95ZZZX6419 	1	19950811	G	5610	33792	WINDSHIELD 			SLINDS	100 	100180 	0140208	SW 										COCKPIT CENTER	DEPARTED 	G		A		A				UNSCHED LANDING 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			SO	05	4066X	2189 				5166				CENTER PORTION OF WINDSHIELD DEPARTED AIRCRAFT WHILE IN CRUISE FLIGHT. PILOT COULD NOT MAINTAIN ALTITUDE; EMERGENCY LAN	DING WAS MADE IN THE SALT MARSH. AIRCRAFT FLIPPED OVER UPON LANDING CAUSING SUBSTANTIAL DAMAGE.					1	H	7	1 	3O				1A21 					 
1995021000248	19950210	00248	SW 	1995	2	10	95ZZZX642 	1	19950116	G	3340	KIT38	MODULE 			MOONEY	M20 	M20E 	5870212	SW 										LIGHT FLASHER	OVERHEATED 	F		A		O				OTHER 				M	B		OVER TEMP 	SMOKE/FUMES/ODORS/SPARKS 		CR	CRUISE 	1			WP	27	55040	19 				605				DURING ROUTINE FLIGHT, SMOKE EMITTED FROM UNDER INSTRUMENT PANEL, NO FIRE. AIRCRAFT MADE SAFE LANDING, NO DAMAGE. INVE	STIGATION FOUND LANDING LIGHT FLASHER MODULE TO HAVE OVERHEATED. UNIT CONTINUED TO OPERATE NORMALLY, EXCEPT OVERHEATING	. TESTS ON MODULE SHOWED 1 OF 4 TRANSISTORS, PN IRFZ40, HAD FAILED AND CIRCUIT BOARD OVERHEATED. MANUFACTURE RECORDS 	SHOW MODULE PRODUCED IN BATCH NR 1. PRODUCT IMPROVEMENT CHANGE SUBMITTED TO FAA FOR APPROVAL TO IMPROVE HEAT-SINK AND A	DD THERMO FUSE TO POWER CIRCUIT TO PREVENT SMELL/SMOKE. SERVICE LETTER TO BE SENT TO ALL OWNER/OPERATORS. VNY MIDC ADV	ISED. STC SA5480NM.	1	L	7	1 	3O				2A3 					 
1995120100319	19951201	00319	GL 	1995	12	1	95ZZZX6420 	3	19951027	G	6114		HUB 													MCAULY	2A36C	D2A36C33 	GL 	DOWEL PIN HOLE	CRACKED 	B		A	FG6R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	07								60679		CUSTOMER COMPLAINED OF OIL ON WINDSHIELD. DISASSEMBLY OF PROPELLER REVEALED HUB CRACKED FROM DOWEL PIN TO CENTER HOLE I	N MOUNTING FLANGE. ALL INTERNAL PARTS AND BLADES SCRAP DUE TO RUST AND CORROSION. SUBMITTER STATED PROPELLER WAS WELL 	OVER 5 YEAR RECOMMENDED TBO.														5	C	P880	 
1995120100320	19951201	00320	EA 	1995	12	1	95ZZZX6421 	3	19951017	G	6114	A437	BUSHING 			UNIVAR	415 	415C 	0420302	NM 						SNSNCH	76A	76AK 	EA 	PROPELLER HUB	UNAPPROVED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	27	93990					1313				DURING ANNUAL INSPECTION, FOUND FUEL HOSE FABRICATED AS BUSHINGS AND INSTALLED IN PLACE OF NR A437 STEEL PROPELLER DOWEL	 BUSHINGS.					1	L	7	1 	3O				A718 		5	N	1P210	 
1995120100321	19951201	00321	CE 	1995	12	1	95ZZZX6422 	1	19950831	G	3233	12810012	ACTUATOR 			CESSNA	182 	TR182 	2072735	CE 										MLG	HOUSING CRACKED 	D		A		K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	07	6123T					R18201910				NOTED ON INSPECTION THAT LEFT MAIN GEAR ACTUATOR WAS LEAKING FLUID FROM ACTUATOR COVER PLATE. REMOVED ACTUATOR AND NOTE	D ROLLER BEARING BACKED OUT FROM BEARING BOSS. FURTHER INSPECTION REVEALED CRACK IN HOUSING ASSY AT LOWER BEARING BOSS 	AND EXTENDING THROUGH ACTUATOR HOUSING. MISALIGNED ROLLER FROM ACTUATOR PISTON CAUSED HOUSING SCORING AND PISTON SCORIN	G AS WELL AS CRACKED HOUSING.			1	H	7	1 	3O				3A13 					 
1995120100322	19951201	00322	EU 	1995	12	1	95ZZZX6423 	1	19951025	G	2520	104022070009	SEAT BELT ASSY 			SOCATA	TB20 	TB21 	8680697	EU 										EYE END LT	CORRODED 	B		A	FE6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	20DV	1559 			430	612				WHILE PERFORMING MANDATORY SB 10-044, AMDT 1, DATED SEPT 1993 (DUE AT EACH ANNUAL INSPECTION), IT WAS NOTED THE LEFT AND	 RIGHT INERTIA REEL-TYPE FRONT SEAT BELTS HAVE SEVERE EXFOLIATION CORROSION ON THE EYE END THAT ATTACHES TO THE FORWARD 	OUTBOARD FUSELAGE STRUCTURE. THE SB CALLS FOR CHECKING FOR OXIDATION OR EXFOLIATON CORROSION SO THE MFG IS AWARE OF THE	 PROBLEM. EYE END IS OF AN ALUMINUM MATERIAL WHEREIN MOST U. S. MANUFACTURED SEAT BELTS HAVE STEEL EYE ENDS. SEAT BELT	 EYE ENDS TO BE REPLACED.		1	L	7	1 	3O			RT	A51EU 					 
1995120100323	19951201	00323	EU 	1995	12	1	95ZZZX6424 	1	19951025	G	2520	104022070009	SEAT BELT ASSY 			SOCATA	TB20 	TB21 	8680697	EU 										EYE END RT	CORRODED 	B			FE6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	20DV	1559 			499	612				WHILE PERFORMING MANDATORY SB 10-044, AMDT 1, DATED SEPT 1993 (DUE AT EACH ANNUAL INSPECTION), IT WAS NOTED THE LEFT AND	 RIGHT INERTIA REEL-TYPE FRONT SEAT BELTS HAVE SEVERE EXFOLIATION CORROSION ON THE EYE END THAT ATTACHES TO THE FORWARD 	OUTBOARD FUSELAGE STRUCTURE. THE SB CALLS FOR CHECKING FOR OXIDATION OR EXFOLIATON CORROSION SO THE MFG IS AWARE OF THE	 PROBLEM. EYE END IS OF AN ALUMINUM MATERIAL WHEREIN MOST U. S. MANUFACTURED SEAT BELTS HAVE STEEL EYE ENDS. SEAT BELT	 EYE ENDS TO BE REPLACED.		1	L	7	1 	3O			RT	A51EU 					 
1995120800094	19951208	00094	NM 	1995	12	8	95ZZZX6427 	1	19951001	G	5313		LONGERON 			CHILD 	S2 	S2BPITTS 	0110304	NM 										UPPER RT FUSE	CRACKED 	G		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	6068V					5198				DURING ROUTINE MAINTENANCE, A AND P MECHANIC FOUND UPPER RT FUSELAGE LONGERON CRACKED COMPLETELY THROUGH. AIRFRAME AT 7	26 HOURS SINCE NEW. THIS WAS BROUGHT TO THE ATTENTION OF ASI. SAFETY RECOMMENDATION WAS SENT TO AAI-200 ON 10-27-5.					1	Q	7	1 	3O				A8SO 					 
1995120800095	19951208	00095	SW 	1995	12	8	95ZZZX6428 	1	19951101	G	5541	442283	SPAR 			GULSTM	112 	114 	7630314	SW 										RUDDER	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	5804N	3324 				14372				RUDDER SPAR CRACKED UNDER UPPER HINGE AND PROTRUDED PAST HINGE. CRACK RAN ALONG THE SIDE OF SHIM, PN 40113-3. SL-114-1	7 ADDRESSES THIS PROBLEM.					1	L	7	1 	3O				A12SO 					 
1995120800096	19951208	00096	CE 	1995	12	8	95ZZZX6429 	1	19951001	G	3213	22411001	FITTING 			CESSNA	182 	R182 	2072734	CE 										RT MLG SPRING	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	6465T	2128 				R18202033				FAILED FITTING IS USED TO ATTACH THE RIGHT MAIN GEAR SPRING TUBE TO THE AXLE. ON ANNUAL INSPECTION, FOUND A ONE INCH CR	ACK PARALLEL TO TUBE STARTING ON THE BOTTOM OF THE MACHINED HOLE THAT THE SPRING TUBE GOES INTO. IT APPEARS THAT CRACK 	HAPPENED BECAUSE OF DISSIMILAR METAL CORROSION. RUST ON STEEL TUBE EXPANDED AND CRACKED ALUMINUM FITTING. SUBMITTER ST	ATED COULD BE STOPPED BY USING ZINC CHROMATE AND SEALING SURFACES.			1	H	7	1 	3O			RT	3A13 					 
1995021000249	19950210	00249	SW 	1995	2	10	95ZZZX643 	1	19950116	G	3340	KIT138	MODULE 			MOONEY	M20 	M20F 	5870214	SW 										LIGHT FLASHER	OVERHEATED 	F				K				NONE 				M	B		OVER TEMP 	SMOKE/FUMES/ODORS/SPARKS 		IN	INSP/MAINT 	1			WP	27	6937V	18 				221310				DURING ROUTINE FLIGHT, SMOKE EMITTED FROM UNDER INSTRUMENT PANEL, NO FIRE. A/C MADE SAFE LANDING, NO DAMAGE. INVESTIGA	TION FOUND LANDING LIGHT FLASHER MODULE TO HAVE OVERHEATED AND HAD 30 AMP FUSE (S/B 20 AMP). A/C RECORDS INDICATED RADI	O REPAIR WORK PRIOR TO THIS FLIGHT. UNIT CONTINUED TO OPERATE NORMALLY, EXCEPT OVERHEATING. TESTS ON MODULE SHOWED 1 O	F 4 TRANSISTORS, PN IRFZ40, HAD FAILED AND CIRCUIT BOARD OVERHEATED. MFG RECORDS SHOW MODULE PRODUCED IN BATCH NR 1. P	RODUCT IMPROVEMENT CHANGE SUBMITTED TO FAA FOR APPROVAL TO IMPROVE HEAT-SINK AND ADD THERMO FUSE IN POWER CIRCUIT TO PRE	VENT SMELL/SMOKE. SERVICE LETTER TO BE SENT TO ALL OWNER/OPERATORS VNY MIDO NOTIFIED. TC SA5480NM.	1	L	7	1 	3O				2A3 					 
1995120800097	19951208	00097	CE 	1995	12	8	95ZZZX6430 	1	19951023	G	2121	HE812933	BLOWER 		HE813003 	CESSNA	340 	340A 	2076405	CE 										AIR COND EVAP	MOTOR FAILED 	B			ITWR	O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			NM	07	6311X				8316	340A0482				AIR CONDITIONING BLOWER FAN MOTOR FIELD WINDING SHORTED AND BURNED UNDER AIR CONDITIONER MODE OPERATION. AIRCRAFT WAS I	N-FLIGHT AT THE TIME, AND SMOKE ENTERED THE CABIN THROUGH THE CABIN 'WEMAC' OUTLETS FOR A/C AIR. WHILE TOTAL TIME OF TH	IS COMPONENT IS UNKNOWN, THE LENGTH OF THE ARMATURE BRUSHES WOULD INDICATE THIS ITEM'S FAILURE WAS IMMINENT.				1	L	7	2 	3O				3A25 					 
1995120800098	19951208	00098	CE 	1995	12	8	95ZZZX6431 	1	19951102	G	5312	07126161	BULKHEAD 			CESSNA	182 	182H 	2072718	CE 										LT RUDDER STOP	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	8572S	3700 				18256672				DURING AN ANNUAL INSPECTION, THE BULKHEAD WAS FOUND CRACKED. ACCORDING TO CESSNA' C.A.P. FOR 100 SERIES AIRCRAFT, THIS 	IS A CRUCIAL PART OF A GOOD INSPECTION. SUBMITTER STATED IT IS ALSO NOTEWORTHY THAT BECAUSE THE AD ON THE SUBJECT TALKS	 MORE SPECIFICALLY ABOUT NUTPLATES AND BOLT HOLES THAT CESSNA HAS MULTIPLE SERVICE BULLETINS ON THE SUBJECT THAT ALSO IN	CLUDES SEVERAL 100 SERIES AIRCRAFT.			1	H	7	1 	3O			NT	3A13 					 
1995120800099	19951208	00099	SO 	1995	12	8	95ZZZX6432 	1	19951103	G	2913	11200302	SWITCH 	PARKERHANFIN	256A 	PIPER 	PA46 	PA46310P 	7104605	SO 										POWER PACK	FAILED 	B			LF1R	O				OTHER 				O			OTHER 			CL	CLIMB 	1			EA	07	9125R	4 				4608091				OWNER STATED GEAR WOULD NOT RETRACT. PLACED AIRCRAFT ON JACKS, TROUBLESHOT SYSTEM AND FOUND 'UP' PRESSURE SWITCH INOP. 	 SWITCH HAD BEEN INSTALLED 4.0 HOURS EARLIER. THIS SWITCH WAS LATEST STYLE IAW PIPER SB 98. ACCORDING TO MANUFACTURER,	 NEW SWITCHES ARE BEING DESIGNED. THERE ARE TWO OF THESE SWITCHES INSTALLED. FAILURE OF DOWN SWITCH WOULD PREVENT NORM	AL EXTENSION OF LANDING GEAR.			1	L	7	1 	3O				A25SO 					 
1995120800100	19951208	00100	CE 	1995	12	8	95ZZZX6433 	1	19951109	G	2752		FLAP MOTOR 			CESSNA	172 	172M 	2072418	CE 										FLAP CONTROL	BAD GROUND 	D				O				OTHER 				F	B		FLT CONT AFFECTED 	SMOKE/FUMES/ODORS/SPARKS 		TX	TAXI/GRND HDL 	1			NE	05	1393U	5550 				17267064				WHILE CLEARING THE RUNWAY AFTER TRAINING FLIGHT, FLAPS WERE SELECTED UP. THE FLAPS FAILED TO OPERATE AND THE FLIGHT CRE	W REPORTED SMELLING 'SMOKE'. INVESTIGATION REVEALED A BAD GROUND ON THE FLAP MOTOR AND THE ALTERNATOR CIRCUIT BREAKER W	AS FOUND DAMAGED BY HEAT. WITH THE FULL LOAD OF LIGHTS, AVIONICS AND THE ADDITIONAL LOAD OF THE IMPROPERLY OPERATING FL	APS, THE CIRCUIT BREAKER GOT HOT ENOUGH TO DEFORM, BUT DID NOT 'POP'. REPAIRED FLAP WIRING AND REPLACED CIRCUIT BREAKER	. SYSTEMS OPERATE NORMALLY.		1	H	7	1 	3O			NT	3A12 					 
1995120800101	19951208	00101	CE 	1995	12	8	95ZZZX6434 	1	19951010	G	3250	16981001127	HOUSING 			BEECH 	23 	C23 	1151242	CE 										NLG STEERING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	18931	2542 				B1995				FOUND THE HOLE THAT MOUNTS THE STEERING COLLAR AND SUPPORT BEARING HAS CRACKS COMING FROM EDGE.						1	L	7	1 	3O				A1CE 					 
1995120800102	19951208	00102		1995	12	8	95ZZZX6435 	4	19951108	G	6122	A20734	FLYWEIGHT 			CESSNA	402 	402C 	207590R	CE 										PROPELLER GOV	BASE CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	88TN	4527 			810776	402C0621				PROPELLER GOVERNOR FLYWEIGHT BASE CRACKED.						1	L	7	2 	3O				A7CE 					 
1995120800103	19951208	00103	NM 	1995	12	8	95ZZZX6436 	1	19950622	G	3231	D61C065AR	WHEEL BAIL CABLE			PROPJT	200 	200A 	0140304	NM 										RT WELL INB DOOR	ATTACH INCORRECT	B			FTUR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	05	492C					256				RIGHT GEAR, INBOARD DOOR WHEEL BAIL CABLE ATTACH POINT INSTALLED IN THE WRONG POSITION. ATTACH POINT WAS LOCATED ON THE	 TOP OF THE BAIL APPROXIMATELY 2 INCHES FORWARD OF THE AFT CORNER. PROPER POSITION SHOULD BE APPROXMATELY AT THE AFT CO	RNER.				1	L	7	1 	3O				3A18 					 
1995120800104	19951208	00104	CE 	1995	12	8	95ZZZX6437 	1	19950831	G	3233	12810012	HOUSING 			CESSNA	172 	172RG 	2072438	CE 										MLG ACTUATOR	CRACKED 	D				O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			WP	07	172CM					172RG0787				DURING FLIGHT AND GEAR-UP, ONE GEAR WOULD NOT FULLY RETRACT. INSPECTION REVEALED MAIN LANDING GEAR ASSY HOUSING CRACKED	 FORWARD OF PISTON ROLLER BOSS. SUBMITTER STATED THIS CONDITION WAS NOTED ON TWO OTHER AIRCRAFT IN THIS FLEET, ALL CESS	NA 172RG.				1	H	7	1 	3O				3A17 					 
1995120800105	19951208	00105	CE 	1995	12	8	95ZZZX6438 	1	19950925	G	5511	05320019	SPAR ASSY 			CESSNA	172 	172D 	2072410	CE 										HORIZONTAL STAB	CRACKED 	B			AJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	2057Y	3865 				49557				FOUND 2 CRACKS AT LIGHTENING HOLE IN CENTER SECTION OF FRONT SPAR AND REINFORCEMENT SPAR OF HORIZONTAL STABILIZER. SUSP	ECT CAUSE - IMPROPER GROUND HANDLING. RECOMMENDATION - USE TOW BAR.					1	H	7	1 	3O			NT	3A12 					 
1995120800106	19951208	00106	CE 	1995	12	8	95ZZZX6439 	1	19950925	G	5510	053200111	SPAR ASSY 			CESSNA	172 	172D 	2072410	CE 										HORIZONTAL STAB	CRACKED 	B			AJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	2057Y	3865 				49557				FOUND 2 CRACKS AT LIGHTENING HOLE IN CENTER SECTION OF FRONT SPAR AND REINFORCEMENT SPAR OF HORIZONTAL STABILIZER. SUSP	ECT CAUSE - IMPROPER GROUND HANDLING. RECOMMENDATION - USE TOW BAR.					1	H	7	1 	3O			NT	3A12 					 
1995021000250	19950210	00250	SO 	1995	2	10	95ZZZX644 	1	19950106	G	5730	62061004	SKIN 			PIPER 	PA28 	PA28181 	7102807	SO 										RT WING WALKWAY	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	6912D	8643 				288590052				RIGHT WING WALKWAY HAD A SPONGY FEEL IN AREA THAT IS STEPPED ON, OFF OF STEP. INSPECTION OF LOWER PANEL THROUGH INSPECT	ION PANELS, CRACKS WERE VISIBLE ON INBOARD CORRIGATIONS AND RADIUS (NEXT TO FIRST RIB). TIN-CANNING EFFECT OF STEPPING 	ON WALKWAY ON SAME SPOT SUSPECTED AS CAUSE. NO RECOMMENDATIONS TO PREVENT RECURRENCE. TEN OF 12 CORRIGATIONS HAD CRACK	S. SAME MODEL AIRCRAFT HAD FORWARD AND AFT PANELS CRACKED AND REPLACED IN 1994. BOTH AIRCRAFT ARE USED IN FLIGHT TRAIN	ING. FAILED PARTS BEING KEPT FOR SIX MONTHS.		1	L	7	1 	3O				2A13 					 
1995120800107	19951208	00107	CE 	1995	12	8	95ZZZX6440 	1	19950927	G	5511	053200198	SPAR ASSY 			CESSNA	172 	172N 	2072434	CE 										HORIZ STABILIZER	CRACKED 	B			AJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	4QQ	3319 				17272542				FOUND 3 CRACKS AT LIGHTENING HOLE IN FRONT SPAR OF HORIZONTAL STABILIZER (CENTER SECTION), APPROXIMATELY .75 INCH EACH. 	 SUSPECT CAUSE - IMPROPER GROUND HANDLING. RECOMMENDATION - USE TOW BAR.					1	H	7	1 	3O			NT	3A12 					 
1995120800108	19951208	00108	CE 	1995	12	8	95ZZZX6441 	1	19950927	G	5511	053200197	SPAR 			CESSNA	172 	172N 	2072434	CE 										HORIZ STABILIZER	CRACKED 	B			AJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	4QQ	3319 				17272542				FOUND 3 CRACKS AT LIGHTENING HOLE IN FRONT SPAR OF HORIZONTAL STABILIZER (CENTER SECTION), APPROXIMATELY .75 INCH EACH. 	 SUSPECT CAUSE - IMPROPER GROUND HANDLING. RECOMMENDATION - USE TOW BAR.					1	H	7	1 	3O			NT	3A12 					 
1995120800109	19951208	00109	CE 	1995	12	8	95ZZZX6442 	1	19951010	G	3250	16981001127	HOUSING 			BEECH 	23 	C23 	1151242	CE 										NLG STEERING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5107M	3930 				M2027				FOUND THE HOLES THAT MOUNT THE STEERING COLLAR AND SUPPORT BEARING HAVE CRACKS COMING FROM THEM.						1	L	7	1 	3O				A1CE 					 
1995120800110	19951208	00110	SO 	1995	12	8	95ZZZX6443 	1	19951023	G	2910	4085400	LINE 			PIPER 	PA31 	PA31350 	7103110	SO 										PUMP CK VALVE	CRACKED 	B		A	JUJR	O				OTHER 				K			FLUID LOSS 			AP	APPROACH 	1			SO	07	885HA					317405416				HYDRAULIC PRESSURE LINE FROM RESERVOIR TO HAND PUMP CHECK VALVE WAS FOUND BROKEN AT CHECK VALVE FLARE NUT. THE BREAK AT	 THIS POINT CAUSED THE RESERVOIR TO EMPTY AND THE HAND PUMP TO BE INOPERATIVE. THE LINE WAS PROPERLY INSTALLED, AND HAD	 NO SIGNS OF STRESS OR DAMAGE.				1	L	7	2 	3O				A20SO 					 
1995120800111	19951208	00111	CE 	1995	12	8	95ZZZX6444 	1	19951003	G	7603	98630561	CONTROL CABLE 			CESSNA	150 	152 	2071835	CE 										THROTTLE CONTROL	FAILED 	B	P		LE6R	A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			WP	09	5447L	1311 				15284317				PILOT REPORTED POWER HAD BEEN REDUCED TO DESCEND, AND THAT IT WAS NOT POSSIBLE TO RESTORE ENGINE POWER; MOVEMENT OF THE 	THROTTLE YIELDED NO CHANGE IN ENGINE POWER. AN OFF-AIRPORT LANDING OCCURRED. THE AIRPLANE WAS NOT DAMAGED DURING THE LA	NDING ON A DRY DESERT LAKE BED/SALT FLAT, BUT CLIMATIC CONDITIONS AT THE LANDING SITE CAUSED SUBSTANTIAL CORROSION DAMAG	E TO LANDING GEAR COMPONENTS. AN INVESTIGATION REVEALED THE THROTTLE CONTROL CABLE WAS BROKEN JUST BEHIND THE THREADED 	PORTION WHICH ENGAGES THE SPHERICAL ROD END AT THE THROTTLE CONTROL ARM ON THE CARBURETOR.		1	H	7	1 	3O			NT	3A19 					 
1995120800112	19951208	00112	CE 	1995	12	8	95ZZZX6445 	1	19951102	G	2820	S14956	HOSE 			CESSNA	182 	R182 	2072734	CE 										FUEL SYSTEM	LEAKING 	D		A		K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	01	4649T	2583 				R18201724				HOSE USED AS COUPLING BETWEEN RIGID FUEL LINES MADE OF ALUMINUM TUBING, FOUND BADLY DETERIORATED AND LEAKING FUEL. THIS	 LINE IS LOCATED AT PILOT'S WINDSHIELD POST AND LINE IS ROUTED ALONG WITH ELECTRICAL WIRING. ANY SPARKS COULD RESULT IN	 A VERY SERIOUS CONDITION. (PARTS CATALOG, FIGURE 96A, SHEETS 1 AND 2.)				1	H	7	1 	3O			RT	3A13 					 
1995120800113	19951208	00113	SO 	1995	12	8	95ZZZX6446 	1	19951030	G	3243	1030	MASTER CYLINDER 	PARKERHANFIN		PIPER 	PA28 	PA28161 	7102803	SO 										PILOT RT BRAKE	FAILED 	B			AD4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	6909T	1500 				288516049				STUDENT PILOT STATED THAT RIGHT RUDDER PEDAL BROKE (ON START-UP). CHECKED TO FIND THE RIGHT PILOT'S MASTER CYLINDER HAD	 BROKEN. ALL HYDRAULIC FLUID WAS GONE AND RIGHT RUDDER PEDAL WAS AT 90 DEGREE ANGLE. THE PISTON ROD HAD COME OUT OF TH	E UNIT BECAUSE OF A BROKEN SNAP RING.				1	L	7	1 	3O				2A13 					 
1995120800114	19951208	00114	NE 	1995	12	8	95ZZZX6447 	3	19951018	G	6114	51459	SPIDER 			SCWZER	G164 	G164 	3952702	EA 						HAMSTD	2D	2D30 	NE 	PROPELLER	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17								P9886		INSPECTION FOUND PROPELLER SPIDER ARM CRACKED.						1	Q	7	1 	3R				1A16 		5	C	P206	 
1995120800115	19951208	00115	NE 	1995	12	8	95ZZZX6448 	3	19951018	G	6114	S8462	BARREL HALF 			SCWZER	G164 	G164 	3952702	EA 						HAMSTD	2D	2D30 	NE 	PROPELLER	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17								P9886		INSPECTION FOUND PROPELLER BARREL HALVES CRACKED AT INNER RADIUS WHERE BLADE IS RETAINED.						1	Q	7	1 	3R				1A16 		5	C	P206	 
1995120800116	19951208	00116	NE 	1995	12	8	95ZZZX6449 	3	19950929	G	6114	51430	COUNTERWEIGHT 			SCWZER	G164 	G164 	3952702	EA 						HAMSTD	12D	12D40 	NE 	PROPELLER	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17		530 						76274		INSPECTION FOUND COUNTERWEIGHT ARM CRACKED WHERE THE KIDNEY BEARING IS INSTALLED.						1	Q	7	1 	3R				1A16 		5	C	P257	 
1995021000251	19950210	00251	CE 	1995	2	10	95ZZZX645 	1	19950113	G	7603	5038901229	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										RT THROTTLE	BROKEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	1888W	109 				TH340				THROTTLE AND MIXTURE CONTROL CABLES ARE BREAKING AT THE THREADED END WHERE THE CABLE ATTACHES TO THREADED PORTION OF CAB	LE. THIS HAS OCCURRED 11 TIMES ON THIS AIRCRAFT SINCE MAY, 1994. SUBMITTER STATED THAT BEECH AIRCRAFT HAS BEEN NOTIFIE	D OF PROBLEM, WITH NO RESULTS AS OF THIS DATE.				1	L	7	2 	3O			 	3A16 					 
1995120800117	19951208	00117	SO 	1995	12	8	95ZZZX6450 	2	19951031	G	8530	649317A1	CYLINDER 			CESSNA	207 	T207 	2073612	CE 	CONT 	O520 	TSIO520G 	17040	SO 					NR 6	DEPARTED 	D				O				OTHER 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			AL	05	91029		243 			T20700020	507005			NR 6 CYLINDER DEPARTED THE CASE. ALL THE CYLINDER BASE STUDS WERE BROKEN.						1	H	7	1 	3O	3	O		A16CE 	E8CE				 
1995120800118	19951208	00118	EA 	1995	12	8	95ZZZX6451 	1	19951113	G	4980	38460272	CLAMP 		GTCP36100E 	CNDAIR	CL600 	CL6001A11 	1900302	EA 										APU VLV EXHAUST	FAILED 	H	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	914X				P213	1021				DURING POST-FLIGHT OF APU OIL, FOUND MANY SMALL SECTIONS OF SS FOIL EMBOSSED LINER LAYING ON FLOOR OF APU ENCL. REMOVED	 COVER ASSY & FND CLAMP ASSY THAT HOLDS SURGE VALVE EXHAUST AIR TO EXH DUCT BROKEN AT WELD ON THE CLAMP. THIS CAUSED HO	T EXHAUST GASSES TO HIT DIRECTLY ON APU ENCL BOX & NOT EXHAUST OVERBOARD. THIS THEN CAUSED SS FOIL MATERIAL TO BURN OFF	 & ALSO PULL AWAY FROM APU ENCL STRUCTURE ON THE COMPLETE RT SIDEWALL & ONE-THIRD OF FWD RT SECTION OF THE WALL. IF THI	S WAS NOT FOUND, NEXT APU START WOULD HAVE CAUSED A BURN-THROUGH OF APU ENCLOSURE & POSSIBLY OTHER STRUCTURAL DAMAGE. N	OTE: ALLIED SIGNAL HAS SB ISSUED TO CORRECT PROBLEM, SB GTCP 36-49-6093. DID NOT HAVE THIS INSTALLED AT THE TIME.	2	L	7	2 	4F			RT	A21EA 					 
1995120800119	19951208	00119	CE 	1995	12	8	95ZZZX6452 	1	19951031	G	5712	00011013321	RIB 			BEECH 	200 	200BEECH 	1152920	CE 										LT WING	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	630DB					BB187				SCHEDULED INSPECTION FOUND BOTH LEADING EDGE RIBS ARE CRACKED. MOUNT SCREWS ARE TIGHT. LEFT WING PREVIOUSLY REPAIRED B	Y DOUBLER ON SKIN. BOTH RIBS HAVE ABOUT 4,000 HOURS SINCE LAST REPLACEMENT.					1	L	7	2 	4T				A24CE 					 
1995120800120	19951208	00120	CE 	1995	12	8	95ZZZX6453 	1	19951031	G	5712	00011013322	RIB 			BEECH 	200 	200BEECH 	1152920	CE 										RT WING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	630DB					BB187				SCHEDULED INSPECTION FOUND BOTH LEADING EDGE RIBS ARE CRACKED. MOUNT SCREWS ARE TIGHT. LEFT WING PREVIOUSLY REPAIRED B	Y DOUBLER ON SKIN. BOTH RIBS HAVE ABOUT 4,000 HOURS SINCE LAST REPLACEMENT.					1	L	7	2 	4T				A24CE 					 
1995120800121	19951208	00121	SO 	1995	12	8	95ZZZX6454 	1	19951007	G	2820	5764605	LINE 			PIPER 	PA42 	PA42720 	7104212	SO 										NAC TO WING ROOT	CHAFED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	9279A					425501036				REMOVED INBOARD LEADING EDGE AND FOUND FUEL LINE CHAFING AGAINST ANCHOR NUT FOR LEADING EDGE SCREWS AT NACELLE. ALSO, F	OUND CHAFING AT FUEL LINE B-NUT AND THE BUTT OF A HYLOCK ALL IN THE SAME AREA INSIDE THE NACELLE WHERE THE LEADING EDGE 	ATTACHES TO THE WING. CHAFING WAS NOT APPARENT DUE TO THE AMOUNT OF FUEL AND HYDRAULIC LINES IN THE VERY SMALL AND TIGH	T AREA. RECOMMEND VERY CLOSE INSPECTION OF THIS AREA.			1	L	7	2 	4T				A23SO 					 
1995120800122	19951208	00122	CE 	1995	12	8	95ZZZX6455 	1	19951004	G	2150	113622	COMPRESSOR 			BEECH 	B300 	B300 	1159232	CE 										AIR CONDITIONER	CLUTCH FAILED 	B		A	VIBR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	13	305RL	84 			082642	FL10				CATASTROPHIC FAILURE OF THE AIR CONDITIONER COMPRESSOR CLUTCH RESULTED IN DAMAGE TO THE ENGINE MOUNT. THE ENGINE MOUNT 	WAS SEVERELY DENTED AS A RESULT OF METAL FRAGMENT FROM THE CLUTCH HITTING THE ENGINE MOUNT DIAGONAL TUBE MEMBER. THE EN	GINE MOUNT REQUIRES MAJOR REPAIR DUE TO THIS DAMAGE.				2	L	7	2 	4T			RT	A24CE 					 
1995120800123	19951208	00123	CE 	1995	12	8	95ZZZX6456 	1	19951021	G	7170	476284	PUMP ASSY 			BEECH 	200 	200BEECH 	1152920	CE 										FUEL DRAIN	CORRODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	50LT	6947 				BB284				DUE TO THE HORIZONTAL POSITION OF FUEL DRAIN PUMP ASSEMBLY, WATER COLLECTS AT BOTTOM OF FILTER AREA CAUSNG CORROSION. D	ISCOVERED DURING ROUTINE INSPECTION OF FILTER. MAYBE A DRAIN OR REPOSITIONING THE PUMP WITH A DRAIN IN COVER.					1	L	7	2 	4T				A24CE 					 
1995120800125	19951208	00125	NE 	1995	12	8	95ZZZX6458 	3	19950920	G	6111	E10950K	BLADE 			BEECH 	1900 	1900D 	1154162	CE 						HARTZL	HCE4A	HCE4A3A 	NE 	LEADING EDGE	DEBONDED 	B		A	LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17		1925 						HJ86		FOUND LEADING EDGE OF COMPOSITE BLADE DEBONDED UNDER DEICE BOOT.						2	L	7	2 	4T			RT	A24CE 		5	C	P10NE	 
1995120800126	19951208	00126	SW 	1995	12	8	95ZZZX6459 	1	19951010	G	3610	88026737	LINE 			GULSTM	690TP 	690A 	0141722	SW 										BLEED SYSTEM	DEFECTIVE 	B		A	DJFR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	690HF	5636 				11298				DURING C/W SL 327, NOTED AFT FLARE ON BLEED LINE HAD ALMOST COMPLETELY WORN AWAY. PART WAS VERY CLOSE TO FAILURE WHICH 	WOULD HAVE RESULTED IN LARGE BLEED AIR LEAK IN AFT AVIONICS BAY. SUBMITTER RECOMMENDS SB 327 BE C/W ON ALL AFFECTED AIR	CRAFT.				1	H	7	2 	3T				2A4 					 
1995120800127	19951208	00127	CE 	1995	12	8	95ZZZX6460 	1	19950904	G	3246	A9541624	WHEEL ASSY 			RKWELL	NA265 	NA26560 	7630106	CE 										NLG	RIM BOLTS LOOSE 	H				K				NONE 				E			VIBRATION/BUFFET 			TO	TAKEOFF 	1			WP	01	2MIL					30666				NOSE WHEEL ASSY VIBRATED DURING ROUTINE TAKEOFF. WHILE ON GROUND, NOSE WHEEL ASSY WAS INSPECTED AND 2 RIM RETAINING BOL	TS WERE FOUND LOOSE. TIRE WAS DEFLATED AND ALL RIM RETAINING BOLTS WERE FOUND LOOSE. THIS UNIT WAS OVERHAULED BY SABRE	 LINER ON 11-2-94, ORDER NR 42522, 119.6 HOURS ON UNIT. SUBMITTER SUGGESTS ALL NOSE WHEEL ASSYS OVERHAULED BY SABRE LIN	ER DURING THIS PERIOD BE INSPECTED FOR NOTED CONDITION. NOTE: US NAVY AIRCRAFT MAINTAINED UNDER CIVILIAN MAINTENANCE P	ROGRAM.		2	L	7	2 	4J			RT	A2WE 					 
1995120800129	19951208	00129	EU 	1995	12	8	95ZZZX6462 	1	19951024	G	2910	HTE4350	VALVE 			HWKSLY	DH125 	BH125400A 	4230138	EU 										RT HYD SYSTEM	FAILED 	D				K				NONE 				B	K		SMOKE/FUMES/ODORS/SPARKS 	FLUID LOSS 		NR	NOT REPORTED 	1			SW	99	72HC					NA780				HYDRAULIC FLUID FLOWED FROM RESERVOIR TO BLEED AIR SYSTEM THROUGH RT PRESSURE SOURCE LINE. SUSPECT HYDRAULIC FLUID FLOW	 INTO BLEED AIR SYSTEM CAUSED BY INITIAL FLOW OF AIR IN SYSTEM. NON-RETURN VALVE IN PRESSURE SOURCE LINE INSTALLED TO P	REVENT THIS REVERSE FLOW. FAILURE RESULTED IN SEVERE CONTAMINATION OF BLEED AIR SYSTEM WITH HYDRAULIC FLUID CAUSING SMO	KE IN COCKPIT CABIN. SUBMITTER STATED NO REFERENCE TO THESE NON-RETURN VALVES NOTED IN AIRFRAME MAINTENANCE SCHEDULE FO	R INSPECTION, TESTING, OR REPLACEMENT. RECOMMEND REGULAR INTERVAL FOR TESTING BE ESTABLISHED.		2	L	7	2 	4J				A3EU 					 
1995120800130	19951208	00130	CE 	1995	12	8	95ZZZX6463 	1	19951020	G	2140	66004238	MOTOR 			LEAR 	55 	55LEAR 	5170702	CE 										TEMP CONTROL	FAILED 	D				O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			NE	05	100VA					029				AFT DUCT OVERHEAT LIGHT ILLUMINATED IN LEVEL FLIGHT. FOUND TEMP CONTROL VALVE TORQUE MOTOR FAILED IN HOT POSITION.						2	L	7	2 	4F				A10CE 					 
1995120800131	19951208	00131	CE 	1995	12	8	95ZZZX6464 	1	19951102	G	2435	03601014	BEARING 	LUCAS 	23080050 	BEECH 	MU300 	400BEECH 		CE 										START/GEN	FAILED 	B			KC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	31967	837 			94234	RK96				STARTER/GENERATOR UNIT RECEIVED FOR OVERHAUL. PIECES OF BEARING RETAINER FELL OUT OF UNIT. FOUND THAT COMMUTATOR END B	EARING HAD FAILED AND DRIVE END BEARING WAS VERY ROUGH FEELING.					2	H	7	2 	4F			RT	A16SW 					 
1995120800132	19951208	00132	EA 	1995	12	8	95ZZZX6465 	2	19951001	G	7321	DPF2	FUEL CONTROL 	BENDIX 		PIPER 	PA31T 	PA31T 	7103124	SO 	PWA 	PT6 	PT6A28 		EA 					FCU TO PUMP	SHAFT BROKEN 	B			DDNR	E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	27	29CA				A7784	317T78120076				AIRCRAFT WAS CRUISING AT 20,000 FEET AND PILOT NOTICED ITT, NG, AND FUEL FLOW RISE DRAMATICALLY. TRIED TO PULL POWER BA	CK, BUT HAD NO CONTROL OVER ENGINE WITH POWER LEVER. ENGINE WAS SHUT DOWN IN-FLIGHT. FOUND FCU TO FUEL PUMP INTERCONNE	CT SHAFT BROKEN. FUEL CONTROL UNIT SHAFT WAS SEIZED.				1	L	7	2 	3T	4	T		A8EA 	E4EA				 
1995120800134	19951208	00134	CE 	1995	12	8	95ZZZX6467 	1	19951012	G	2842	100380006169	PROBE 			BEECH 	200 	B200 	1152922	CE 										LT OTBD AUX	DEFECTIVE 	B			VIBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	6789					B1382				FUEL TRANSMITTER PROBE HAS LOW RESISTANCE BETWEEN SIGNAL AND RETURN. PART INSTALLED AND CHECKED SATISFACTORY 9-21-95. P	ILOT REPORTED PROBLEM 10-12-95, WHEN TAKING AIRCRAFT FOR TEST FLIGHT, AIRCRAFT HAD NO FUEL ADDED TO AUXILIARY TANKS. PA	RT WAS REPLACED BEFORE TEST FLIGHT. SUBMITTER STATED THIS SAME PROBLEM OCCURRED 3 TIMES IN 10 MONTHS.				1	L	7	2 	4T				A24CE 					 
1995120800135	19951208	00135	CE 	1995	12	8	95ZZZX6468 	1	19951031	G	2460	727725	BREAKER 			BEECH 	200 	200BEECH 	1152920	CE 										LT/RT SIDE	STUCK 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	630DB	7746 				BB187				SCHEDULED INSPECTION FOUND CIRCUIT BREAKERS LOCATED BY INVERTERS, BOTH SIDES ARE STUCK AND CANNOT BE PULLED, 3 OUT OF 4 	BREAKERS STUCK. REPLACED CIRCUIT BREAKERS, NO FURTHER PROBLEMS. P/N 7277-2-5 AND P/N 7277-2-7 1/2.					1	L	7	2 	4T				A24CE 					 
1995120800136	19951208	00136	CE 	1995	12	8	95ZZZX6469 	1	19951031	G	2460	727425	BREAKER 			BEECH 	200 	200BEECH 	1152920	CE 										RT WING	STUCK 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	35GR	3000 				BB1167				SCHEDULED INSPECTION FOUND BATTERY RELAY CIRCUIT BREAKER LOCATED ON HOT BUS CANNOT BE OPENED. REPLACED CIRCUIT BREAKER.	 NO FURTHER PROBLEMS.					1	L	7	2 	4T				A24CE 					 
1995021000253	19950210	00253	CE 	1995	2	10	95ZZZX647 	1	19950113	G	2810	S14956	HOSE 			CESSNA	182 	182R 	2072731	CE 										FUEL VENT	DETERIORATED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11		1427 								FUEL STAIN WAS NOTED INSIDE COCKPIT ON RIGHT SIDE PANEL AT FORWARD DOOR POST. INSPECTION REVEALED FUEL LEAKAGE THROUGH 	DETERIORATED HOSE ON LOWER WYE BRANCH OF FUEL SYSTEM VENT LINE. THIS ALLOWED FUEL TO RUN DOWN DOOR POST INTO COCKPIT. E	XAMINATION OF VENT LINE CONNECTING HOSE ON LEFT SIDE SHOWED SIMILAR CONDITION. THESE HOSES ARE UNDER PLASTIC TRIM BETWE	EN DOOR POST AND WINDSHIELD AND ARE, THEREFORE, HARD TO SEE.			1	L	7	1 	3O			NT	3A13 					 
1995120800137	19951208	00137	GL 	1995	12	8	95ZZZX6470 	3	19951108	G	6111	1301	CLAMP 			DORNER	DO228 	DO228* 		EU 						HARTZL	HCB3W	HCB3W302 	GL 	321 SCREW HOLE	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	2FOR	3010 			CC7886			AB2470		PROPELLER CLAMP IS CRACKED WHERE THE 321 SCREW HEAD GOES THROUGH THE CLAMP.						1	H	7	2 	4T			RT	A16EU 		5	C	P10EA	 
1995120800138	19951208	00138	GL 	1995	12	8	95ZZZX6471 	3	19951108	G	6114	A18842	PILOT TUBE 			DORNER	DO228 	DO228* 		EU 						HARTZL	HCB3W	HCB3W302 	GL 	PROPELLER	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	2FOR	2010 						AB2470		PROPELLER PILOT TUBE HAS AN APPROXIMATE .50 INCH LONG CRACK.						1	H	7	2 	4T			RT	A16EU 		5	C	P10EA	 
1995120800139	19951208	00139	GL 	1995	12	8	95ZZZX6472 	2	19951110	G	7240	23056130	COMBUSTION LINER			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					DOUBLE LIP	CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V				17545	490487D	CAE830976			COMBUSTION LINER INSPECTION FOUND CRACK ON INSIDE OF DOUBLE LIP AT 8:00 POSITION ABOUT 2.5 INCHES LONG. LINER RETURNED 	FOR REPAIR ON ALLISON 250. REPORT NR R159723.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995120800140	19951208	00140		1995	12	8	95ZZZX6473 	4	19951113	G	2562	0030006	BATTERY PACK 	POINTER 	ELT3000 	BOLKMS	105 	BO105S 	5626006	EU 										ELT	INOPERATIVE 	D				K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			WP	19	50EG				330682	S348				ARTEX ALKALINE ELT BATTERY PACK WAS FOUND INOPERATIVE DURING YEARLY ELT OPERATIONS CHECK REQUIRED BY FAR 91.207. BATTER	Y PACK WAS MANUFACTURED AUGUST, 1994, INSTALLED SEPTEMBER 7, 1994. ELT WAS NOT ACTIVATED OR TESTED EXTENSIVELY, NO MORE	 THAN 10 MINUTES TOTAL OPERATING TIME ACCUMULATED WITHIN THE LAST YEAR.				1	G	7	2 	3U				H3EU 					 
1995120800141	19951208	00141	EU 	1995	12	8	95ZZZX6474 	1	19951107	G	5321	105223411	PANEL 			BOLKMS	105 	BO105S 	5626006	EU 										FLOOR	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15		5642 								FLOOR PANEL RECEIVED WITH TWO UPPER SKINS OF .020 INCH EACH. SB REQUIRED SKIN OF .020 INCH PANEL. SHOWS HEAVY CORROSIO	N. PART PREVIOUSLY OVERHAULED BY ANOTHER REPAIR STATION.					1	G	7	2 	3U				H3EU 					 
1995120800142	19951208	00142	SW 	1995	12	8	95ZZZX6475 	1	19951010	G	6220	206010451005	INNER RING 			BELL 	206 	206L1 	1182107	SW 										PYLON M/R	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05					RE0541					DID NOT GRIND INNER RING TO A MAXIMUM OUTSIDE DIAMETER = 5.3740 INCHES.						1	G	7	1 	3U				H2SW 					 
1995120800143	19951208	00143	SW 	1995	12	8	95ZZZX6476 	1	19950922	G	6310	222044685101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05					A513M					ZINC COATING COMING OFF INSIDE DIAMETER OF SHAFT.						1	G	7	2 	3U				H9SW 					 
1995120800144	19951208	00144	SW 	1995	12	8	95ZZZX6477 	1	19950919	G	6310	222044685101	SHAFT 			BELL 	222 	222 	1182122	SW 										M/R	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05					A518M					ZINC COATNG FLAKING OFF INSIDE DIAMETER OF SHAFT. REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995120800145	19951208	00145	SW 	1995	12	8	95ZZZX6478 	1	19950908	G	6310	222044685101	SHAFT 			BELL 	222 	222U 	1182140	SW 										M/R	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05		361 			A450					IN C/W ASB 222U 95-46, SHAFT P/N 222-044-685-101, RECALL AND REPLACEMENT OF SHAFTS WITH DEFECTIVE COATING OR PRIMER TO I	NSIDE DIAMETER OF SHAFT. REMOVED AND REPLACED.					1	G	7	2 	3U				H9SW 					 
1995120800146	19951208	00146		1995	12	8	95ZZZX6479 	1	19950915	G	6310	222044685101	SHAFT 																	M/R	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05					A565M					ZINC COATING COMING OFF OF INSIDE DIAMETER (USED BORESCOPE TO CHECK).																			 
1995120800147	19951208	00147		1995	12	8	95ZZZX6480 	4	19951011	G	3421	5040017908	GYRO 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ATTITUDE	MALFUNCTION 	B			TI1R	K				NONE 				I			FLT. ATTITUDE INST. 			NR	NOT REPORTED 	1			SW	05	105MH	48 			1706	S419				GYRO SHOWS LEFT BANK ON LEVEL GROUND AND IN LEVEL FLIGHT.						1	G	7	2 	3U				H3EU 					 
1995120800148	19951208	00148	EU 	1995	12	8	95ZZZX6481 	1	19950904	G	6240	117945641	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										MAST MOMENT	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	1140H	102 			E040615	7078				MAST MOMENT HAS NO INDICATION (INOPERATIVE). ONLY LASTED 44 DAYS AND 101.8 HRS SINCE LAST REPAIR.						1	G	7	2 	3U				H13EU 					 
1995120800149	19951208	00149	EU 	1995	12	8	95ZZZX6482 	1	19950904	G	6240	10594575	TRANSMITTER 			BOLKMS	117 	BK117A3 	5626015	EU 										MAST MOMENT	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	1140H	102 			E040615	7078				MAST MOMENT HAS NO INDICATION (INOPERATIVE). ONLY LASTED 44 DAYS AND 101.8 HRS.						1	G	7	2 	3U				H13EU 					 
1995120800150	19951208	00150		1995	12	8	95ZZZX6484 	4	19951011	G	3421	5040017926	GYRO 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT ATTITUDE	LIGHT INOP 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117MH	128 			7107	7112				ATTITUDE GYRO'S INTERNAL ILLUMINATION LIGHT INOP.						1	G	7	2 	3U				H13EU 					 
1995120800151	19951208	00151		1995	12	8	95ZZZX6485 	4	19950903	G	2562	ELT10	ELT 			BOLKMS	117 	BK117A3 	5626015	EU 										G-SWITCH	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117MH	285 			75539	7112				RADIO IMPACT SWITCH WEAK. ALLOW RADIO TO OPERATE DURING NORMAL FLIGHT. KEEPS GOING OFF DURING LANDING.						1	G	7	2 	3U				H13EU 					 
1995120800152	19951208	00152	EU 	1995	12	8	95ZZZX6486 	1	19950906	G	6240	117945641	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										MAST MOMENT	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117UC	17 			E100732	7098				MAST MOMENT INOPERATIVE. INDICATOR DOES NOT INDICATE. INSTALLED 10 DAYS AGO AND 16.9 HRS.						1	G	7	2 	3U				H13EU 					 
1995120800153	19951208	00153	EU 	1995	12	8	95ZZZX6487 	1	19950906	G	6240	10594575	TRANSMITTER 			BOLKMS	117 	BK117A3 	5626015	EU 										MAST MOMEMT	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117UC	17 			E100732	7098				INOPERATIVE MAST MOMENT TRANSMITTER, (INDICATOR WILL NOT INDICATE). INSTALLED 10 DAYS AGO AND 16.9 HRS.						1	G	7	2 	3U				H13EU 					 
1995120800154	19951208	00154	EU 	1995	12	8	95ZZZX6488 	1	19951012	G	6720	741C000005	ACTUATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	LEAKING 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117UC	172 			00181	7098				LEAKING TAIL ROTOR ACTUATOR.						1	G	7	2 	3U				H13EU 					 
1995120800155	19951208	00155	EU 	1995	12	8	95ZZZX6489 	1	19950810	G	6720	741C000005	ACTUATOR 			BOLKMS	117 	BK117A1 	5626010	EU 										T/R	LEAKING 	B			TI1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	05	117LF	57 			00201	7013				PEDALS KICK IN APPROACH MODE. ACTUATOR LEAKING. LAST REPAIR WAS EXCESSIVE LEAKAGE ALSO (LESS THAN 3 MONTHS LATER).						1	G	7	2 	3U				H13EU 					 
1995021000255	19950210	00255	SO 	1995	2	10	95ZZZX649 	1	19950120	G	7110	6735000	COWL 			PIPER 	PA28 	PA28R200 	7102811	SO 										ENGINE TOP	DETACHED 	H		A		O				OTHER 				O			OTHER 			CR	CRUISE 	1			SO	16	4494T					28R7235039				FIFTEEN MINUTES AFTER TAKEOFF, THE ONE-PIECE TOP COWLING CAME OFF STRIKING THE PROPELLER AND BREAKING OUT THE COPILOT'S 	WINDSHIELD. THE COWLING WAS NOT RECOVERED. IT IS BELIEVED THE TWO-COWL FASTENERS ON THE LEFT SIDE CAME UNFASTENED. TH	E COWLING CAME UP AND ROLLED FROM LEFT TO RIGHT BREAKING OFF APPROXIMATELY 6 INCHES ABOVE THE FASTENERS ON THE RIGHT SID	E. THE FASTENERS ON THE RIGHT REMAINED FASTENED. THE FASTENERS WERE SECURED ON PRE-FLIGHT, IT IS SUSPECTED THE WING NU	TS WERE LOOSE WITH NO TENSION IN THE LOCKED POSITION. IT IS SUSPECTED AIR FLOW OR VIBRATION ALLOWED FASTENERS TO COME L	OOSE IN FLIGHT. SUGGEST ALL OWNERS, OPERATORS & MECHANICS KEEP A CLOSE WATCH ON THESE WING NUTS FOR SECURITY.	1	L	7	1 	3O				2A13 					 
1995120800156	19951208	00156	EU 	1995	12	8	95ZZZX6490 	1	19950817	G	6240	1179405303	INDICATOR 			BOLKMS	117 	BK117A1 	5626010	EU 										TRIPLE TACH NR	INTERMITTENT 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117LF	48 			481	7013				NO NR, ROTOR INDICATOR INSTALLED WITH INTERMITTENT NR WHEN PUT IN, THEN IT CLEARED UP. RE-APPEARED AGAIN ONE WEEK LATER	. IT ONLY LASTED ONE WEEK AND 47.9 HRS. N2 NEEDLE ERRATIC ON START-UP.					1	G	7	2 	3U				H13EU 					 
1995120800157	19951208	00157		1995	12	8	95ZZZX6491 	4	19950825	G	2211	117884141	COMPUTER 			BOLKMS	117 	BK117A1 	5626010	EU 										YAW CSAS	DEFECTIVE 	B			TI1R	O				OTHER 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			SW	05	117LF	36 			8609010	7013				YAW SYSTEM COMPUTER WOULD HAVE INTERMITTENT OPERATION AND KICK AIRCRAFT AROUND 45 DEGREES TO 70 DEGREES IN AIR. ONLY 36	.2 HRS SINCE LAST REPAIR ON AUGUST 1, 1995.					1	G	7	2 	3U				H13EU 					 
1995120800158	19951208	00158	EU 	1995	12	8	95ZZZX6492 	1	19951009	G	5530	11730650	FIN 			BOLKMS	117 	BK117A1 	5626010	EU 										VERTICAL STAB	CRACKED 	B			KI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	117LF				S013	7013				CRACKED VERTICAL FIN.						1	G	7	2 	3U				H13EU 					 
1995120800159	19951208	00159	EU 	1995	12	8	95ZZZX6493 	1	19951004	G	7714	1179405303	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										TRIPLE TACH N2	FLUCTUATES 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	170MC				524	7217				NR 1 N2 NEEDLE FLUCTUATES WHILE ENGINE IS AT 100 PERCENT. NEEDLE FLUCTUATES FROM 70 PERCENT - 25 PERCENT INTERMITTENTLY	. LAST REPAIR WAS ALSO FLUCTUATES, STILL DOING THE SAME THING.					1	G	7	2 	3U				H13EU 					 
1995120800160	19951208	00160	EU 	1995	12	8	95ZZZX6494 	1	19950828	G	3340	A7151	LANDING LIGHT 			BOLKMS	117 	BK117B1 	5626012	EU 										FIXED LIGHT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	215AE	516 				7216				LANDING LIGHT INOPERATIVE, LESS THAN 1,000 HRS OR 1 YEAR. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995120800162	19951208	00162		1995	12	8	95ZZZX6496 	4	19950912	G	3422	5223241000	GYRO 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT DG	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2907T	241 			7111	S577				DIRECTIONAL GYRO OUT, 90 DEGREES OFF HEADING.						1	G	7	2 	3U				H3EU 					 
1995120800163	19951208	00163	GL 	1995	12	8	95ZZZX6497 	2	19950601	G	7261	6876925	OIL TUBE 			BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2907T					S577	CAE834920			OIL TUBE FAILED INSPECTION REQUIRED BY CEB1307. REMOVED AND REPLACED.						1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995120800164	19951208	00164	EU 	1995	12	8	95ZZZX6498 	1	19950830	G	6210	1178016602	BRACKET 			BOLKMS	117 	BK117A4 	5626017	EU 										VIB ABSORBER	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	313LF					7138				VIBRATION ABSORBER WASHER UNDER BOLT HEAD DOES NOT LAY FLAT ON MOUNT FLANGE AT LEADING END OF BRACKET.						1	G	7	2 	3U				H13EU 					 
1995120800165	19951208	00165	NE 	1995	12	8	95ZZZX6499 	2	19951006	G	7412	9580113800	H. E. GENERATOR 			AEROSP	SA365 	SA365N1 	8680668	EU 	TMECA 	ARRIEL	ARRIEL1C 	60030	NE 					ENGINE IGN	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	365SC	333 			6656	6298	5028			INTERMITTENT OPERATION OF H.E. GENERATOR.						1	G	7	2 	3U	3	U		H10EU 	E19EU				 
1995021000256	19950210	00256	CE 	1995	2	10	95ZZZX650 	1	19950112	G	2434	ALT9422	ALTERNATOR 	PRESTOLITE 		CESSNA	310 	310R 	2074245	CE 										BEARING	FAILED 	D				A				UNSCHED LANDING 				B	J		SMOKE/FUMES/ODORS/SPARKS 	WARNING INDICATION 		CL	CLIMB 	1			SO	11	72GL		756 		A91008	310R0155				CATASTROPHIC FAILURE OF OUTER BEARING. ACFT WAS CLIMBING OUT AFTER TAKEOFF. PILOT SAW ALTERNATOR FAIL LIGHT COME ON. L	OOKED OUT AT ENGINE NACELLE AND SAW SPARKS. PILOT RETURNED TO AIRPORT WITHOUT ANY INCIDENT. THE BEARING THAT FAILED IS	 EXPOSED TO THE ELEMENTS OF WEATHER AND WIND BLASTS. SUBMITTER SUGGESTS LUBE OF BEARING EVERY 250 HOURS. REPLACEMENT E	VERY 500 HOURS.			1	L	7	2 	3O				3A10 					 
1995120800166	19951208	00166		1995	12	8	95ZZZX6500 	4	19950927	G	3421	4021541671	GYRO 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT HORIZ	MALFUNCTION 	B			TI1R	K				NONE 				I			FLT. ATTITUDE INST. 			NR	NOT REPORTED 	1			SW	05	312LF	95 			85091232	7083				GYRO MAKES YAW SAS ACTIVATE LEFT TO RIGHT DURING FLIGHT. TAKES OVER 3 MINUTES, 30 SECONDS TO PULL FLAG. HORIZON WILL A	LSO BE LEANING RIGHT WHILE IN STRAIGHT AND LEVEL FLIGHT.					1	G	7	2 	3U				H13EU 					 
1995120800167	19951208	00167	EU 	1995	12	8	95ZZZX6501 	1	19950821	G	5530	11730610	FIN 			BOLKMS	117 	BK117A4 	5626017	EU 										LE PANEL	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	313LF	87 			ADS512101	7138				VERTICAL FIN HAS CRACK IN LEADING EDGE AROUND KNOCKOUT PANEL.						1	G	7	2 	3U				H13EU 					 
1995120800168	19951208	00168	EU 	1995	12	8	95ZZZX6502 	1	19950909	G	3310	1179203103	CONTROL UNIT 			BOLKMS	BK117 	BK117C1 	5626025	EU 										INST LIGHTS	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	768 			0878	7505				NO POWER OUTPUT TO INSTRUMENT LIGHTS. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995120800169	19951208	00169	EU 	1995	12	8	95ZZZX6503 	1	19950801	G	5320	11722201103	HINGE 			BOLKMS	BK117 	BK117C1 	5626025	EU 										EQUIP DECK	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	8 				7505				CRACKED HINGE ON EQUIPMENT DECK. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995120800170	19951208	00170	EU 	1995	12	8	95ZZZX6504 	1	19950901	G	2121	19A2772	BLOWER 			BOLKMS	BK117 	BK117C1 	5626025	EU 										VENT FAN	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	747 				7505				INTERMITTENT VENT FAN, 2 EACH. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995120800171	19951208	00171	EU 	1995	12	8	95ZZZX6505 	1	19950829	G	2121	ES730732	BLOWER 			BOLKMS	BK117 	BK117C1 	5626025	EU 										VENT FAN	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	746 			0188	7505				BLOWER INTERMITTENT DURING OPERATION. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995120800172	19951208	00172	EU 	1995	12	8	95ZZZX6506 	1	19950901	G	5620	117242002	SUPPORT BRACE 			BOLKMS	BK117 	BK117C1 	5626025	EU 										RT DOOR WINDOW	NOT INSTALLED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	317MC	746 			112492	7505				THE BK117C1 REQUIRES SUPPORT BRACKET. WINDOW DID NOT HAVE SUPPORT BRACKET WHEN AIRCRAFT ARRIVED.						1	G	7	2 	3U			NC	H13EU 					 
1995120800173	19951208	00173		1995	12	8	95ZZZX6507 	4	19950927	G	3421	5208014002	GYRO 			BOLKMS	BK117 	BK117C1 	5626025	EU 										COCKPIT VG	DEFECTIVE 	B			TI1R	K				NONE 				I			FLT. ATTITUDE INST. 			NR	NOT REPORTED 	1			SW	05	317MC				13917	7505				VERTICAL GYRO OCCASIONALLY FALLS OFF TO 20 PERCENT RIGHT BANK ON EFIS DISPLAY. ALSO, GENERATES AUTOPILOT ERROR CODES.						1	G	7	2 	3U			NC	H13EU 					 
1995120800174	19951208	00174	EU 	1995	12	8	95ZZZX6508 	1	19950913	G	3412	600801	SWITCH 			BOLKMS	BK117 	BK117C1 	5626025	EU 										AIR TEMPERATURE	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	771 			0017	7505				AIR TEMPERATURE SWITCH DEFECTIVE. SUSPECT TEMPERATURE RANGE TO BE LOW. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995120800175	19951208	00175	SW 	1995	12	8	95ZZZX6509 	1	19950907	G	3340	A469A	FLASH TUBE 			BELL 	206 	206L1 	1182107	SW 										STROBE	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	400SL	61 				45235				INOPERATIVE FLASH TUBE. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995021000257	19950210	00257	CE 	1995	2	10	95ZZZX651 	1	19950120	G	7603	S122217	CONTROL CABLE 			CESSNA	150 	150J 	2071820	CE 										THROTTLE	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	50793	2720 				15069558				AT ANNUAL INSPECTION, THROTTLE WAS FOUND TO HAVE .50 INCH OF TRAVEL AFTER CARBURETOR WAS AGAINST THE IDLE SPEED SCREW. M	OVEMENT WAS STILL FREE AND SMOOTH. SUSPECT THE INNER CORE OF THE FLEXIBLE CABLE WAS BROKEN AND THE OUTER SPINAL WIRES W	ERE STILL CONNECTED.				1	H	7	1 	3O			 	3A19 					 
1995120800176	19951208	00176		1995	12	8	95ZZZX6510 	4	19950918	G	3422	40205773	COMPASS 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT	ERRORS 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4493X				85063655	S7038				COMPASS SYSTEM GIVING ERRONEOUS HEADING INDICATION. ALSO, NR 2 RMI COMPASS WAS INOPERATIVE TO SLAVING MODE.						1	G	7	2 	3U				H13EU 					 
1995120800177	19951208	00177		1995	12	8	95ZZZX6511 	4	19950915	G	3416	5934PA3	ALTIMETER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	ERROR 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4572R	30 			2KZ03	S663				ALTIMETER INDICATES INCORRECTLY AND IT RATTLES.						1	G	7	2 	3U				H3EU 					 
1995120800178	19951208	00178	EU 	1995	12	8	95ZZZX6512 	1	19950922	G	6520	4639311006	GEARBOX 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	MISREPAIRED 	B			KI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	03	460H	2937 			5818345	7142				GEARBOX HOUSING WAS SENT FOR REPAIR 11-30-94 AND WAS RETURNED ON 9-19-95 WITH A SERVICEABILITY TAG AND THE WORK REQUESTE	D WAS NOT COMPLETED. IT WAS ONE-HALF FINISHED AND COULD NOT BE INSTALLED IN ITS CURRENT CONDITION. REASON IT WAS SENT,	 WAS FOR EXCESSIVE CORROSION DAMAGE.				1	G	7	2 	3U				H13EU 					 
1995120800179	19951208	00179	SW 	1995	12	8	95ZZZX6513 	1	19950815	G	6310	CL422501	CLUTCH 			BELL 	206 	206L1 	1182107	SW 										FREEWHEEL	SPRAG DEFECT 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	519EH	158 			FD10399	45429				FOUND SMALL DEFECT ON 1 EACH SPRAG ON INSIDE DIAMETER OF CLUTCH. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995120800180	19951208	00180	SW 	1995	12	8	95ZZZX6514 	1	19951009	G	7714	206075682107	INDICATOR 			BELL 	206 	206L4 	1182110	SW 										N1 TACHOMETER	ERRATIC 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	706SD	1305 			0524	52056				N1 TACHOMETER HAS ERRATIC INDICATION. JUMPS FROM 2 PERCENT TO 15 PERCENT WHILE STARTING.						1	G	7	1 	3U			NC	H2SW 					 
1995120800181	19951208	00181	EU 	1995	12	8	95ZZZX6515 	1	19950926	G	3040	11780325	SUPPORT 			BOLKMS	117 	BK117A3 	5626015	EU 										WIPER LT	MISMANUFACTURED 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	950MB					7061				WIPER, LT SUPPORT DEFECTIVE. THERE SHOULD BE AN INSERT IN ONE OF THE HOLES, BUT THERE IS NOT.						1	G	7	2 	3U				H13EU 					 
1995120800182	19951208	00182	SW 	1995	12	8	95ZZZX6516 	1	19950901	G	6310	222044672101	COUPLING 			BELL 	222 	222 	1182122	SW 										MAIN DRIVE	CORRODED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	368 			798	47520				OUTER COUPLING - CORROSION FOUND ON SPLINES REPEATEDLY IN THIS AREA ON MANY OF BHT 222'S MAIN DRIVESHAFTS. SUSPECT FAUL	TY GREASE. REMOVED AND REPLACED.					1	G	7	2 	3U				H9SW 					 
1995120800183	19951208	00183		1995	12	8	95ZZZX6517 	4	19950828	G	2211	105980624	COMPUTER 			BOLKMS	105 	BO105LSA3 	5626020	EU 										CSAS	DEFECTIVE 	B			TR1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911SV				018811033	2033				PITCH AXIS OSCILLATES FORWARD AND AFT. REPLACED PITCH ACTUATOR. REPLACING EACH UNIT SEPARATELY DID NOT CURE DISCREPANC	Y.					1	G	7	2 	3U				H3AU 					 
1995021000258	19950210	00258		1995	2	10	95ZZZX652 	4	19950105	G	3450	KN74	COMPUTER 			PIPER 	PA31 	PA31325 	7103105	SO 										LAMP CIRCUIT	MISWIRED 	B			CE4R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03	59813					317612039				NR 1 NAV INOP IN VOR DISPLAY ON PILOT'S HSI UNLESS DME WAS LOCKED ON. PROBLEM CAUSED BY REMOTE AREA/NAV SELECT LIGHT BE	ING IMPROPERLY WIRED TO A LAMP ASSEMBLY WITH NO ISOLATED GROUND. WITH A HARD GROUND ON PIN 16 OF THE KN74, IT WAS STUCK	 IN LOCALIZED MODE UNLESS A POSITIVE FLAG FROM THE DME LOCK ON 'FIXED' THE PROBLEM. INSTALLED AND WIRED PROPER LIGHT AS	SEMBLY FOR NORMAL OPERATION. INSTALLATION NOTES SHOULD BE READ VERY CAREFULLY.			1	L	7	2 	3O				A20SO 					 
1995120800383	19951208	00383	SW 	1995	12	8	95ZZZX6523 	1	19951101	G	2821		STRAINER 			TMPSON	NAVION	NAVION* 	6150130	SW 										FUEL SYSTEM	MISSING 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	91689					NAV4431				DURING ANNUAL INSPECTION, FOUND ENTIRE FUEL STRAINER ASSEMBLY HAD BEEN REMOVED FROM AIRCRAFT. NO INFORMATION NOTED IN L	OG BOOK. FUEL SYSTEM LINES DIRECTLY TO INJECTION SYSTEM AT INDUCTION SYSTEM.					1	L	7	1 	3O				A782 					 
1995120800384	19951208	00384	SW 	1995	12	8	95ZZZX6524 	1	19951101	G	7160	14542201SA1	AIR BOX 			TMPSON	NAVION	NAVION* 	6150130	SW 										90 DEGREE ELL	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	91689					NAV4431				ON INSPECTION, 90 DEGREE 'L' FOUND CRACKED. ATTACH BOLTS NOT TIGHT. TT UNKNOWN. ORIGINAL A/C ISSUE. REPAIRED WITH DO	UBLER. VIBRATION SUSPECTED AS CAUSE.					1	L	7	1 	3O				A782 					 
1995120800385	19951208	00385	CE 	1995	12	8	95ZZZX6525 	1	19950927	G	5520	58341308	BRACKET 		57341001 	CESSNA	441 	441 	2076020	CE 										ELEV LT INBD	EXCESS WORN 	B		A	CWNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	6855P	3390 				4410233				BOLT HOLES IN BOTH BRACKETS EXCESSIVELY WORN AND THE MOUNT BOLT, PN NAS464P6-11, HAD GROOVES IN IT. CONDITION WAS FOUND	 BY MECHANIC ON WALK-AROUND INSPECTION PRIOR TO MAINTENANCE INSPECTION PRE-RUNUP. A CESSNA MFG PHASE 2 INSPECTION WAS B	EING PERFORMED AT THIS TIME WHICH DOES NOT REQUIRE INSPECTION OF THE EMPENNAGE. SUBMITTER RECOMMENDS CLOSER INSPECTION 	ON WALK-AROUND. NEW BRACKETS AND BOLT INSTALLED WERE FURNISHED BY CESSNA AIRCRAFT.			1	L	7	2 	3T			RT	A28CE 					 
1995120800386	19951208	00386	CE 	1995	12	8	95ZZZX6526 	1	19950927	G	5520	58341309	BRACKET 		57341001 	CESSNA	441 	441 	2076020	CE 										ELEV RT INBD	EXCESS WORN 	B			CWNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	6855P	3390 				4410233				BOLT HOLES IN BOTH BRACKETS EXCESSIVELY WORN AND THE MOUNT BOLT, PN NAS464P6-11, HAD GROOVES IN IT. CONDITION WAS FOUND	 BY MECHANIC ON WALK-AROUND INSPECTION PRIOR TO MAINTENANCE INSPECTION PRE-RUNUP. A CESSNA MFG PHASE 2 INSPECTION WAS B	EING PERFORMED AT THIS TIME WHICH DOES NOT REQUIRE INSPECTION OF THE EMPENNAGE. SUBMITTER RECOMMENDS CLOSER INSPECTION 	ON WALK-AROUND. NEW BRACKETS AND BOLT INSTALLED WERE FURNISHED BY CESSNA AIRCRAFT.			1	L	7	2 	3T			RT	A28CE 					 
1995120800387	19951208	00387	CE 	1995	12	8	95ZZZX6527 	1	19951004	G	3233	3800025	MOTOR 			BEECH 	200 	200BEECH 	1152920	CE 										MLG	FAILED 	B			CWNR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			WP	09	2FOR		5 		1315	BB435				NOTE MLG MOTOR FAILURE AT 4.5 HRS AFTER OVERHAUL. MOTOR WOULD NOT MOVE LANDING GEAR. SUBMITTER RECOMMENDS CLOSER FINAL	 OPERATIONAL TEST PRIOR TO RETURN TO SERVICE FROM TEST BENCH.					1	L	7	2 	4T				A24CE 					 
1995120800388	19951208	00388	SW 	1995	12	8	95ZZZX6528 	1	19951101	G	2916	14558016	RESERVOIR 			TMPSON	NAVION	NAVION* 	6150130	SW 										HYDRAULIC SYSTEM	PARTS MISSING 	D	S			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	01	91689					NAV4431				ON ANNUAL INSPECTION, NOTED PARTS NOT IN SYSTEM. FILTER CLOGGED. TT ON FILTER UNKNOWN. NO RECORD FOR PAST 5 YEARS FOR 	FILTER CHANGE. PARTS LEFT OUT ON LAST CHANGE. FILTER MUST BE CHANGED EVERY 12 MONTHS. MISING PARTS: GASKET-AN902-8, 	GUIDE-1U5-58161, PACKING-AN62273.				1	L	7	1 	3O				A782 					 
1995120800389	19951208	00389	SW 	1995	12	8	95ZZZX6529 	1	19951101	G	2750	14552021	BELLCRANK 			TMPSON	NAVION	NAVION* 	6150130	SW 										FLAP	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	91689					NAV4431				INSPECTION, PART CLEANED WITH WIRE BRUSH WHEN MOVEMENT WAS NOTED. BUSHING WORN IN VERTICAL PLANE, NR 47. LOWER ARM CRA	CKED. IF IT BROKE WHILE LOWERING FLAPS, COULD CAUSE FAILURE. SUSPECT CAUSE AS DROPPING FLAPS IN EXCESS OF 100 MPH OR G	EAR-UP LANDING WITH FLAPS.				1	L	7	1 	3O				A782 					 
1995021000259	19950210	00259		1995	2	10	95ZZZX653 	2	19950126	G	7414	M3040	COIL WEDGE 	SLICK 	4271 															COIL RETAIN	DEFECTIVE 	B		A	A4OR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03										COIL WEDGES CAUSING DAMAGE TO COIL CORE LAMINATIONS - SEPARATION OF LAMINATIONS AND TWISTING OF LAMINATED CORE WITHIN CO	IL RESULTING IN CRACKS IN COIL CASING. NO PRECISE METHOD EXISTS FOR DRIVING WEDGES TO ASSURE THEY ARE TIGHT ENOUGH NOT 	TO FALL OUT YET NOT SO TIGHT AS TO DAMAGE THE COIL. SUBMITTER SUGGESTS AN ALTERNATIVE METHOD OF COIL RETENTION, SCREWS,	 CLAMPS, ETC. CURRENT DESIGN USES AN ALUMINUM WEDGE SIMPLY DRIVEN IN BETWEEN COIL CORE AND HOUSING. MANUFACTURER'S INS	TRUCTIONS FOR INSTALLING THIS WEDGE IS 'DRIVE COIL WEDGE TIGHT'.															 
1995120800390	19951208	00390	EU 	1995	12	8	95ZZZX6530 	1	19951109	G	6720	350A33214501	ROD 			SNIAS 	350 	AS350B 	8680801	EU 										T/R PITCH CONT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	842BP	1471 			2103	2037				DURING 100-HOUR INSPECTION, LOOSENESS OF BEARING WAS FOUND. SUSPECTED CAUSE, NORMAL WEAR.						1	G	7	1 	3U				H9EU 					 
1995120800391	19951208	00391	SW 	1995	12	8	95ZZZX6531 	1	19951024	G	7160	600355507	VALVE 			MOONEY	M20 	M20J 	5870219	SW 										ALTERNATE AIR	DETACHED 	B	S	A	DYTR	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			R			PARTIAL RPM/PWR LOSS 			TO	TAKEOFF 	1			SO	15	193ER	4162 				243243				AIRCRAFT SUFFERED ENGINE POWER LOSS ON TAKEOFF ROLL. PILOT ABORTED TAKEOFF AND STOPPED TAKEOFF ROLL ON RUNWAY. INSPECT	ION REVEALED ALTERNATE AIR VALVE HAD COME LOOSE. NUT AND COTTER PIN WERE MISSING. VALVE ROLLED DOWN INSIDE INDUCTION A	IR DUCT AND BLOCKED OFF AIR FLOW TO FUEL SERVO.				1	L	7	1 	3O				2A3 					 
1995120800392	19951208	00392	SO 	1995	12	8	95ZZZX6532 	1	19951011	G	3222	7020693	FORK 			GULSTM	AA5 	AA5B 	3960105	SO 										NLG	NUT MISSING 	G		A		A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			WP	07	81218					0458				DURING TAKEOFF AT LIFT OFF, THE NOSE FORK/WHEEL ASSEMBLY DEPARTED (FELL OFF) THE AIRCRAFT. RETURNED AND LANDED WITHOUT 	INCIDENT. AN INSPECTION OF THE NOSE GEAR REVEALED THE FORK RETAINING NUT WAS MISSING, IT HAD BACKED OFF. IT IS SUSPECT	ED THAT THE COTTER PIN HAD BEEN REMOVED DURING MAINTENANCE AND HAD NOT BEEN RE-INSTALLED.				1	L	7	1 	3O				A16EA 					 
1995120800393	19951208	00393	CE 	1995	12	8	95ZZZX6533 	1	19951110	G	3242	16402504	DISK 			BEECH 	76 	76 	1153005	CE 										MLG BRAKE	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	822ER					ME293				FOUND TINY HAIR LINE FRACTURES ON INBOARD SIDE OF DISC ROTOR. COULD NOT IDENTIFY THE CAUSE OF THE CRACKS.						1	L	7	2 	3O				A29CE 					 
1995120800394	19951208	00394	CE 	1995	12	8	95ZZZX6534 	1	19950823	G	5753		ROLLER 			CESSNA	172 	172N 	2072434	CE 										RT FLAP	FAILED 	D	L			O				OTHER 				O			OTHER 			CL	CLIMB 	1			WP	25	4624D					17272317				TT, 6,804.7 HRS. PILOT REPORTED UNUSUAL SOUND UPON FLAP RETRACTION AFTER TAKEOFF. FLAP FOUND BUCKLED, BUT MOSTLY RETRA	CTED. FOUND FLAP ROLLERS WITH CRACKS IN THE BEARING SHELLS AND FAILED ROLLER. REPLACED FLAP & ROLLERS. TT, 9,534.3 HR	S. DURING SLOW SPEED AIR-WORK, FLAP OUTBOARD ROLLER ARM FROZE IN RAIL AND REST OF FLAP RETRACTED RESULTING IN OTBD PORT	ION (ONE-THIRD) AT 40 DEGREES AND INBD TWO-THIRDS RETRACTED.			1	H	7	1 	3O			NT	3A12 					 
1995120800395	19951208	00395	SO 	1995	12	8	95ZZZX6535 	1	19951016	G	5313		STRINGER 			PIPER 	PA28 	PA28R201 	7102816	SO 										FS 191	CRACKED 	B		A	OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	813ND	4285 				2837044				FOUND CENTER STRINGER ON BELLY CRACKED AT STA 191 BULKHEAD/FORMER. SUBMITTER STATED CRACKS IN THIS STRINGER HAVE BEEN F	OUND AND REPAIRED IN NUMEROUS AIRCRAFT IN PA28 FLEET OF 55 AIRCRAFT. SOME AIRCRAFT HAVE 2 DIAGONAL STRINGERS, ALSO, AT 	THIS LOCATION. THEY ARE ALSO PRONE TO CRACKING.				1	L	7	1 	3O				2A13 					 
1995120800396	19951208	00396	SO 	1995	12	8	95ZZZX6536 	2	19951114	G	8520	639200	CRANKSHAFT 								CONT 	O360 	TSIO360CB 	17025	SO 					FLANGE	CRACKED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	6LH						R236024R			ENGINE WAS WINDMILLING DURING A GEAR-UP LANDING (10-11-95) AT ROCKY MOUNTAIN AIRCARE. REPAIRED BELLY AND HAD PROP OVERH	AULED AT H & H. REINSTALLED PROPELLER WITH A DIAL INDICATOR RUN-OUT CHK ONLY, WAS RETURNED TO SERVICE AS AIRWORTHY. DU	RING THE INSPECTION, THE CRANKSHAFT WAS FOUND CRACKED IN THE RADIUS IMMEDIATELY BEHIND THE PROP FLANGE. SEVERAL CRACKS 	RUNNING AROUND THE RADIUS EDGE GO APPROXIMATELY 80 PERCENT AROUND THE SHAFT. UPON DISASSEMBLY OF THE ENGINE, THE CRANKC	ASE WAS ALSO FOUND CRACKED IN THE FRONT MAIN BEARING SADDLE.							3	O			E9CE				 
1995120800397	19951208	00397	EA 	1995	12	8	95ZZZX6537 	2	19951019	G	8530	73806	PUSHROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235N2C 	41505	EA 					VALVE TRAIN	FAILED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	6238P		1930 			15284990	RL2247915			PUSHROD MARKED AS 73806# FAILED AT END OF PUSHROD. LYCOMING MANDATORY SB OA-522 IN CONJUNCTION WITH AD 95-03-10, WAS AC	COMPLISHED 2-16-95. NO DEFECTS IN ENGINE VALVE TRAIN OR VALVES STICKING WERE NOTED. PARTS WERE REPLACED AND ENGINE RAN	 OK AND RETURNED TO SERVICE. THE POUND SIGN (*) HAD BEEN HAND ENGRAVED NEXT TO STAMPED P/N 73806, WAS ONLY UNUSUAL THIN	G NOTED. NO OTHER MARKINGS WERE FOUND.			1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995120800398	19951208	00398	GL 	1995	12	8	95ZZZX6538 	3	19951011	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	PROPELLER	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	95892	6366 				15285979		DG066		WHILE PERFORMING AD 95-21-01 ON MCCAULEY PROPELLER, CRACK WAS FOUND TO BE UNACCEPTABLE AND BEYOND LIMITS. PROP SCRAPPED	.					1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995120800399	19951208	00399	GL 	1995	12	8	95ZZZX6539 	3	19951011	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	PROPELLER	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	5198L	7940 				15284277		775802		WHILE PERFORMING AD 95-21-01 ON MCCAULEY PROPELLER, CRACK WAS FOUND TO BE UNACCEPTABLE AND BEYOND LIMITS. PROP SCRAPPED	.					1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995021000260	19950210	00260		1995	2	10	95ZZZX654 	4	19950126	G	6113	E6178	BULKHEAD 	MCAULY 		CESSNA	414 	414A 	2075907	CE 										PROP SPINNER	CRACKED 	B			DQIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	414VA	557 				414A0442				AIRCRAFT MODIFIED PER STC SA4943SW (RAM WINGLETS AND GROSS WEIGHT INCREASE) AND STC SA7633SW (LIQUID ENGINES AND MCCAULE	Y PROPS). SPINNER BULKHEAD FOUND WITH 3 CRACKS EMANATING FROM ATTACHMENT STUD HOLES. TWO CRACKS APPROXIMATELY 1 INCH L	ONG, OTHER APPROXIMATELY 4 INCHES LONG. IT APPEARS THE WAY THE 3 CRACKS STARTED, THAT THE OTHER 3 MOUNT HOLES WOULD CRA	CK SOON. POSSIBLE REINFORCEMENT REQUIRED IN THIS AREA.			1	L	7	2 	3O				A7CE 					 
1995120800400	19951208	00400	GL 	1995	12	8	95ZZZX6540 	3	19951011	G	6114		HUB 			CESSNA	150 	152 	2071835	CE 						MCAULY	1A103	1A103TCM 	GL 	PROPELLER	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	93407	5820 				15285481		DG080		WHILE PERFORMING AD 95-21-01 ON MCCAULEY PROPELLER, CRACK WAS FOUND TO BE UNACCEPTABLE AND BEYOND LIMITS. PROP SCRAPPED	.					1	H	7	1 	3O			NT	3A19 		5	N	P50GL	 
1995120800401	19951208	00401	SO 	1995	12	8	95ZZZX6541 	1	19951116	G	7810	557369	CLAMP 			PIPER 	PA31 	PA31350 	7103110	SO 										TURBO EXHAUST	BURNED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	27341		300 			317752162				PIPER TURBO EXIT DUCT V-BAND CLAMPS ON BOTH ENGINES HAD ALLOWED EXHAUST GASSES TO LEAK PAST, BURNING THE CLAMPS SAFETY T	ABS OFF. ALSO, THE LOCK NUTS ON BOTH CLAMPS WERE FREE-TURNING.					1	L	7	2 	3O				A20SO 					 
1995120800402	19951208	00402	SO 	1995	12	8	95ZZZX6542 	1	19951110	G	7810	NH100089750	CLAMP 			PIPER 	PA31 	PA31P 	7103120	SO 										TURBO PIPE	CRACKED 	B			AGJR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	90AP					31P7300148				FOUND CLAMP CRACKED DURING INSPECTION OF ALL EXHAUST COMPONENTS FOR CONDITION FOLLOWING PURCHASE OF AIRCRAFT BY CUSTOMER	. ADVISE CLAMPS BE INSPECTED VERY CLOSELY AS THIS CLAMP LOOKED LIKE A GOOD CLAMP UNTIL CLOSE INSPECTION REVEALED APPROX	IMATELY A 2 INCH CRACK ALONG 'BOTTOM' RIDGE OF CLAMP (AS INSTALLED).				1	L	7	2 	3O				A8EA 					 
1995120800403	19951208	00403	SO 	1995	12	8	95ZZZX6543 	1	19951108	G	5320	7599300	FITTING 			PIPER 	PA44 	PA44180 	7104402	SO 										FS 73	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	36699	7435 				447995005				FOUND STEEL FITTINGS, BOTH LEFT AND RIGHT SIDE, CORRODED AT STA 73. WINDOW WAS LEAKING CAUSING WATER TO SATURATE INSULA	TION. THIS CAUSED A CORROSIVE ENVIRONMENT. SUBMITTER RECOMMENDATIONS WOULD BE TO INSPECT STEEL FITTINGS, INSULATION AN	D WINDOW. REPLACE AND/OR SEAL NECESSARY PARTS. AFTER DOING NECESSARY MAINTENANCE, TREAT ATTACH STEEL FITTINGS WITH DIN	OL AV 8 CORROSION COMPOUND. PIPER P/N 89500-800. INSPECT EVERY ANNUAL/100 HOUR, AND THEREAFTER.			1	L	7	2 	3O				A19S0 					 
1995120800404	19951208	00404	CE 	1995	12	8	95ZZZX6544 	1	19951113	G	5523	12340007	TRIM TAB 		112340002 	CESSNA	210 	210M 	2073450	CE 										ELEVATOR	CORRODED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	732PW	4515 				21021675				THERE IS EXCESSIVE CORROSION ON THE ELEVATOR TRIM TAB. THERE ARE PIN HOLES THROUGH THE METAL ON TOP AND LOWER PORTION O	F TRIM TAB NEAR THE TRIM TAB ACTUATOR ATTACH POINT. SUBMITTER STATED THIS IS A VERY SERIOUS CONDITION.					1	H	7	1 	3O				3A21 					 
1995120800405	19951208	00405	EA 	1995	12	8	95ZZZX6545 	2	19951026	G	8520	LW18372	CRANKCASE 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					ALT MOUNT BOSS	CRACKED 	B			OG5R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	21	118ND	3845 	650 			2841136	L1596139A			DURING ENGINE INSPECTION, TECHNICIAN TRACED OIL LEAK TO A CRANKCASE CRACK IN THE AREA OF THE ALTERNATOR MOUNT BOSS. CRA	CK IS IN THIS AREA OF RIGHT CRANKCASE HALF LESS THAN .25 INCH FORWARD OF SECOND CRANKCASE BOLT HOLE (FROM FRONT OF ENGIN	E). NEW ENGINE BEING INSTALLED.				1	L	7	1 	3O	3	O		2A13 	E274				 
1995120800406	19951208	00406	EA 	1995	12	8	95ZZZX6546 	2	19951021	G	8530	LW19001	VALVE 			PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E2A 	41508	EA 					NR 3 CYL EXHAUST	BROKEN 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			CE	05	6932W		1589 			2821290	L1587427A			ENGINE - NR 3 EXHAUST VALVE BROKE (STEM INTACT) CAUSING ENGINE FAILURE AND RESULTNG IN EMERGENCY LANDING/ACCIDENT. ANNUA	L INSPECTION ACCOMPLISHED OCTOBER 6, 1995. HAD NOT FLOWN FROM 6-26-91 THROUGH 6-26-95. FOUR YEARS OF INACTIVE FLIGHT T	IME.				1	L	7	1 	3O	3	O		2A13 	E274				 
1995121800001	19951218	00001	SO 	1995	12	18	95ZZZX6547 	2	19951113	G	7414	6320	MAGNETO 	SLICK 		CESSNA	210 	T210M 	2073451	CE 	CONT 	O520 	TSIO520R 	17040	SO 					ENGINE	COIL FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	6591M	558 			92020065	21061980	522628			MAG FAILURE TRACED TO BAD COIL.						1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995120800407	19951208	00407	SO 	1995	12	8	95ZZZX6548 	2	19951113	G	8530	648044	PISTON 			CESSNA	210 	T210M 	2073451	CE 	CONT 	O520 	TSIO520R 	17040	SO 					NR 4	FAILED 	D				A				UNSCHED LANDING 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			WP	07	6591M	1651 				21061980	522628			LOST OIL PRESSURE AND MADE FORCE LANDING, NO DAMAGE TO AIRCRAFT, PILOT OR PASSENGERS. FOUND PISTON FAILED.						1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995120800408	19951208	00408	SO 	1995	12	8	95ZZZX6549 	1	19950728	G	2913	9667102	PUMP 			PIPER 	PA32 	PA32R300 	7103213	SO 										HYD SYSTEM	DEFECTIVE 	G				O				OTHER 				O			OTHER 			LD	LANDING 	1			WP	07	1942H	5000 				32R7780206				GEAR-UP LANDING DUE TO INTERMITTENT OPERATION OF GEAR HYDRO-PUMP. SUBMITTER RECOMMENDS PUMP GO THROUGH OVERHAUL AT 4,00	0 HRS TIME IN SERVICE.					1	L	7	1 	3O				A3SO 					 
1995120800409	19951208	00409		1995	12	8	95ZZZX6550 	2	19951030	G	7414	1051324	SPRING 		BL5136028 															MAG IMPULSE	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21		1 			L149417DR					MAGNETO IMPULSE FAILED TO OPERATE. ON DISASSEMBLY, IMPULSE SPRING FOUND BROKEN IN TWO PLACES NEAR THE OUTER END. SPRIN	G IS APPARENTLY TOO BRITTLE.																		 
1995120800410	19951208	00410	SO 	1995	12	8	95ZZZX6551 	2	19951107	G	8530		ROCKER SHAFT 			BEECH 	36 	A36 	1151604	CE 	CONT 	O520 	IO520BB 	17032	SO 					NR 2 CYL	BOLT SHEARED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	3853Z					E1836	573570			NR 2 CYLINDER VALVE COVER REMOVED FROM PUSHROD TUBE SEAL REPLACEMENT. FOUND FORWARD ROCKER SHAFT THROUGH-BOLT IN 3 PIEC	ES. BOLT SHEARED FLUSH IN CYL HEAD, ALSO, INSIDE ROCKER SHAFT. APPROX .3125 INCH HOLE IN FWD SHAFT HOLDER WAS FND ENLA	RGED TO .50 INCH. ENG TIME SINCE TOP OVERHAUL, 450 HRS AT WHICH TIME TAPERED ROCKER SHAFTS WERE INSTALLED PER TCM SB. E	NG TT, 2,000 PLUS HRS. CUSTOMER STATED OIL ANALYSIS SHOWED HIGH ALUM AND FERROUS MATERIALS. SUSPECT OVERTORQUING TO BE	 CAUSE OF PROBLEM. REPLACED CYL WITH RE-WORKED CYL. ALSO, INSPECTED REMAINING CYLINDERS, NO DEFECTS NOTED.		1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995120800411	19951208	00411	EA 	1995	12	8	95ZZZX6552 	2	19951101	G	8530	77160S	GUIDE 			MOONEY	M20 	M20M 	5870222	SW 	LYC 	O540 	TIO540AF1A 	41532	EA 					NR 3 EXH VALVE	EXCESS WEAR 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			SW	99	505RD	281 				270143	L937061A			PILOT EXPERIENCED ROUGH ENGINE ON RUN-UP. PERFORMED COMPRESSION TEST AND FOUND CYLINDER NR 3 HAD ZERO COMPRESSION. UPO	N REMOVAL OF CYLINDER, FOUND EXHAUST VALVE MISSING APPROX ONE-THIRD OF FACE AREA. FURTHER INSP REVEALED EXCESSIVE WEAR 	OF GUIDE. OTHER FIVE CYLINDERS HAD EXCESSIVE GUIDE WEAR ALSO. LYCOMING SB NR SB503 ISSUED IN 1992 CALLS FOR REPLACEMEN	T OF EXHAUST GUIDES WITH NEW P/N LW-19001 FOR ENGINE S/N'S THROUGH L-9293-61A. AFFECTED CYLINDERS FALL OUTSIDE OF THIS 	S/N RANGE.		1	L	7	1 	30	3	O	RT	2A3 	E14EA				 
1995120800412	19951208	00412		1995	12	8	95ZZZX6553 	4	19951024	G	2562	3000	ELT 	POINTER 		CESSNA	150 	150M 	2071830	CE 										G-SWITCH	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	63297				321016	15077235				DURING THE ANNUAL INSPECTION REQUIRED BY FAR91.207(D), THE POINTER ELT WOULD NOT OPERATE USING THE G-SWITCH TEST. WHEN 	SWITCHED TO THE 'ON' POSITION, IT WOULD ONLY WORK WHEN THE CASE WAS BUMPED, AND WHEN IT DID WORK, THE OUTPUT WAS WEAK.					1	H	7	1 	3O				3A19 					 
1995120800413	19951208	00413	CE 	1995	12	8	95ZZZX6554 	1	19950913	G	7810	17540071	EXHAUST RISER 			CESSNA	172 	172N 	2072434	CE 										CYL NR 3 EXH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	738HX	2442 				17270000				DURING ROUTINE 100-HOUR INSPECTION, EXHAUST LEAK NOTED FROM CYLINDER NR 3. AFTER REMOVAL OF EXHAUST RISER, A CRACK AND 	SEPARATION ON THE FLANGE WAS DISCOVERED. RISER REMOVED FOR REPAIR. SUSPECT CAUSE MISALIGNED EXHAUST, AGE, FATIGUE. RE	COMMENDATION: INSPECT WITH 10X GLASS AND VISUAL EVERY 50 HOURS.				1	H	7	1 	3O			NT	3A12 					 
1995120800414	19951208	00414	EA 	1995	12	8	95ZZZX6555 	2	19951115	G	8520		CRANKCASE 			PIPER 	PA28 	PA28181 	7102807	SO 	LYC 	O360 	O360A4M 	41514	EA 					NR 1 CYLINDER	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	05	29296	2778 	551 			287990447	L2865836A			DISCOVERED A 3 INCH LONG CRACK IN ENGINE CASE BELOW NR 1 CYLINDER WHILE INVESTIGATING AN OIL LEAK.						1	L	7	1 	3O	3	O		2A13 	E286				 
1995120800415	19951208	00415	CE 	1995	12	8	95ZZZX6556 	1	19950914	G	3230	504501019	TORQUE TUBE 			CESSNA	340 	340A 	2076405	CE 										LT MLG	CRACKED 	H	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	37333	1517 				340A0353				INSPECTION FOUND LT MLG TORQUE TUBE CRACKED. (REPLACED WITH NEW STYLE 5045010-33). SUBMITTER RECOMMENDS DYE CHECK OF A	NY AIRCRAFT OVER 1,000 HOURS WITH OLD STYLE TUBES.					1	L	7	2 	3O				3A25 					 
1995120800416	19951208	00416	SO 	1995	12	8	95ZZZX6557 	2	19950616	G	8540	628760	INDICATOR 		635050A4 	CESSNA	185 	A185E 	2072818	CE 	CONT 	O520 	IO520D 	17032	SO 					ENG TIMING PLATE	DEFECTIVE 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	07	1997U		300 			18501766	175979R			WHILE CHECKING MAGNETO TO ENGINE TIMING, DISCOVERED WHEN THE TIMING MARK ON THE ALTERNATOR DRIVE SHEAVE, P/N 635165, WAS	 LINED UP WITH THE TIMING MARKS ON THE ENGINE TIMING INDICATOR PLATE, THE CRANKSHAFT POSITION WAS 10 DEGREES ADVANCED OF	 THE POSITION INDICATED. THESE TIMING MARKS WERE USED TO SET IGNITION TIMING AND THE TIMING WAS FOUND 10 DEGREES ADVANC	ED FROM ITS NORMAL 22 DEGREE POSITION, RESULTING IN AN UNAIRWORTHY CONDITION. TCM SB M84-8 ADDRESSES THIS PROBLEM BY RE	QUIRING THE INDICATOR PLATE TO BE REMOVED AND THE TIMING PROCEDURE IN SB M94-8 USED INSTEAD.		1	H	7	1 	3O	3	O		3A24 	E5CE				 
1995120800417	19951208	00417	SO 	1995	12	8	95ZZZX6558 	1	19951101	G	5500	4052105	CLEVIS 			PIPER 	J3 	J3 	7100502	SO 										TAIL BRACE	BROKEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	98342	3000 				18513				DURING ANNUAL INSPECTION, FOUND A BROKEN CLEVIS AT THE TOP OF THE LEFT TOP TAIL BRACE WIRE. THE SPECIAL WASHER, P/N 401	31-00, WAS IN PLACE. THE BREAK WAS AT THE INSIDE BOTTOM OF CLEVIS AND HARD TO SEE DURING PRE-FLIGHT INSPECTION. SUBMIT	TER STATED TO REPLACE ALL WIRES WITH NEW.				1	H	7	1 	3O				ATC660 					 
1995120800418	19951208	00418	CE 	1995	12	8	95ZZZX6559 	1	19951108	G	2140	2070171	CONNECTOR 			BEECH 	58 	58 	1152740	CE 										HEATER BLOWER	PINS BURNED 	B	S		VJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	5643C	6534 				TH1573				HEATER BLOWER INOP. FOUND PLUGS P56 AND J56, PINS NR 5 AND NR 9 BURNED/MELTED.						1	L	7	2 	3O				3A16 					 
1995120800419	19951208	00419	CE 	1995	12	8	95ZZZX6560 	1	19951108	G	2140	2070171	CONNECTOR 			BEECH 	58 	58 	1152740	CE 										HEATER BLOWER	PINS BURNED 	B	S		VJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	3149P	8531 				TH1470				HEATER BLOWER INOP. FOUND PLUGS P56 AND J56, PINS NR 5 AND NR 9 BURNED/MELTED.						1	L	7	2 	3O				3A16 					 
1995120800420	19951208	00420	NM 	1995	12	8	95ZZZX6561 	1	19951102	G	5711	20001605	SPAR CAP 			PIPER 	PA60 	PA60600A 	7106002	NM 										LT WING	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	742WP	3500 				600022				DURING A ROUTINE INSPECTION, THE LT WING LOWER SKIN WAS NOTICED CRACKED AFT OF THE LANDING GEAR TRUNNION. FURTHER INVES	TIGATION BY REMOVAL OF SKIN REVEALED THE AFT SPAR WAS CRACKED. SUSPECT CAUSE, HARD LANDING. WING HAD HAD PREVIOUS DAMA	GE HISTORY, FATIGUE. PREVENTION, INSPECTION OF AREAS.				1	M	7	2 	3O			RT	A17WE 					 
1995120800421	19951208	00421	CE 	1995	12	8	95ZZZX6562 	1	19951114	G	5753	35165050606	FLAP 			BEECH 	55 	D55 	1152730	CE 										RT ACT ATTACH	FAILED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	69RP	6802 				TE766				UPON EXITING THE AIRCRAFT, THE WEIGHT OF THE PILOT STANDING ON THE RT FLAP, TORE THE ACTUATOR ATTACH BRACKET, RIPPED THE	 SKIN AND PULLED THE RIB ATTACHMENT OUT OF THE FLAP. THIS CONDITION ALLOWED THE FLAP TO GO TO THE EXTENDED POSTION. IN	-FLIGHT, AN UNNOTICED CRACK IN THE AREA COULD RESULT IN FLAP RETRACTION UNDER THE EXTREME AIR LOADS IN THIS AREA. SUSPE	CT CAUSE, OVER-STRESS OF ACTUATOR ATTACH AREA. WEAK AREA. PREVENTION, MODIFY, BEEF-UP, MORE FREQUENT INSPECTIONS.			1	L	7	2 	3O				3A16 					 
1995120800422	19951208	00422	GL 	1995	12	8	95ZZZX6563 	3	19951116	G	6111	C13019S	CLAMP 			SWRNGN	SA226 	SA226TC 	8780404	SW 						HARTZL	HCB3T	HCB3TN5 	GL 	BLADE	CRACKED 	B	S		CBCR	O				OTHER 				C			F.O.D. 			NR	NOT REPORTED 	1			NM	03		31824	668 		DD7394			BV2031		PROPELLER HIT AN ANTELOPE. CLAMP IS FROM BLADE THAT HAD A SMALL AMOUNT OF DAMAGE ON TRAILING EDGE. THE BLADE THAT TOOK	 THE MAIN HIT, HAD NO CRACKED PARTS.					1	L	7	2 	4T				A8SW 		6	C	P15EA	 
1995120800423	19951208	00423	CE 	1995	12	8	95ZZZX6564 	1	19951025	G	2810	C156001	FUEL CAP 			CESSNA	182 	182G 	2072716	CE 										FUEL TANK	LEAKING 	D				K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			CE	07	2468R					18255568				FUEL CAPS BEGAN LEAKING CAUSING LOSS OF FUEL DURING FLIGHT. REPLACED WITH FUEL CAPS BY MONARCH AIR TYPE SA2376CE.						1	H	7	1 	3O			NT	3A13 					 
1995120800424	19951208	00424		1995	12	8	95ZZZX6565 	4	19951122	G	6122	F824L	GOVERNOR 	HARTZL 																PROPELLER	FAILED 	B			ME4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19					B1312T					UPON INSPECTION, INTERNAL PARTS OF BODY AND BASE OF GOVERNOR WERE FOUND DISINTEGRATED. GOVERNOR HAS BEEN CONDEMNED AND 	SCRAPPED.																		 
1995120800425	19951208	00425	SO 	1995	12	8	95ZZZX6566 	2	19951122	G	7414	0703200MJ3A	FILTER 			CESSNA	310 	310P 	2074238	CE 	CONT 	O470 	IO470VO 	17026	SO 					MAG P-LEAD	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	55DP					310P0038				FOUND MAGNETO FILTER DEFECTIVE WHEN SUBJECT TO MAGNETO P-LEAD VOLTAGE OR HIGH TENSION LEAD TESTER VOLTAGE. REGULAR OHM 	CHECK DID NOT PICK UP DEFECT. ENGINE WOULD RUN INTERMITTENTLY BAD ON THIS MAGNETO. THIS IS AN AFTER-MARKET PART INSTAL	LED IN LINE WITH P-LEADS TO REDUCE MAGNETO P-LEAD VOLTAGE INTERFERENCE.				1	L	7	2 	3O	3	O		3A10 	3E1				 
1995120800426	19951208	00426	EU 	1995	12	8	95ZZZX6567 	1	19951030	G	7921	TB0954010001	BAFFLE ASSY 			SOCATA	TB9 	TB9 	8680694	EU 										OIL COOL MOUNT	BROKEN 	B			DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	140ER	224 				1529				DURING A 100-HOUR INSPECTION, THE OIL COOLER WAS FOUND SUPPORTED BY ONLY TWO BOLTS. THE OIL COOLER MOUNTING BAFFLE WAS 	COMPLETELY BROKEN AT TWO OF THE MOUNT HOLES AND THE OTHER TWO WERE SEVERELY CRACKED. THIS COULD CAUSE OIL COOLER TANK L	EAKAGE AND POSSIBLE ENGINE FAIILURE. NEW BAFFLE INSTALLED.				1	L	7	1 	3O			NT	AS1EU 					 
1995120800427	19951208	00427	CE 	1995	12	8	95ZZZX6568 	1	19951102	G	2810	1221118	FUEL CAP 			CESSNA	210 	T210H 	2073438	CE 										FUEL TANK	LEAKING 	B			APJR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	6935R					T2100335				FUEL CAPS LEAKING WATER, REPLACED WITH BARTON FUEL CAPS, STC SA2456CE.						1	H	7	1 	3O				3A21 					 
1995120800428	19951208	00428		1995	12	8	95ZZZX6569 	2	19951024	G	7414	ES10682056	DISTRIBUTOR BLK 	BENDIX 	D3000 															BEARING PLATE	CRACKED 	B			KC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03					2020967					DURING INSPECTION OF MAG, FOUND DISTRIBUTOR BLOCK CRACKED AT BEARING BORE. ALSO, NOTED THAT BREAKER ADJUSTING SCREW INS	ERTS WERE PULLING OUT ALLOWING BREAKERS TO LOOSEN. THIS COULD CAUSE MAG TO STOP FUNCTIONING. NOTE THAT THIS IS AN ELEC	TRO SYSTEMS FAA-PMA DISTRIBUTOR BLOCK ASSEMBLY.																	 
1995021000263	19950210	00263	CE 	1995	2	10	95ZZZX657 	2	19950105	G	7414	10357586	DISTRIBUTOR 		S6LN25P 	MOONEY	M20 	M20K 	5870220	SW 	CONT 	O360 	TSIO360MB 	17025	CE 					MAG GEAR	TEETH FAILED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			NE	03	261CB	447 			1238756D	250391	317176			ENGINE DEVELOPED VIBRATION ON TAKEOFF. AFTER LANDING AND MAG CHECK, LT MAGNETO DEAD. DISASSEMBLY FOUND DISTRIBUTOR GEA	R WITH EIGHT TEETH MISSING. FOUND ALL TEETH IN MAGNETO HOUSING. MAGNETO DISTRIBUTOR GEAR DATED 9-13-91 O/H BY MIDSTATE	S AIRCRAFT ENGINE, TULSA, OK. SERVICEABLE TAG W/O NR 910519.				1	L	7	1 	3O	3	O		2A3 	E9CE				 
1995120800429	19951208	00429	EA 	1995	12	8	95ZZZX6570 	2	19951018	G	8530		CYLINDER 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					NR 2	CRACKED 	D				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			GL	03	757BG	4744 	1358 			15279605	RL1524115			LOSS OF POWER AND ENGINE ROUGHNESS WAS REPORTED. UPON INSPECTION, CYLINDER NR 2 WAS FOUND TO HAVE LOW COMPRESSION. FUR	THER INSPECTION LED TO FINDING A CRACK APPROXIMATELY ONE-HALF WAY AROUND THE CIRCUMFERENCE OF THE CYLINDER BETWEEN THE F	INS AT THE JUNCTION OF THE HEAD AND BARREL. CYLINDER WAS REPLACED AND ENGINE WAS RETURNED TO SERVICE. CYLINDER WAS BOR	ED .010 INCH.			1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995120800430	19951208	00430	CE 	1995	12	8	95ZZZX6571 	1	19951113	G	3230	520496FG	ROD END 			CESSNA	177 	177RG 	2073709	CE 										MLG ACTUATOR	BROKEN 	D				O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			SW	15	2075Q	2700 				177RG0475				DURING FLIGHT, BOTH MAIN LANDING GEARS DROPPED TO TRAIL. GEAR-UP LANDING WAS MADE. ON MAINTENANCE CHECK, THE ROD END O	N THE MAIN GEAR ACTUATOR CYLINDER WAS FOUND BROKEN.					1	H	7	1 	3O				A20CE 					 
1995120800431	19951208	00431	CE 	1995	12	8	95ZZZX6572 	1	19951109	G	3710	211CC	PUMP 	AIRBORNE 		CESSNA	150 	152 	2071835	CE 										VACUUM SYSTEM	SHAFT SHEARED 	C			CDIS	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	67322	18 				15285274				INSTALLED A RAPCO RE-BUILT VACUUM PUMP. CLEANED ALL LINES AND CHANGED BOTH FILTERS. PUMP FAILED AFTER 18 HOURS TIME IN	 SERVICE. FAILURE WAS DUE TO DRIVESHAFT SHEARING.					1	H	7	1 	3O			NT	3A19 					 
1995120800432	19951208	00432	EA 	1995	12	8	95ZZZX6573 	2	19951107	G	8530		VALVE 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					EXH VLV GUIDE	STUCK 	D				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			EA	05	738BF	3751 	1264 			17269843	L663676T			SOME POWER LOSS WAS NOTED AFTER TAKEOFF WHEN EXHAUST VALVE STUCK. SUBMITTER SUGGESTS LYCOMING SERVICE BULLETINS BE COMP	LIED WITH.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995120800433	19951208	00433	CE 	1995	12	8	95ZZZX6574 	1	19951107	G	5312		BULKHEAD 			CESSNA	180 	180 	2072602	CE 										FS 172.0	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	2311C	3349 				30611				DURING 100-HOUR INSPECTION, CRACK WAS FOUND AT THE TOP CENTER FUSELAGE BULKHEAD IN BEND RADIUS AT FS 172.0 WHERE DORSAL 	FIN ATTACH FITTING IS RIVETED. AIRCRAFT WAS USED FOR SKYDIVING OPERATIONS AND ESTIMATE LONG, FULL POWER OPERATION AND P	ROPELLER VIBRATION CAUSED CRACK. SUBMITTER RECOMMENDS THOROUGH INSPECTION EACH 100 HOURS OF AREA. AN APPROVED CHANNEL 	DOUBLER WAS INSTALLED FOR STRENGTH.			1	H	7	1 	3O			NC	5A6 					 
1995120800434	19951208	00434	EA 	1995	12	8	95ZZZX6575 	2	19950925	G	7322	MA4SPA	CARBURETOR TUBE 			CESSNA	172 	172 	2072402	CE 	LYC 	O320 	O320E2D 	41508	EA 					ACCEL DISCHARGE	MISSING 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			GL	15	12805		2125 		BL2010704	17262275	L3514627A			PILOT SAID THE ENGINE HAD A LOSS OF POWER AND IT WAS HARD TO START. ENGINE WAS REMOVED FOR OVERHAUL WITH 2125 TSO. WHE	N THE CARBURETOR WAS REMOVED, IT WAS NOTICED THE ACCELERATOR DISCHARGE TUBE WAS MISSING. SUBMITTER SUSPECTED REASON FOR	 LOSS OF TUBE WAS CARBURETOR FIRE.				1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995120800435	19951208	00435	CE 	1995	12	8	95ZZZX6576 	1	19951031	G	8011	MHB4016R	STARTER 			CESSNA	172 	172P 	2072436	CE 										NOSE PIECE	BOLTS FAILED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	5227K		892 		8V000423	17274020				DURING NORMAL MAINTENANCE, THE HEADS OF THE BOLTS SECURING THE STARTER MOTOR TO THE NOSE PIECE OF BENDIX WERE NOTED MISS	ING. AFTER REMOVAL AND DISASSEMBLY, INSPECTION CONCLUDED THE BOLTS NOT OF AIRCRAFT GRADE AND WERE TIGHTENED SO AS TO ST	ART A CRACK IN SHANK. INSPECTION WITH A 10X GLASS SHOWS CORROSION ON THREE-FOURTHS OF THE CRACKS SURFACE INDICATING THE	 CRACK OCCURRED SOME TIME AGO (PROBABLY AT OVERHAUL). SUBMITTER STATED IF MOTOR HAD COME LOOSE, FIRE DUE TO ARCING MAY 	HAVE OCCURRED. POOR QUALITY CONTROL.		1	H	7	1 	3O			NT	3A12 					 
1995120800436	19951208	00436	GL 	1995	12	8	95ZZZX6577 	3	19951110	G	6114	E4344	HUB 													MCAULY	3AF32C	3AF32C87 	GL 	NR 3 SOCKET	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15		2568 	1171 		781226			781226		PERFORMING SB 205B, EDDY CURRENT CHECK OF THREADS IN HUB FOR BLADES, INDICATION WAS A CRACK. VISUALLY SAW A SCRATCH. E	XCEPT IN ONE AREA, IT WAS SLIGHTLY OPEN.															5	C	P22EA	 
1995120800437	19951208	00437	NM 	1995	12	8	95ZZZX6578 	1	19951106	G	5315		FLOOR BEAM 			BOEING	727 	727225 	1384077	NM 										BS 1130	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	353PA	58777				20622				SEVERAL AREAS OF CORROSION WERE FOUND ON UPPER CAP OF THE BS 1130 FLOOR BEAM. THE DEFECTS WERE FOUND DURING A CPCP TASK	 CARD C53-224-03, PART 2. SUSPECT LEAKAGE FROM LAV'S AND NOT SEALED PROPERLY.					2	L	7	3 	4F				A3WE 					 
1995120800438	19951208	00438	NE 	1995	12	8	95ZZZX6579 	2	19951117	G	7510	37B201215P10	HOSE 			LEAR 	25 	25D 	5170514	CE 	GE 	CJ610 	CJ6108 	30006	NE 					LT NAC AI TUBE	FAILED 	D				K				NONE 				O			OTHER 			LD	LANDING 	1			SW	15	1U	4798 				371	E311328A			PILOT STATED LT NACELLE ANTI-ICE INOP AND TRIPPING CIRCUIT BREAKER ON LANDING. AFTER REMOVAL OF TOP COWLING, FOUND HOSE	 CONNECTING ANTI-ICE TUBE AND ANTI-ICE TEE TUBE WAS TORN IN HALF CAUSING EXPELLED BLEED AIR TO DISCONNECT ANTI-ICE VALVE	 POWER WIRE FROM CANNON PLUG AND GROUND TO ENGINE. ALSO, ANTI-ICE TUBE WAS CRACKED AT FLANGE TO ANTI-ICE VALVE.				2	L	7	2 	4J	4	J		A10CE 	1E16				 
1995120800439	19951208	00439	EU 	1995	12	8	95ZZZX6580 	1	19951003	G	7714	0177555050	TACHOMETER BOX 			SNIAS 	350 	AS350B 	8680801	EU 										AFT CARGO	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			EA	09	5771C		32 			1369				BLEED VALVE WOULD NOT CLOSE DUE TO FAILURE OF TACHOMETER BOX. THIS AIRCRAFT AND OTHERS HAVE EXPERIENCED AN INCREASE IN 	TACHOMETER BOX FAILURES RECENTLY. ACFT TT, 7,404.1 HOURS.					1	G	7	1 	3U				H9EU 					 
1995120800440	19951208	00440	EU 	1995	12	8	95ZZZX6581 	1	19951003	G	7714	017755517	TACHOMETER BOX 			SNIAS 	350 	AS350B 	8680801	EU 										AFT CARGO	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	5771C					1369				BLEED VALVE WOULD NOT STAY CLOSED ON ENGINE. BLEED VALVE IS CONTROLLED BY AN ELECTRO-PNEUMATIC SIGNAL. TACHOMETER BOX 	CONTROLS THE ELECTRICAL SIGNAL AND, IN THIS CASE, TACHOMETER BOX FAILED INTERNALLY. ACFT TT, 7,372.2 HOURS.					1	G	7	1 	3U				H9EU 					 
1995120800441	19951208	00441	EU 	1995	12	8	95ZZZX6582 	1	19950814	G	7931	DK040	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										OIL SYSTEM	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105NG	65 			6323	S632				TRANSMITTER INTERMITTENTLY PEGS OUT. REMOVED AND REPLACED.						1	G	7	2 	3U				H3EU 					 
1995120800442	19951208	00442	EU 	1995	12	8	95ZZZX6583 	1	19950809	G	2430	117188001	BONDING CABLE 			BOLKMS	117 	BK117B1 	5626012	EU 										DC SYSTEM	END BROKEN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117LU	68 				7144				BONDING CABLE END BROKEN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995120800444	19951208	00444	SW 	1995	12	8	95ZZZX6585 	1	19950825	G	2900	222080134101	BRACE 			BELL 	222 	222U 	1182140	SW 										HYD INSTALL	BROKEN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	219HM	105 				47573				BROKEN BRACE. REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW 					 
1995120800445	19951208	00445	SW 	1995	12	8	95ZZZX6586 	1	19951019	G	2510	222320823125	RESTRAINT 			BELL 	206 	206B 	1181511	SW 										COCKPIT	EXCESS WEAR 	B			WG3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	33TV	979 				4306				REMOVED RESTRAINT ASSY DUE TO EXCESS WEAR ON BOLT ASSY AFTER 978.8 HOURS OF USE. INSTALLED NEW RESTRAINT ASSY, P/N 222-	320-823-125 INTO AIRCRAFT.					1	G	7	1 	3U				H2SW 					 
1995120800446	19951208	00446	SW 	1995	12	8	95ZZZX6587 	1	19951019	G	3340	A402AR	STROBE LENS 			BELL 	206 	206B 	1181511	SW 										STROBE	DEFECTIVE 	B			WG3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	33TV	979 				4306				UPON INSPECTION, FOUND P/N A402A-R REFLECTIVE LENS INSIDE AT STROBE LENS HAD CHAFED THROUGH ALLOWING REFLECTIVE LENS TO 	DROP DOWN ONTO THE STROBE FLASH TUBE ASSY AT 978.8 HOURS. INSTALLED NEW STROBE LENS ASSY P/N A402A-R.					1	G	7	1 	3U				H2SW 					 
1995120800447	19951208	00447	EU 	1995	12	8	95ZZZX6588 	1	19950920	G	3340	A7151	LIGHT HOUSING 			BOLKMS	117 	BK117A4 	5626017	EU 										LIGHTS	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	313LF	88 				7138				LIGHT HOUSING MOUNTING BRACKET CRACKED. REMOVED AND REPLACED, 2 EACH.						1	G	7	2 	3U				H13EU 					 
1995120800448	19951208	00448	EU 	1995	12	8	95ZZZX6589 	1	19950723	G	6730	7012409901	ACTUATOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										DUPLEX PITCH	ERROR CODE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	1 			91050153	7505				DUPLEX PITCH ACTUATOR HAS ERROR CODES OF E28, E29, AND E30. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995021000265	19950210	00265	SO 	1995	2	10	95ZZZX659 	1	19950112	G	3222	6705403	TRUNNION 			PIPER 	PA32 	PA32RT300 	7103215	SO 										NLG DOWN LINK	DAMAGED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	39478	1591 				32R7885221				DURING ANNUAL INSP., ABNORMAL PLAY NOTICED AT MOUNT POINT OF THE TRUNNION (UPPER LEFT). AFTER REMOVAL OF TRUNNION ASSY,	 UPPER LT BEARING FOUND SEPARATED UNDER THE FLANGE. FURTHER DAMAGE FOUND ON LT SIDE OF DOWNLOCK BRACE ASSY BOSS. NO HA	RD LANDINGS REPORTED AND THE ONLY GEAR WORK PERFORMED RECENTLY WAS SB955 (206 HOURS EARLIER) AND INSTALLATION OF THE ENG	INE MOUNT DRAG LINK WAS INSPECTED FOR ALIGNMENT/BINDING. NO PROBLEMS NOTED. IT IS UNCLEAR AS TO WHERE THE DAMAGE BEGAN	, AT THE BEARING OR AT THE DOWNLOCK LINK BOSS. RECOMMEND ANY TRUNNION PLAY BE CAREFULLY INSPECTED IN AREAS MENTIONED.		1	L	7	1 	3O				A3SO 					 
1995120800449	19951208	00449	EU 	1995	12	8	95ZZZX6590 	1	19950911	G	3310	56D011	SWITCH 			BOLKMS	BK117 	BK117C1 	5626025	EU 										OVERHEAD	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	770 				7505				OVERHEAD SWITCH RATTLES. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995120800450	19951208	00450	EU 	1995	12	8	95ZZZX6591 	1	19950725	G	6320	360A32109820	SEAL SEAT 			AEROSP	SA365 	SA365N1 	8680668	EU 										M/R GEARBOX	EXCESS WEAR 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	365SC	333 				6298				SEAL SEAT HAS EXCESSIVE WEAR. RMA NR R003777. REMOVED AND REPLACED.						1	G	7	2 	3U				H10EU 					 
1995120800451	19951208	00451	EU 	1995	12	8	95ZZZX6592 	1	19950729	G	5530	11730610	FIN 			BOLKMS	117 	BK117B1 	5626012	EU 										VERTICAL	DAMAGED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	460H	50 			109IND	7142				VERTICAL FIN DAMAGED (HOLE IN FIN).						1	G	7	2 	3U				H13EU 					 
1995120800452	19951208	00452	NE 	1995	12	8	95ZZZX6593 	2	19951009	G	7250	430136201	BEARING 			BELL 	222 	222U 	1182140	SW 	LYC 	LTS101	LTS101650B1 	41560	NE 					TURBINE NR 2	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	6992	609 			31482	47521	LE47231			UPON DISASSEMBLY OF POWER SECTION FOR REPAIR, NR 2 INNER BEARING WAS FOUND TO HAVE 11 OF 20 CAGE SEPARATORS CRACKED ON F	ORWARD SIDE OF AFT 'WINGS'. OHI WO NR 96-894. INSTALLED SERVICEABLE BEARING.					1	G	7	2 	3U	3	U		H9SW 	E5NE				 
1995120800453	19951208	00453	SW 	1995	12	8	95ZZZX6594 	1	19951009	G	2840	222375023107	INDICATOR 			BELL 	222 	222 	1182122	SW 										COCKPIT MGT	READS LOW 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911MK	134 			013	47515				INDICATOR READS 10 PERCENT LOW, NR 2 ENGINE.						1	G	7	2 	3U				H9SW 					 
1995120800454	19951208	00454	EU 	1995	12	8	95ZZZX6595 	1	19950816	G	7931	6607A2114	SWITCH 			BOLKMS	105 	BO105LSA3 	5626020	EU 										OIL PRESSURE	FAULTY 	B			TI1R	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			SW	05	911SV	228 			S46317	2033				AED AND PRESSURE LIGHT ON. REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU 					 
1995120800564	19951208	00564	CE 	1995	12	8	95ZZZX6596 	1	19951030	G	2460		BUS TIE 			BEECH 	1900 	1900C 	1154161	CE 										LT DC BUS	OPENED 	C	L	A		O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			CE	07	160AM					UC160				DURING CRUISE FLIGHT, LT BUS TIE OPEN WARNING FOLLOWED BY LT DC GENERATOR FAIL WARNING. CAPTAIN LOST HEADSET AUDIO WHIC	H IS POWERED FROM LT GENERATOR BUS. THIS OCCURRENCE CAUSED LOSS OF COMMUNICATION BETWEEN COCKPIT CREW AT A TIME CREW CO	ORDINATION IS CRITICAL. COMMUNICATION IS LOST DUE TO LOSS OF DC BUS POWER. SUBMITTER STATES BUS TIE PROTECT DEVICES TE	ND TO BE OVERLY SENSITIVE IN OPERATION.			2	L	7	2 	4T			RT	A24CE 					 
1995120800565	19951208	00565	CE 	1995	12	8	95ZZZX6597 	1	19951103	G	3233	NAS464P7L53	BOLT 			LEAR 	55 	55LEAR 	5170702	CE 										NLG ACT ATTACH	BROKEN 	B		A	CW1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	723H	7297 				90				UPON TOWING OF AIRCRAFT, EXCESS MOVEMENT OF NOSE STRUT WAS OBSERVED. FURTHER INVESTIGATION FOUND UPPER NOSE GEAR ACTUAT	OR ATTACH BOLT BROKEN. BOLT RETURNED TO MFG FOR ANALYSIS.					2	L	7	2 	4F				A10CE 					 
1995120800566	19951208	00566	EU 	1995	12	8	95ZZZX6598 	1	19951106	G	5610	53430242	WINDSHIELD 	PPG 		ISRAEL	1121 	1121B 	0142010	EU 										COPILOT	SHATTERED 	B		A	FE6R	O				OTHER 				O			OTHER 			CR	CRUISE 	1			NM	07	122ST				011218069	122				THE COPILOT'S WINDSHIELD SHATTERED AT ALTITUDE. DAMAGE WAS CONTAINED IN THE INNER HEATING ELEMENT PORTION OF THE OUTER 	WINDSHIELD. THE PRESSURE VESSEL WAS NOT COMPROMISED AS IT IS THE INNER WINDSHIELD. OUTER WINDSHIELD WAS INSTALLED IN D	ECEMBER, 1994. IT IS NOT POSSIBLE TO DETERMINE WHETHER THE WINDSHIELD WAS NEW AT THAT TIME. UNABLE TO DETERMINE CAUSE 	OF WINDSHIELD FAILURE.			2	M	7	2 	4J				A2SW 					 
1995021000266	19950210	00266	SO 	1995	2	10	95ZZZX660 	1	19950101	G	5751	A258	BRACKET 			GULSTM	AA5 	AA5 	0631410	SO 										AILERON HINGE	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	525RB	1072 				AA50760				DURING POST-PURCHASE INSPECTION OF AMERICAN GENERAL AIRCRAFT SB-185, CONTROLS WERE CHECKED FOR WEAR IN BUSHING AND HINGE	 BRACKETS WERE FOUND CRACKED. THESE HAVE THE AILERON TRAVEL STOPS ATTACHED. SUSPECT WIND SHIPPING AILERONS COULD HAVE 	CRACKED THEM.				1	L	7	1 	3O				A16EA 					 
1995120800568	19951208	00568	EU 	1995	12	8	95ZZZX6600 	1	19951114	G	3231	F10A191008	BRACKET 			AMD 	FALC10	FALCON10 	2730101	EU 										LT MLG DOOR UPLK	CRACKED 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	36BG					190				WHILE PERFORMING A-CHECK GENERAL VISUAL INSPECTION ITEM ON THE MLG DOORS, NOTICED A CRACK IN THE LOWER RADIUS OF THE LT 	GEAR DOOR UPLOCK BRACKET. THE CRACK WOULD NOT BE NORMALLY VISIBLE UNLESS LOOKING THROUGH THE HOLE IN THE DOOR INNER SKI	N, AT THE LOWER OUTBOARD SIDE OF THE BRACKET. SUSPECT CAUSES; DEFECTIVE PART OR IF THE STOP P/N F10A191008003 WAS TIGHT	ENED WITH SHIM P/N F10A191008004 NOT INSTALLED, IT COULD HAVE POSSIBLY CAUSED THE CRACK.			2	L	7	2 	4F				A33EU 					 
1995120800569	19951208	00569	WP 	1995	12	8	95ZZZX6601 	2	19951111	G	7250	31038391	SEAL 		31070852 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					1ST STG TURB	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		10244			0233151178		P70004			DURING HOT SECTION INSPECTION, FOUND SEAL FLANGE CRACKED 8 PLACES. SUBMITTER STATED THIS IS A CRITICAL MAIN ROTATING GR	OUP LIFE-LIMITED COMPONENT. LIFE-LIMIT IS 10,000 CYCLES. SUBMITTER STATES THIS IS THE 20TH MALFUNCTION/DEFECT REPORT S	UBMITTED REGARDING THIS PART. TOTAL CYCLES, 10,279.									4	T			E4WE				 
1995120800570	19951208	00570	CE 	1995	12	8	95ZZZX6602 	1	19950926	G	5711	5011100033	SPAR CAP 			BEECH 	90 	65A90 	1152908	CE 										RT OTBD WING	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	623AW	9076 				LJ282				FOUND BLISTERS ON TOP, RIGHT OUTBOARD SPAR CAP AT STA 102 AND STA 94.8 DURING DAILY INSPECTION. AFTER PICKING AT BLISTE	RS, FOUND WHITE POWDER. CONSULTED BEECH CUSTOMER SUPPORT. REMOVED WING FROM AIRCRAFT, SEPARATED LEADING EDGE WING AND 	BOX WING FROM SPAR. FOUND SIX AREAS OF DEFOLIATING 1G CORROSION. AREA NOT VISIBLE UNLESS WING IS SEPARATED. AD 89-25-	10 ACCOMPLISHED 11/94.			1	L	7	2 	3T				3A20 					 
1995120800571	19951208	00571	SO 	1995	12	8	95ZZZX6603 	1	19951110	G	3097		WIRE 			GULSTM	G1159 	G1159A 	3970109	SO 										WINDSHIELD HEAT	SHORTED 	B			AOSR	K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			IN	INSP/MAINT 	1			EA	11	40CH	4935 				377				SMOKE WAS NOTED IN FRONT ENTRANCE AREA DURING GROUND RUN. FLOOR WAS REMOVED. WINDSHIELD HEATING WIRES WERE SHORTED, ME	LTED, AND BURNED. CIRCUIT BREAKER NR 80A COVERS INSPECTION FOR THIS PROBLEM. ASC234 IS REPAIR FOR THIS PROBLEM. EVALU	ATION STILL IN PROGRESS.				2	L	7	2 	4F			 	A12EA 					 
1995120800572	19951208	00572	CE 	1995	12	8	95ZZZX6604 	1	19951106	G	2822	2017002	PUMP 	TRW 		RKWELL	NA265 	NA26540 	6402608	CE 										FUEL BOOST	SHORTED 	H				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	09	301NT		64 		1001252D	282009				BOOST PUMP CAUSES CIRCUIT BREAKER TO TRIP IN-FLIGHT. SUSPECT INTERNAL SHORT OR BAD BEARINGS.						2	L	7	2 	4J				A2WE 					 
1995120800573	19951208	00573	CE 	1995	12	8	95ZZZX6605 	1	19951106	G	2822	2017002	PUMP 			RKWELL	NA265 	NA26540 	6402608	CE 										FUEL BOOST	FAILED 	H				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	09	31NT		67 		100C642D	282019				BOOST PUMP CAUSES CIRCUIT BREAKER TO TRIP IN-FLIGHT. SUSPECT CAUSE, INTERNAL SHORT OR BAD BEARINGS.						2	L	7	2 	4J				A2WE 					 
1995120800574	19951208	00574	CE 	1995	12	8	95ZZZX6606 	1	19951106	G	2822	217002	PUMP 	TRW 		RKWELL	NA265 	NA26540 	6402608	CE 										FUEL BOOST	DEFECTIVE 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	09	311NT				10C1492D	282019				THIS BOOST PUMP WAS RECEIVED FROM THE VENDOR WITH A FRESH OVERHAUL. ON OPS CHECK, THE PUMP HAD A RUBBING NOISE. THE SC	REEN WAS REMOVED AND THE IMPELLER WAS FOUND RUBBING THE WALL ON ONE SIDE AND THE HOUSING BASE ON THE OTHER SIDE. EITHER	 THE SHAFT IS BENT OR THE BEARING IS IMPROPERLY POSITIONED.				2	L	7	2 	4J				A2WE 					 
1995120800575	19951208	00575	CE 	1995	12	8	95ZZZX6607 	1	19951106	G	7897	V315	WIRE 			CESSNA	500 	560CESSNA 	2076750	CE 										RT TR DEPLOY	BROKEN 	D		A		O				OTHER 				O			OTHER 			TX	TAXI/GRND HDL 	1			SO	01	1000W					5600204				WHEN CREW PERFORMED TAXI CHECKS, IT WAS NOTED RT THRUST REVERSER DID NOT DEPLOY. SUBMITTER STATED CAUSED BY BROKEN WIRE	 TO RT THRUST REVERSER DEPLOY SWITCH, P/N V3-15. SWITCH SHOULD BE RE-DESIGNED TO ILLIMINATE SOLDERING THE WIRE TO SWIT	CH AND PREVENTING WIRE HARDENING OR MOUNTING SWITCH IN SUCH A MANNER TO PREVENT THE WIRE FROM BEING CAUGHT AND BROKEN BY	 THRUST REVERSER CONTROL OPERATION.			2	L	7	2 	4F			RT	A22CE 					 
1995120800576	19951208	00576	EU 	1995	12	8	95ZZZX6608 	1	19951018	G	5610	T67M17031	CANOPY 			SLNSBY	T67 	T67M260 	8323006	EU 										COCKPIT	FAILED 	H		A		K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	17	3047K	344 				2147				EIGHTEEN MINUTES INTO FLIGHT THE CANOPY OPENED AND SHATTERED. OTHER THAN CANOPY, VERY MINOR DAMAGE DONE TO AIRFRAME. 1	5MM HOLE - STAB, RT SIDE TOP. 15MM HOLE - ELEV RT SIDE TOP. 10MM SCRATCH RT SIDE, MID-RUDDER CANOPY DECK FAIRING CHIPP	ED. AIRFRAME CHIPPED ON BOTH SIDES AT CANOPY STAYS. NO CAUSE AT THIS TIME.				1	L	7	1 	3O			NT	A73EU 					 
1995120800577	19951208	00577	EA 	1995	12	8	95ZZZX6609 	2	19951016	G	8530	LW11633	CYLINDER 			CESSNA	150 	A152 	2071836	CE 	LYC 	O235 	O235L2C 	41505	EA 					NR 4 HEAD	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	4973B		50 			15283733				INSTALLED CERMICHROME OHL CYLINDERS AT OVERHAUL. AT 50 SMOH, DETECTED A LEAK IN THE NR 4 CYLINDER-HEAD-BARRREL JUNCTION	. UPON REMOVAL, OBSERVED A 11 INCH CIRCUMFERENTIAL CRACK 1 INCH FROM THE TOP OF THE BARREL AT THE 6:00 POSITION.					1	H	7	1 	3O	3	O		3A19 	E223				 
1995120800578	19951208	00578	SO 	1995	12	8	95ZZZX6610 	2	19951116	G	8530		CYLINDER 		653445 	BEECH 	36 	A36 	1151604	CE 	CONT 	O550 	IO550B 		SO 					NR 4 CYL EXH VLV	GUIDE WORN 	D				O				OTHER 				E	R	J	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	WARNING INDICATION 	CR	CRUISE 	1			SW	15	36CL	740 				E1980	281855R			PILOT REPORTED LOSS OF RPM, ENGINE ROUGHNESS IN CRUISE FLIGHT, CONFIRMED BY EXTREMELY HOT INDICATION ON AIRCRAFT EGT SCA	NNER. NR 6 CYLINDER POSITION, FOUND NR 6 CYLINDER EXHAUST VALVE BURNED THROUGH, SEAT DETERIORATED BEYOND LIMITS. REMOV	ED NR 4 CYLINDER TO FACILITATE REMOVAL OF NR 6 CYLINDER. FOUND EXHAUST GUIDE WORN BEYOND LIMITS ON NR 4 CYLINDER. INST	ALLED NEW FACTORY SUPPLIED CYLINDER NR 6 POSITION AND REWORKED AND INSTALLED NEW GUIDE NR 4 CYLINDER. ENGINE TEST RUN A	ND FLOWN.		1	L	7	1 	3O	3	O		3A15 	E3SO				 
1995120800579	19951208	00579	SO 	1995	12	8	95ZZZX6611 	2	19951116	G	8530		VALVE 			BEECH 	36 	A36 	1151604	CE 	CONT 	O550 	IO550B 		SO 					NR 6 CYLINDER	BURNED 	D				O				OTHER 				E	R	J	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	WARNING INDICATION 	CR	CRUISE 	1			SW	15	36CL	740 				E1980	281855R			PILOT REPORTED LOSS OF RPM, ENGINE ROUGHNESS IN CRUISE FLIGHT, CONFIRMED BY EXTREMELY HOT INDICATION ON AIRCRAFT EGT SCA	NNER. NR 6 CYLINDER POSITION, FOUND NR 6 CYLINDER EXHAUST VALVE BURNED THROUGH, SEAT DETERIORATED BEYOND LIMITS. REMOV	ED NR 4 CYLINDER TO FACILITATE REMOVAL OF NR 6 CYLINDER. FOUND EXHAUST GUIDE WORN BEYOND LIMITS ON NR 4 CYLINDER. INST	ALLED NEW FACTORY SUPPLIED CYLINDER NR 6 POSITION AND REWORKED AND INSTALLED NEW GUIDE NR 4 CYLINDER. ENGINE TEST RUN A	ND FLOWN.		1	L	7	1 	3O	3	O		3A15 	E3SO				 
1995120800580	19951208	00580	EA 	1995	12	8	95ZZZX6612 	2	19951114	G	7414	D6LN3000	MAGNETO 			PIPER 	PA32 	PA32RT300 	7103215	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					BASE FLANGE	DEFECTIVE 	E				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	05	3421W	400 				32R7885276				'ACCESSORY CASE OIL LEAK'. A FACTORY LYCOMING ENGINE HAD A PERSISTENT SLIGHT OIL SEEP AT THE MAGNETO BASE. AFTER REMOV	AL, IT WAS FOUND TO HAVE A FLAW IN THE APPARENT CASTING. A LOW SPOT IN THE GASKET AREA ALLOWED OIL TO SEEP BY. PART WA	S REPLACED FOR THIS REASON AS WELL AS FLANGE/CLAMP WEAR.				1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995120800581	19951208	00581	EA 	1995	12	8	95ZZZX6613 	2	19951113	G	8550	60746	PUMP 			CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					ENGINE OIL	FAILED 	D				A				UNSCHED LANDING 				J			WARNING INDICATION 			CL	CLIMB 	1			NM	09	21329					17263931	L3919527A			ENGINE LOST OIL PRESSURE ON DEPARTURE AND RETURNED TO THE AIRPORT. NO INCIDENT OCCURRED. ENGINE WOULD NOT MAKE FULL RP	M. PROPELLER STOPPED WHEN POWER REDUCED TO IDLE. SUBMITTER STATED ENGINE WAS OPERATED MOST OF ITS LIFE WITHOUT AN OIL 	FILTER. RECOMMEND MANDATORY FILTER INSTALLATIONS FOR PROPER ENGINE LIFE. FOUND BROKEN OIL PUMP GEAR, SHEARED PUMP DRIV	E, LOST OIL PRESSURE. SPUN ROD BEARINGS. ENGINE TSMOH, 1,970 HOURS.			1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995120800582	19951208	00582	CE 	1995	12	8	95ZZZX6614 	1	19951101	G	7922	53E19600	VALVE 			CESSNA	172 	172F 	2072414	CE 	LYC 	O360 	O360* 	41514	EA 					THERMO BYPASS	DEFECTIVE 	B			PB2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	5700R					17253350	L1395036A			DURING OVERHAUL, THERMOSTATIC BYPASS WAS INSPECTED. IN ADDITION TO CRIMP NUT BEING LOOSE, SNAP RING THAT HOLDS BODY OFF	 VALVE WAS FOUND TO HAVE EXCESSIVE PLAY. DISSASSEMBLY SHOWED SNAP RING WORN APPROXIMATELY 50 PERCENT AND BRASS PORTION 	OF PLUNGER THAT IT SEATS ON IS BROKEN.				1	H	7	1 	3O	3	O	NT	3A12 	E286				 
1995120800583	19951208	00583	NM 	1995	12	8	95ZZZX6615 	1	19951025	G	2820		CONNECTOR 			PIPER 	PA60 	PA60600 	7106001	NM 										LT ENG CROSSFLOW	CORRODED 	D				O				OTHER 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			GL	07	6076L					600713796122				LEFT ENGINE SHUT DOWN IN-FLIGHT AFTER GOING FROM CROSSFLOW BACK TO NORMAL. FOUND CORROSION ON CROSSFLOW CANNON PLUG CLE	AN. OPS CHECKS GOOD.					1	M	7	2 	3O			RT	A17WE 					 
1995120800584	19951208	00584	EA 	1995	12	8	95ZZZX6616 	2	19951016	G	8530	LW11633	CYLINDER 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					ENGINE	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	6401M		350 			15284710				INSTALLED CERMICHROME OHL CYLINDERS AT OVERHAUL. AT 350 SMOH, DETECTED AN OIL LEAK FROM THE HEAD-BARREL-JUNCTION. UPON	 REMOVAL, DETECTED A CIRCUMFERENTIAL CRACK 1.50 INCHES LONG, ONE INCH FROM THE TOP OF THE BARREL AT THE 12:00 POSITION.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995120800585	19951208	00585	EA 	1995	12	8	95ZZZX6617 	2	19951023	G	8520		CONNECT ROD 			PIPER 	PA28 	PA28R180 	7102809	SO 	LYC 	O360 	IO360B1E 	41514	EA 					NR 4 CYLINDER	BOLT FAILED 	G			QFGS	O				OTHER 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			SW	15	7471J					28R30824	553251A			NR 4 CONNECTING ROD CAP CAME OFF. ENGINE FAILED. ENGINE TEAR DOWN REVEALED THAT ONE NUT CAME OFF OF ONE CONNECTING ROD	 BOLT AND THE OTHER CONNECTING ROD BOLT BROKE. IT WAS ALSO NOTED THAT ONE CONNECTING ROD BOLT WAS MISSING FROM THE NR 2	 CONNECTING ROD. THAT NUT WAS FOUND IN SUMP IN SEVERAL PIECES. THE BOLT WAS NOT FOUND. ENGINE TIMES WERE 1,800 HOURS 	SMOH, 1,000 HOURS STOH.			1	L	7	1 	3O	3	O		2A13 	1E10				 
1995120800586	19951208	00586		1995	12	8	95ZZZX6618 	4	19951108	G	6122	A20734	FLYWEIGHT BASE 		DCFS290D9TE 	CESSNA	402 	402C 	207590R	CE 						MCAULY	3AF32C	3AF32C505 	GL 	PROP GOVERNOR	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	88TN	4527 			810777	402C0621		815140		FOUND GOVERNOR FLYWEIGHT BASE CRACKED.						1	L	7	2 	3O				A7CE 		5	C	P22EA	 
1995120800587	19951208	00587	SO 	1995	12	8	95ZZZX6619 	1	19951101	G	5500	4052105	CLEVIS 			PIPER 	J3 	PA11 	7101102	SO 										TAIL BRACE WIRE	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	4964M	3000 				11450				DURING ANNUAL INSPECTION, FOUND TOP CLEVIS OF THE RT TAIL BRACE WIRE BROKEN. THE SPECIAL WASHER, P/N 40131-00, WAS IN P	LACE. THIS BRAKE WAS ON THE OUTSIDE OF CLEVIS AND EASY TO SEE. ALL THESE OLD TAIL BRACE WIRES AND ENDS WILL BE REPLACE	D WITH COMPLETE NEW UNITS FROM UNIVAIR CORPORATION.				1	H	7	1 	3O				A691 					 
1995120800588	19951208	00588	GL 	1995	12	8	95ZZZX6620 	2	19951124	G	7250	6895021	NOZZLE 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					TURB NR 1	CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V		520 		145104	490487D	CAE830976			REPLACED NR 1 NOZZLE FOR CRACKS AND BURNING. PART SENT IN ON ALLISON 250 REPORT NR 159680.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995120800589	19951208	00589	EU 	1995	12	8	95ZZZX6621 	1	19951109	G	6720	350A33214501	ROD 			SNIAS 	350 	AS350B 	8680801	EU 										T/R PITCH CONT	WORN 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	842BP	1471 			2081	2037				ON 100-HOUR INSPECTION, LOOSENESS OF BEARING WAS FOUND. CAUSE - NORMAL WEAR.						1	G	7	1 	3U				H9EU 					 
1995120800590	19951208	00590	GL 	1995	12	8	95ZZZX6622 	2	19951122	G	7250	6898735	TURBINE 		CAT36372 	HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					NR 2	NOZZLE CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V	3776 	520 			490487D	CAE830976			WHILE CHANGING NR 1 NOZZLE, IT WAS DISCOVERED THE NR 2 NOZZLE WAS CRACKED. UNIT WAS SENT IN FOR REPAIR.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995021000269	19950210	00269		1995	2	10	95ZZZX663 	4	19950119	G	2312	KY196	TRANSCEIVER 			HUGHES	369 	369D 	4470706	WP 										DISPLAY	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y				10917	500716D				LOWER PORTION OF DIGITAL DISPLAY CUTS OFF DURING OPERATION. REPLACED UNIT AND SENT IN FOR REPAIR.						1	G	7	1 	3U				H3WE 					 
1995121500142	19951215	00142	CE 	1995	12	15	95ZZZX6645 	1	19951015	G	3240	11480083	BRAKE 			BEECH 	1900 	1900C 	1154161	CE 										NR 1	WORN 	A			GPPA	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			O			OTHER 			TO	TAKEOFF 	1			CE	09	34010					UC3				IAD/EWR - AIRCRAFT ON TAKEOFF ROLL PULLED HARD TO LEFT. RETURNED TO GATE. UPON INSPECTION, FOUND NR 1 TIRE WORN. REPL	ACED TIRE, ALSO BRAKE WAS STICKING. AIRCRAFT BEING FERRIED TO GSO FOR INSTALLATION OF NR 1 BRAKE ASSY. REMOVED AND REP	LACED NR 1 BRAKE AND BEARINGS.				2	L	7	2 	4T			RT	A24CE 					 
1995121500211	19951215	00211		1995	12	15	95ZZZX6648 	4	19950921	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					15928					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500212	19951215	00212		1995	12	15	95ZZZX6649 	4	19950704	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					56483					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500213	19951215	00213		1995	12	15	95ZZZX6650 	4	19950830	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					29335					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500214	19951215	00214		1995	12	15	95ZZZX6651 	4	19950907	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					99822					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500215	19951215	00215		1995	12	15	95ZZZX6652 	4	19950901	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					19368					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500216	19951215	00216		1995	12	15	95ZZZX6653 	4	19950922	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					79491					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500217	19951215	00217		1995	12	15	95ZZZX6654 	4	19950920	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					39344					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500218	19951215	00218		1995	12	15	95ZZZX6655 	4	19951009	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					30180					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500219	19951215	00219		1995	12	15	95ZZZX6656 	4	19950724	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					21998					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500220	19951215	00220		1995	12	15	95ZZZX6657 	4	19950825	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14605					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500221	19951215	00221		1995	12	15	95ZZZX6658 	4	19950607	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					10088					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500222	19951215	00222		1995	12	15	95ZZZX6659 	4	19950901	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					10022					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500223	19951215	00223		1995	12	15	95ZZZX6660 	4	19950922	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					15924					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500224	19951215	00224		1995	12	15	95ZZZX6661 	4	19950922	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					33065					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500225	19951215	00225		1995	12	15	95ZZZX6662 	4	19950817	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					16136					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500226	19951215	00226		1995	12	15	95ZZZX6663 	4	19950726	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					51690					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500227	19951215	00227		1995	12	15	95ZZZX6664 	4	19950920	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					98989					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500228	19951215	00228		1995	12	15	95ZZZX6665 	4	19950725	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					76618					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500229	19951215	00229		1995	12	15	95ZZZX6666 	4	19950719	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					73179					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500230	19951215	00230		1995	12	15	95ZZZX6667 	4	19950920	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					22322					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500231	19951215	00231		1995	12	15	95ZZZX6668 	4	19950623	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					66205					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500232	19951215	00232		1995	12	15	95ZZZX6669 	4	19950921	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					69571					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500233	19951215	00233		1995	12	15	95ZZZX6670 	4	19950911	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					71772					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500234	19951215	00234		1995	12	15	95ZZZX6671 	4	19950912	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18834					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500235	19951215	00235		1995	12	15	95ZZZX6672 	4	19950714	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					11321					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500236	19951215	00236		1995	12	15	95ZZZX6673 	4	19950725	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					73083					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500237	19951215	00237		1995	12	15	95ZZZX6674 	4	19950808	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					C11745					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500238	19951215	00238		1995	12	15	95ZZZX6675 	4	19950918	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					90372					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500239	19951215	00239		1995	12	15	95ZZZX6676 	4	19950914	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					66595					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500240	19951215	00240		1995	12	15	95ZZZX6677 	4	19950724	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					44378					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500241	19951215	00241		1995	12	15	95ZZZX6678 	4	19951005	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					30287					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500242	19951215	00242		1995	12	15	95ZZZX6679 	4	19951005	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					19844					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500244	19951215	00244	SO 	1995	12	15	95ZZZX6681 	2	19951116	G	8520	633403	CONNECT ROD 			CESSNA	207 	207 	2073602	CE 	CONT 	O520 	IO520F 	17032	SO 					NR 2 CYLINDER	FAILED 	D				O				OTHER 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			NM	01	9641M	1116 				20700714	291167R			NR 2 CONNECTING ROD FAILED. THIS FAILURE CAUSED A HOLE IN CRANKCASE AND OIL BEING SPRAYED EVERYWHERE.						1	H	7	1 	3O	3	O		A16CE 	E5CE				 
1995121500245	19951215	00245	SO 	1995	12	15	95ZZZX6682 	1	19951027	G	7921	8529245	OIL COOLER 			PIPER 	PA28 	PA28236 	7102815	SO 										BOTTOM SEAM	CRACKED 	B	L		CQVR	O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			CE	01	2204A	1924 	18 			287911006				OIL COOLER SENT FOR REPAIR ON MOUNTING FLANGE. RECEIVED AND REINSTALLED ON 10-12-95. ON 10-22-95, ON A TRIP, THE COOLE	R SPLIT AND DEVELOPED A LEAK. REPAIR STATION FOUND THAT INSTALLER OVERTORQUED THE BOTTOM FITTING. SUBMITTER DISAGREES 	WITH THAT FINDING, BUT FEELS THAT IF IT IS A PROBLEM, PEOPLE NEED TO KNOW.				1	L	7	1 	3O				2A13 					 
1995121500246	19951215	00246	CE 	1995	12	15	95ZZZX6683 	1	19951026	G	3211	1058100203	FITTING 			BEECH 	76 	76 	1153005	CE 										RT MLG STRUT	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	5116M	6150 				ME39				UPON SERVICING THE RIGHT MAIN GEAR STRUT, A VISIBLE CRACK WAS SPOTTED IN THE WEB OF THE SUPPORT FOR THE SHOCK STRUT. UP	ON REMOVAL, THE CONNECTOR WAS FOUND TO BE SLIGHTLY WARPED.					1	L	7	2 	3O				A29CE 					 
1995121500247	19951215	00247	GL 	1995	12	15	95ZZZX6684 	1	19951026	G	2720	2027220600	PEDAL 			DIAMON	DA20A1	DA20A1 	05626UX	GL 										PILOT RUDDER	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	442PC	154 				10042				PILOT COMPLAINED OF POOR BRAKING ACTION. INSPECTION DISCOVERED THAT BOTH THE PILOT'S RUDDER PEDALS WERE BENT BACK AT TH	E OUTSIDE. REMOVAL OF THE PEDALS DISCLOSED THE PEDALS WERE CRACKED AT THE WELD. SUBMITTER SUGGESTS CAUSE IS (WEAK DESI	GN), AND THE FACT THAT THE PEDALS ARE ADJUSTED BY PUSHING THEM WITH THE FEET. ALSO, POOR PLACEMENT OF THE PILOT'S FEET 	ON THE PEDALS MAY ALLOW MORE FORCE TO BE APPLIED TO THE WEAK SIDE OF THE PEDAL.			1	L	7	1 	3O			NT	TA4CH 					 
1995121500248	19951215	00248	CE 	1995	12	15	95ZZZX6685 	1	19951120	G	7120	628257	BRACKET 			CESSNA	182 	182Q 	2072732	CE 										ENG LT REAR MT	CRACKED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	759DB	587 				18265901				DURING INSPECTION, FOUND ENGINE LT REAR MOUNT BRACKET CRACKED. TCM REP STATES NO FAILIURE HISTORY ON THIS PART.						1	H	7	1 	3O			NT	3A13 					 
1995121500249	19951215	00249	EA 	1995	12	15	95ZZZX6686 	2	19951006	G	7414	M3548	ROTATE SHAFT 	SLICK 	4370 	HUGHES	269 	269C 	4470504	WP 	LYC 	O360 	HO360* 	41514	EA 					RT MAGNETO	SHEARED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	61442	108 			95060282	0002	L3448236A			PILOT REPORTED RIGHT MAGNETO WAS INOP. REMOVED MAGNETO AND DISASSEMBLED. FOUND SHAFT END WITH CAM AND ROTOR GEAR SHEAR	ED. LOCATION OF SHEAR WAS AT BASE OF CAM SLOT. POSSIBLE MANUFACTURING DEFECT AS CAUSE.					1	G	7	1 	3O	3	O		4H12 	E286				 
1995121500250	19951215	00250	GL 	1995	12	15	95ZZZX6687 	1	19951025	G	3213		GEAR LEG 			AMTR 	MSTGMI	MUSTANGMIDGT		GL 										RT MLG ATTACH	BROKE 	H				O				OTHER 				O			OTHER 			AP	APPROACH 	1			NE	05	4701	1475 				124				NORMAL APPROACH TO RUNWAY (95 MPH). ACFT STALLED OVER NUMBERS APPROXIMATELY 2 FEET OVER RUNWAY. ON CONTACT, RIGHT LAND	ING GEAR BROKE OFF AT THE ATTACH POINT THROUGH 2 OF 4 BOLT HOLES. BOTH LANDING GEARS WERE STEVE WHITMAN TYPE, STEEL, AP	ROXIMATELY 5 INCHES TAPER TO 3 INCHES. BOTH GEAR LEGS HAD APPROXIMATELY 3,500 LANDINGS.				1	L	7	1 	3O				EXPA1L71					 
1995121500251	19951215	00251	SW 	1995	12	15	95ZZZX6688 	1	19951025	G	6330	222031605109	FLEXTURE 			BELL 	222 	222U 	1182140	SW 										M/R TRANSMISSION	SEPARATION 	B			EFLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21		1500 			BR973R					FLEXTURE MATERIAL SEPARATING/DEBONDING FROM END FITTINGS. SUBMITTER STATED FLEXTURES DO NOT SEEM TO HOLD UP UNDER NORMA	L CONDITIONS AND OPERATION.					1	G	7	2 	3U				H9SW 					 
1995121500252	19951215	00252	SW 	1995	12	15	95ZZZX6689 	1	19951025	G	6330	222031605109	FLEXTURE 			BELL 	222 	222U 	1182140	SW 										M/R TRANSMISSION	SEPARATION 	B			EFLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21		1500 			BR1027R					FLEXTURE MATERIAL SEPARATING/DEBONDING FROM END FITTINGS. SUBMITTER STATED FLEXTURES DO NOT SEEM TO HOLD UP UNDER NORMA	L CONDITIONS AND OPERATION.					1	G	7	2 	3U				H9SW 					 
1995121500253	19951215	00253	SW 	1995	12	15	95ZZZX6690 	1	19951025	G	6330	222031605109	FLEXTURE 			BELL 	222 	222U 	1182140	SW 										M/R TRANSMISSION	SEPARATION 	B			EFLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21		1500 			BR1052R					FLEXTURE MATERIAL SEPARATING/DEBONDING FROM END FITTINGS. SUBMITTER STATED FLEXTURES DO NOT SEEM TO HOLD UP UNDER NORMA	L CONDITIONS AND OPERATION.					1	G	7	2 	3U				H9SW 					 
1995121500254	19951215	00254	SW 	1995	12	15	95ZZZX6691 	1	19951015	G	6220	222310115117	BEARING 			BELL 	222 	222U 	1182140	SW 										M/R	DEBONDED 	B			EFLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21		957 			BW556					BEARING HAS A RETIREMENT LIFE OF 5,000 HOURS. ITEMS HAVE EXCESSIVE DELAMINATION AND DEBONDING. ITEMS IN SERVICE FROM 4	-5 YEARS.					1	G	7	2 	3U				H9SW 					 
1995121500255	19951215	00255	SW 	1995	12	15	95ZZZX6692 	1	19951015	G	6220	222310115117	BEARING 			BELL 	222 	222U 	1182140	SW 										M/R	DEBONDED 	B			EFLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21		1067 			BW704					BEARING HAS A RETIREMENT LIFE OF 5,000 HOURS. ITEMS HAVE EXCESSIVE DELAMINATION AND DEBONDING. ITEMS IN SERVICE FROM 4	-5 YEARS.					1	G	7	2 	3U				H9SW 					 
1995121500256	19951215	00256	SW 	1995	12	15	95ZZZX6693 	1	19951025	G	6220	222310115119	BEARING 			BELL 	222 	222U 	1182140	SW 										M/R	DEBONDED 	B			EFLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21		1067 			BW799					BEARING WAS ON CONDITION LIFE. ITEMS HAVE FAILED DUE TO DEBONDING OR DETERIORATION AND EXTRUSION OF THE RUBBER. ITEMS 	IN SERVICE 4-5 YEARS.					1	G	7	2 	3U				H9SW 					 
1995121500257	19951215	00257	SW 	1995	12	15	95ZZZX6694 	1	19951025	G	6220	222310115119	BEARING 			BELL 	222 	222U 	1182140	SW 										M/R	DEBONDED 	B			EFLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21		1067 			BW798					BEARING WAS ON CONDITION LIFE. ITEMS HAVE FAILED DUE TO DEBONDING OR DETERIORATION AND EXTRUSION OF THE RUBBER. ITEMS 	IN SERVICE 4-5 YEARS.					1	G	7	2 	3U				H9SW 					 
1995121500258	19951215	00258	SW 	1995	12	15	95ZZZX6695 	1	19951025	G	6220	222310115119	BEARING 			BELL 	222 	222U 	1182140	SW 										M/R	DEBONDED 	B			EFLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21		1154 			BW871					BEARING WAS ON CONDITION LIFE. ITEMS HAVE FAILED DUE TO DEBONDING OR DETERIORATION AND EXTRUSION OF THE RUBBER. ITEMS 	IN SERVICE 4-5 YEARS.					1	G	7	2 	3U				H9SW 					 
1995121500311	19951215	00311	SO 	1995	12	15	95ZZZX6697 	1	19950925	G	2710	159CM102191	PUSHROD 			GULSTM	G159 	G159 	3952202	SO 										LT AILERON	CORRODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	307EL	16685				161				PUSHROD WAS CORRODED FROM INSIDE OUT, ABOUT MID-WAY DOWN LENGTH OF PUSHROD. CAUSED BY LACK OF CORROSION PROTECTION ON I	NSIDE OF PUSHROD. FOUND WHEN PUSHROD WAS REMOVED FROM C/W NEW NDT INSPECTION REQUIREMENT. ON VISUAL INSPECTION, FOUND 	.1250 INCH DIAMETER HOLE ON PUSHROD. HOLE WAS NOT VISIBLE FROM INSPECTING PANEL OR AILERON GAP. SUBMITTER RECOMMENDS A	FTER C/W NDT INSPECTION, PUSHROD SHOULD BE FILLED WITH LPS-3 OR OTHER CORROSION INHIBITOR, AND DETAILED INSPECTION DURIN	G WING INSPECTION.		2	L	7	2 	4T				1A17 					 
1995121500312	19951215	00312		1995	12	15	95ZZZX6698 	4	19950922	G	3418	600591997	ACCELEROMETER 	GULTON 		CNDAIR	CL600 	CL6001A11 	1900302	EA 										STALL WARNING	STUCK 	B			SH5R	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			NE	03	1045X				1387	1038				UNIT CAUSES FLASHING STALL PROTECT FAIL LIGHT TO ILLUMINATE. VOLTAGE MEASURED AT 11 VDC, SHOULD BE ZERO MVDC. UNIT WIL	L NOT UNSTICK.					2	L	7	2 	4F			RT	A21EA 					 
1995121500313	19951215	00313	CE 	1995	12	15	95ZZZX6699 	1	19951018	G	2750	65650261	PUSHROD TUBE 			CESSNA	500 	S550 	2076607	CE 										RT INBD FLAP	HOLE RUSTED 	B			IW1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	29AU	3356 				S5500019				DURING COURSE OF ROUTINE INSPECTION, SUSPICIOUS 'BUBBLES' ON PUSH/PULL TUBE WERE POKED AT WITH SCRIBE AND WENT THROUGH T	UBE. AFTER SCRAPING AWAY PAINT AND SCALE, FOUND LARGE OBLONG HOLE RUSTED THROUGH BOTTOM OF PUSH/PULL ROD NEAR INBOARD E	ND OF RIGHT INBOARD FLAP PUSH/PULL ROD. HOLE APPROXIMATELY .3750 INCH BY 2.25 INCHES. REPLACED WITH NEW PART. SUBMITT	ER RECOMMENDS A ONE-TIME ALERT SERVICE INFO LETTER ADDRESSING S550 AND 560 AIRCRAFT FOR ONE-TIME INSPECTION AND POSSIBLE	 INTERNAL EXAMINATION OF TUBE.		1	L	7	2 	4F			RT	A22CE 					 
1995021000417	19950210	00417		1995	2	10	95ZZZX670 	4	19950123	G	2340	107857D	AMPLIFIER BOX 			HUGHES	369 	369D 	4470706	WP 										INTERCOM SYSTEM	FAILED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R	7069 				1151D				PILOT WOULD KEY HIS ICS AND THE ENTIRE SYSTEM WENT HOT AND WOULD STAY HOT UNTIL THE PILOT DEPRESSED THE RADIO TRANSMIT S	WITCH. REPLACED ICS AMP BOX.					1	G	7	1 	3U				H3WE 					 
1995121500314	19951215	00314	NE 	1995	12	15	95ZZZX6700 	2	19950519	G	8530		CYLINDER 			AIRTRC	AT300 	AT301 	0390103	SW 	PWA 	R1340 	R1340AN1 	52016	NE 					NR 4	CRACKED 	H				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			AG	AGRICULTURE 	1			SW	11	3655Z					3010299				THE PILOT COMPLETED THE FIRST SWATH AND INITIATED A CLIMB TO REVERSE DIRECTION. WHILE THE AIRPLANE WAS IN A NOSE HIGH A	TTITUDE AT ABOUT 200 FEET ABOVE THE GROUND, THE ENGINE LOST POWER. DURING THE FORCED LANDING TO A WHEAT FIELD, THE AIRC	RAFT SUSTAINED STRUCTURAL DAMAGE TO THE RIGHT WING AND THE EMPENNAGE. POST-ACCIDENT EXAMINATION OF THE ENGINE BY AN FAA	 INSPECTOR REVEALED A CRACK IN THE NR 4 CYLINDER.			1	L	7	1 	3R	3	R		A9SW 	5E2				 
1995121500315	19951215	00315		1995	12	15	95ZZZX6701 	4	19950731	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A29300					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500316	19951215	00316		1995	12	15	95ZZZX6702 	4	19950714	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					41850					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500317	19951215	00317		1995	12	15	95ZZZX6703 	4	19950727	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					10583					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500318	19951215	00318		1995	12	15	95ZZZX6704 	4	19950908	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					66707					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500319	19951215	00319		1995	12	15	95ZZZX6705 	4	19950908	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					22673					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500320	19951215	00320		1995	12	15	95ZZZX6706 	4	19950727	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					14412					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500321	19951215	00321		1995	12	15	95ZZZX6707 	4	19950908	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					69552					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500322	19951215	00322		1995	12	15	95ZZZX6708 	4	19950829	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					91086					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500323	19951215	00323		1995	12	15	95ZZZX6709 	4	19950921	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18818					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995021000418	19950210	00418	WP 	1995	2	10	95ZZZX671 	1	19950123	G	6220	369D2100521	SUPPORT 			HUGHES	369 	369D 	4470706	WP 										M/R HUB FAIRING	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R	7069 				1151D				ON PRE-FLIGHT, PILOT NOTICED A 'DIMPLE' AROUND AN ATTACHMENT SCREW ON THE MAIN ROTOR HUB FAIRING. SUBSEQUENT INSPECTION	 REVEALED THE TIP OF THE 'STAR' LEG WAS BENT CHANGING ITS ANGLE AND THE SCREW WOULD DIMPLE THE FAIRING IN AS IT WAS TORQ	UED. REPLACED FAIRING SUPPORT.				1	G	7	1 	3U				H3WE 					 
1995121500324	19951215	00324		1995	12	15	95ZZZX6710 	4	19950927	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					49874					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500325	19951215	00325		1995	12	15	95ZZZX6711 	4	19950720	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					12580					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500326	19951215	00326		1995	12	15	95ZZZX6712 	4	19950926	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					28057					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500327	19951215	00327		1995	12	15	95ZZZX6713 	4	19950829	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					72563					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500328	19951215	00328		1995	12	15	95ZZZX6714 	4	19950711	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					94564					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500329	19951215	00329		1995	12	15	95ZZZX6715 	4	19950616	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					16997					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500330	19951215	00330		1995	12	15	95ZZZX6716 	4	19950714	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					29983					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500331	19951215	00331		1995	12	15	95ZZZX6717 	4	19950725	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					39512					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500332	19951215	00332		1995	12	15	95ZZZX6718 	4	19950526	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					92835					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500333	19951215	00333		1995	12	15	95ZZZX6719 	4	19950818	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					49095					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500334	19951215	00334		1995	12	15	95ZZZX6720 	4	19950511	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					26457					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500335	19951215	00335		1995	12	15	95ZZZX6721 	4	19950501	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					49755					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500336	19951215	00336		1995	12	15	95ZZZX6722 	4	19950524	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					68328					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500337	19951215	00337		1995	12	15	95ZZZX6723 	4	19950512	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					A2595					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500338	19951215	00338		1995	12	15	95ZZZX6724 	4	19950510	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					29631					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500339	19951215	00339		1995	12	15	95ZZZX6725 	4	19950503	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					93486					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500340	19951215	00340		1995	12	15	95ZZZX6726 	4	19950522	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					34518					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500341	19951215	00341		1995	12	15	95ZZZX6727 	4	19950524	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					16036					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500342	19951215	00342		1995	12	15	95ZZZX6728 	4	19950714	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					18832					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500343	19951215	00343		1995	12	15	95ZZZX6729 	4	19950726	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					51968					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995021000420	19950210	00420		1995	2	10	95ZZZX673 	4	19950124	G	3453	8010900	ANTENNA 			GULSTM	G159 	G159 	3952202	SO 										LORAN	DEFECTIVE 	B			VIB3	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	3NA					092				NR 1 COMM NOISY IN PRECIPITATION. THE NR 1 COMM WOULD BECOME UNREADABLE IN LIGHT RAIN. TESTED AIRCRAFT WITH DAYTON GRA	NGER TESTER AND FOUND LORAN ANTENNA SOURCE OF NOISE IN COMM. REMOVED AND REPLACED WITH HIGH SPEED BLADE, PN 14663-03. F	LIGHT TESTED AND PROBLEM CORRECTED.				2	L	7	2 	4T				1A17 					 
1995121500344	19951215	00344		1995	12	15	95ZZZX6730 	4	19950828	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					66993					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500345	19951215	00345		1995	12	15	95ZZZX6731 	4	19950823	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					74127					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500346	19951215	00346		1995	12	15	95ZZZX6732 	4	19950620	G	2562	ELT10	ELT 	NARCO 																G-SWITCH	MALFUNCTION 	B			DV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17					51904					UNIT WAS RETURNED FOR RECERTIFICATION TEST PER SB NR ELT-14. UNIT WAS FOUND TO MALFUNCTION DURING 'G-FORCE' ACTIVATION 	TEST DUE TO WHAT APPEARS TO BE A LACK OF REQUIRED MAINTENANCE. FUTURE MALFUNCTIONS COULD BE MINIMIZED BY C/W SB NR ELT-	14 WHICH WAS MANDATED APRIL 21, 1986.																	 
1995121500443	19951215	00443	SO 	1995	12	15	95ZZZX6733 	1	19951115	G	5330		SKIN 			PIPER 	PA32 	PA32300 	7103212	SO 										NEAR RT FIREWALL	CRACKS 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	6868D					3240608				NUMEROUS INSTANCES OF LOOSE RIVETS, AND CRACKS ON AIRFRAME WITH APPROXIMATELY 8 INCHES RADIUS OF LOWER FORWARD CORNER OF	 NOSE BAGGAGE DOOR. SUBMITTER HAS SEEN SEVERAL FIELD REPAIRS, USUALLY A DOUBLER/PATCH ON NOSE PORTION OF AIRFRAME. MOS	T PREVALENT ON OLD AIRPLANES OPERATED UNDER FAR 135.				1	L	7	1 	3O				A3SO 					 
1995122700003	19951227	00003	CE 	1995	12	27	95ZZZX6734 	1	19951116	G	2131		CONTROL 			CESSNA	421 	421C 	2076016	CE 										AIR TEMP PRESS	BINDING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	331JH					421C0037				NUMEROUS INSTANCES OF PRESSURE AIR TEMPERATURE CONTROLS BINDING OR FAILING WHEN COCKPIT KNOB TURNED TO VARY AIR TEMPERAT	URE FOR COMFORT. HEAT EXCHANGER SHUTTERS BIND UP AND STAYS IN ONE POSITION. SUBMITTER SUGGESTS PART NEEDS REDESIGN; MA	INTENANCE PROCEDURES COULD SPECIFY MORE EFFECTIVE LUBRICATION.				1	L	7	2 	3O				A7CE 					 
1995121500444	19951215	00444	CE 	1995	12	15	95ZZZX6735 	1	19951114	G	2730	04112891	BRACKET 			CESSNA	150 	152 	2071835	CE 										ELEV BELLCRANK	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	757YQ	10794				15280113				CRACKS WERE FOUND AT THE LOWER, MOST FORWARD LOCATION OF BRACKET ASSEMBLY FOR THE ELEVATOR BELLCRANK.						1	H	7	1 	3O			NT	3A19 					 
1995121500446	19951215	00446	SO 	1995	12	15	95ZZZX6737 	1	19951031	G	3230	452334	ROD END 		9686002 	PIPER 	PA44 	PA44180 	7104402	SO 										RT MLG	BROKEN 	B		A	OG5R	A				UNSCHED LANDING 				J			WARNING INDICATION 			CL	CLIMB 	1			GL	21	852ND	4105 				4495006				WHEN GEAR WAS RETRACTED, RIGHT MAIN GEAR INDICATOR REMAINED ON. NORMAL EXTENSION PERFORMED. INSPECTION REVEALED ACTUAT	OR TO DRAG/SIDE BRACE ROD END BROKEN OFF. INSTALLED AND RIGGED NEW ROD END. THIS IS SECOND OCCURRENCE BY THIS OPERATOR	 OF 9 AIRCRAFT OF THIS TYPE.				1	L	7	2 	3O				A19S0 					 
1995121500448	19951215	00448	GL 	1995	12	15	95ZZZX6739 	3	19951016	G	6114	E4344	HUB 			CESSNA	340 	340CESSNA 	2076404	CE 						MCAULY	3AF32C	3AF32C87 	GL 	NR 2 SOCKET	CRACKED 	B			IWLR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	765LT	5961 				3400181		765548		INSPECTION FOUND NR 2 BLADE SOCKET WITH .50 INCH LONG CRACK AT EDGE OF BLADE SOCKET, ON OUTSIDE OF HUB, HORIZONTAL TO BL	ADE.					1	L	7	2 	3O				3A25 		5	C	P22EA	 
1995021000270	19950210	00270	CE 	1995	2	10	95ZZZX674 	1	19950101	G	2910	2307024406	TUBE 			LEAR 	24 	24D 	5170311	CE 										HYD SYSTEM	RUPTURED 	H		A		A				UNSCHED LANDING 				J	K		WARNING INDICATION 	FLUID LOSS 		CR	CRUISE 	1			SO	17	157AG	12469				252				AFTER DEPARTURE FROM FXE, ONE HOUR INTO FLIGHT, A/C LOST HYDRAULIC PRESSURE AND LT MAIN GEAR EXTENDED AT 410. PILOT RED	IRECTED FLIGHT TO FLL FOR LANDING FOLLOWING EMERGENCY PROCEDURES. EXTENDED GEAR USING BLOW-DOWN PROCEDURES. GEAR EXTEN	DED AND AIRCRAFT LANDED SAFELY. FAILURE OF HYDRAULIC PRESSURE WAS DUE TO AIRCRAFT TUBING SPLIT IN A BEND LOCATION JUST 	AFTER HYDRAULIC ACCUMULATOR.			2	L	7	2 	4J				A10CE 					 
1995121500449	19951215	00449	SO 	1995	12	15	95ZZZX6740 	1	19951117	G	7922	75944	VALVE 			PIPER 	PA28 	PA28181 	7102807	SO 										THERMO BYPASS	DEFECTIVE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	47907	1675 				287890150				INSPECTION OF VERNATHERM VALVE PER SB FOUND VALVE UNSERVICEABLE. SUBMITTER STATED 80 PERCENT OF THESE VALVES INSPECTED 	HAVE FAILED SB S18B. SUBMITTER RECOMMENDS TO HAVE AN AD ADDRESS THIS.					1	L	7	1 	3O				2A13 					 
1995121500450	19951215	00450	GL 	1995	12	15	95ZZZX6741 	3	19951110	G	6114		HUB 													MCAULY	2A34C	D2A34C58 	GL 	BLADE THREADS	CRACKED 	B			FG6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	07							694244		ROUTINE OVERHAUL FOUND HUB CRACKED IN BLADE RETENTION THREADS.																5	C	P3EA	 
1995121500451	19951215	00451	CE 	1995	12	15	95ZZZX6742 	1	19951121	G	8120	56501241	SUPPORT 			CESSNA	414 	414A 	2075907	CE 	CONT 	O520 	TSIO520J 	17040	SO 					TURBO	CRACKED 	B			FE6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	414GG	2642 				414A0335	20837472J			AFT END OF BRACKET CRACKED 1.5 INCHES OF THE 1.75 INCH WIDTH. AFT END OF BRACKET IS SLOTTED, MAY HAVE BEEN INSTALLED WI	TH A PRELOAD. SUBMITTER STATED TO TIGHTEN FORWARD BOLTS, LET AFT END CENTER BEFORE TIGHTENING.					1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995121500453	19951215	00453		1995	12	15	95ZZZX6744 	4	19951102	G	2562	DMELT6	ELT 	DORNEMARGLN 		CESSNA	210 	P210N 	2073454	CE 										G-SWITCH	MALFUNCTION 	B			ONFR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	999KM	1800 			39742	P21000387				WHEN DOING AN ANNUAL INSPECTION, THE ELT WOULD WORK IN THE ON POSITION, BUT NOT IN THE AUTO POSITION. BATTERY IS GOOD T	O APRIL, 1997. INSPECTION WAS DONE PER FAR 91:207 AND/OR AS CLOSE TO IT.					1	H	7	1 	3O				3A21 					 
1995121500454	19951215	00454	SO 	1995	12	15	95ZZZX6745 	2	19951019	G	8530	SA534610	SEAL 			BEECH 	35 	V35A 	1151544	CE 	CONT 	O470 	IO470* 	17026	SO 					NT 5 CYL SHROUD	LEAKS 	B			HI1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NE	05	168M	5 				D8762				SHORTLY AFTER REPLACING A REPAIRED NR 5 CYLINDER, OIL LEAKS DEVELOPED AROUND OUTBOARD ENDS OF SHROUD TUBES. COMPARISON 	TO ORIGINAL TCM PARTS SHOWED REPLACEMENT SEAL TO BE LARGER IN OUTSIDE DIAMETER CAUSING SEAL NOT TO PROPERLY FIT IN MACHI	NED RECESS CAUSING LEAKS.				1	L	7	1 	3O	3	O		3A15 	E1CE				 
1995121500455	19951215	00455	SO 	1995	12	15	95ZZZX6746 	1	19951101	G	7120		MOUNT BOLTS 			PIPER 	PA28 	PA28181 	7102807	SO 										ENGINE LOWER	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	9900K					287890198				DURING ANNUAL, FOUND LOWER ENGINE MOUNT BOLTS LOOSE.						1	L	7	1 	3O				2A13 					 
1995121500456	19951215	00456	SO 	1995	12	15	95ZZZX6747 	1	19951101	G	5711		SPAR 			PIPER 	PA28 	PA28181 	7102807	SO 										FWD OF AFT SEAT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	9900K					287890198				DURING REPAINT, FOUND EARLY CORROSION INSIDE SPAR CENTER SECTION, JUST FORWARD OF REAR SEATS.						1	L	7	1 	3O				2A13 					 
1995121500457	19951215	00457	SO 	1995	12	15	95ZZZX6748 	1	19951101	G	2434		ALTERNATOR 			PIPER 	PA28 	PA28181 	7102807	SO 										ENGINE MOUNT	BROKEN LUG 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	9900K					287890198				CHRYSLER ALTERNATOR - BROKEN LUG.						1	L	7	1 	3O				2A13 					 
1995121500458	19951215	00458	CE 	1995	12	15	95ZZZX6749 	1	19951012	G	7120		MOUNT 			CESSNA	172 	172M 	2072418	CE 										ENGINE MOUNT	PART MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	560Z	5000 				17262889				DURING OIL CHANGE, FOUND THE CARBURETOR AIR BOX BROKEN FROM THE CARBURETOR. WHILE REMOVING AIR BOX, A 10 INCH PIECE OF 	THE LOWER ENGINE MOUNT WAS FOUND MISSING. IT DOES NOT SHOW SIGNS OF AN OLD CRACK AS BOTH SIDES ARE SHINEY. SUSPECT POS	SIBLY A HARD NOSE WHEEL LANDING.				1	H	7	1 	3O			NT	3A12 					 
1995021000271	19950210	00271	NE 	1995	2	10	95ZZZX675 	2	19950123	G	7310		TUBE 			LEAR 	24 	24 	5170302	CE 	GE 	CJ610 	CJ6104 	30006	NE 					ENG FUEL PUMP	FAILED 	D		A		B	A			EMER. DESCENT 	UNSCHED LANDING 			X			ENGINE FLAMEOUT 			CR	CRUISE 	1			SO	17	72FP		4515 			137				AIRCRAFT AT LEVEL FLIGHT 41,000 FEET WHEN ENGINE SUDDENLY FLAMED OUT. PILOT REQUESTED DESCENT AND WAS GRANTED. PILOT A	TTEMPTED RELIGHT SEVERAL TIMES, UNSUCCESSFUL. PILOT LANDED FIRST AVAILABLE AIRPORT. UNCOWLING OF ENGINE, FOUND SMALL 9	0 DEGREE FUEL TUBE LOCATED ON FUEL PUMP, ENGINE DRIVEN, BROKEN AT FLARE. RECOMMEND AN HSI INSPECTION, TUBE BE REMOVED A	ND INSPECTED FOR CRACKS.			2	L	7	2 	4J	4	J		A10CE 	1E16				 
1995121500459	19951215	00459	SO 	1995	12	15	95ZZZX6750 	1	19950913	G	3230	76426803	UPPER LINK 			PIPER 	PA28 	PA28RT201T 	7102817	SO 										NLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	8094H	1735 				28R7931309				CRACK FOUND LOCATED .25 INCH FORWARD OF DOWNLOCK ASSEMBLY ON UPPER SURFACE OF UPPER LINK. CRACK EXTENDS APPROXIMATELY .	3750 INCH INTO ARM. SUBMITTER SUSPECTS POOR DESIGN OF ARM, DOWNLOCK BOSS SHOULD HAVE BEEN RADIUSED INTO ARM.					1	L	7	1 	3O				2A13 					 
1995121500460	19951215	00460	CE 	1995	12	15	95ZZZX6751 	1	19951009	G	5753	3516505084	RIB 			BEECH 	36 	A36TC 	1151603	CE 										FLAP ACT ATTACH	CRACKED 	B			BX4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	60WB	2064 				EA173				INSPECTION FOUND CRACKED FLAP RIB AT ACTUATOR ATTACH POINT.						1	L	7	1 	3O				3A15 					 
1995121500461	19951215	00461	CE 	1995	12	15	95ZZZX6752 	1	19951011	G	5553	04320049	BRACKET 			CESSNA	150 	152 	2071835	CE 										V-FIN ATTACH	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	64843	6103 	6103 			15281449				DURING C/W AD 80-11-04, IT WAS NOTICED THE WELD ON THE RIGHT FRONT OF THE V-FIN ATTACH FITTING WAS CRACKED. REMOVAL VER	IFIED A 1 INCH CRACK.					1	H	7	1 	3O			NT	3A19 					 
1995121500462	19951215	00462	GL 	1995	12	15	95ZZZX6753 	3	19951102	G	6114	D24841	HUB 			BEECH 	58 	58 	1152740	CE 						HARTZL	HCC2Y	BHCC2YF2 	GL 	HUB FRONT	CRACKED 	B			RR4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	3871G	3411 	1216 			TH1254		HUBDZ746		DURING RESEALING, HUB FOUND CRACKED.						1	L	7	2 	3O				3A16 		5	C	P920	 
1995121500463	19951215	00463	CE 	1995	12	15	95ZZZX6754 	1	19951108	G	3230	00243002027	SUPPORT ASSY 			BEECH 	58 	58 	1152740	CE 										MLG GEARBOX	CRACKED 	B			VJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	5643C	6534 				TH1573				FOUND CRACK IN FORWARD RT SIDE OF LOWER SUPPORT ASSY. ALSO, CRACK IN AFT, LT SIDE OF LOWER SUPPORT ASSY.						1	L	7	2 	3O				3A16 					 
1995121500464	19951215	00464	CE 	1995	12	15	95ZZZX6755 	1	19951108	G	3230	00243002027	SUPPORT ASSY 			BEECH 	58 	58 	1152740	CE 										MLG GEARBOX	CRACKED 	B			VJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	72252	8828 				TH1460				FOUND CRACK IN FORWARD RT SIDE OF LOWER SUPPORT ASSY.						1	L	7	2 	3O				3A16 					 
1995121500465	19951215	00465	CE 	1995	12	15	95ZZZX6756 	1	19951108	G	3230	00243002027	SUPPORT ASSY 			BEECH 	58 	58 	1152740	CE 										MLG GEARBOX	CRACKED 	B			VJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	3149P					TH1470				FOUND SUPPORT ASSY AFT TWO MOUNT BOLT HOLES CRACKED. ALSO, CRACK IN RADIUS, FORWARD RT SIDE OF LOWER SUPPORT ASSY.						1	L	7	2 	3O				3A16 					 
1995121500466	19951215	00466	CE 	1995	12	15	95ZZZX6757 	1	19951019	G	5321		FLOOR PANEL 			CESSNA	150 	152 	2071835	CE 										COPILOT SEAT TRK	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	6224Q	10431				15285202				DURING 100-HOUR INSPECTION, COPILOT'S INBOARD SEAT TRACK AFT FLOOR AREA, FOUND 2 INCH CRACK. CRACK AT RADIUS COMES UP O	VER MAIN LANDING GEAR ATTACH BOXES. SUSPECT CAUSE, SEAT TRACK TOO LONG ENDING IN THE START OF THE RADIUS. SUGGEST BEVE	L SEAT TRACK TO PREVENT.				1	H	7	1 	3O			NT	3A19 					 
1995121500467	19951215	00467		1995	12	15	95ZZZX6758 	4	19951031	G	6113	6580400	BULKHEAD 			PIPER 	PA28 	PA28181 	7102807	SO 										PROPELLER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9900K	2594 				287890198				PROPELLER SPINNER BULKHEAD CRACKED AT MOUNT HOLE. SUSPECT DUE TO TORQUE OF MOUNT BOLTS, ALUMINUM IS CRUSHED OVER A PERI	OD OF TIME, MAKING BOLTS A TIGHT FIT CAUSING WARPAGE OF BULKHEAD AND SUBSEQUENT CRACKING. SUBMITTER SUGGESTS CONDITION 	OF BULKHEADS SHOULD BE MONITORED.				1	L	7	1 	3O				2A13 					 
1995121500468	19951215	00468	EA 	1995	12	15	95ZZZX6759 	2	19951010	G	7414	M3525	COIL 	SLICK 	4732 	CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					LT MAG	OPEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	49191	920 			91090065	5281184	L1366615			LEFT MAG INOP ON RUN-UP. REMOVED MAGNETO AND DISASSEMBLED. ELECTRICALLY CHECKED COIL AND FOUND OPEN CIRCUIT. REPLACED	 COIL WITH SERVICEABLE COIL AND OPS CHECK OK. DATE CODE ON FAILED COIL: 9/16/91.					1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995021000272	19950210	00272	CE 	1995	2	10	95ZZZX676 	1	19950103	G	5300		RIVETS 			CESSNA	425 	425 	2076018	CE 										RIVET HEADS	DAMAGED 	B			FEHR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	13	6844T	5533 				4250066				AIRCRAFT WAS STRIPPED PRIOR TO REPAINTING. WITH AIRCRAFT IN BARE METAL CONDITION. DISCOVERED NUMEROUS UNIVERSAL RIVET 	HEADS HAD BEEN PARTIALLY SANDED OFF FROM PREVIOUS PAINT PREPARATIONS. THIS INVOLVED NR 3, NR 4, AND NR 5 STRUCTURAL RIV	ETS. SOME OF THESE WERE SO SANDED, THEY WERE ALMOST FLAT. THE DAMAGED RIVETS REQUIRED REPLACEMENT. THE LOG BOOKS REFL	ECTED ONLY 2 PRIOR PAINT JOBS THAT WERE PERFORMED BY THE SAME FACILITY. OBVIOUSLY, GREAT CARE MUST BE TAKEN WHEN PREPPI	NG AIRCRAFT FOR PAINT TO NOT DAMAGE HARDWARE OR ALTER SKIN THICKNESSES.		1	L	7	2 	3T			RT	A7CE 					 
1995121500469	19951215	00469	EA 	1995	12	15	95ZZZX6760 	2	19951117	G	7322	MA3A	CARBURETOR 	FACET 		GULSTM	AA1 	AA1A 	0630710	SO 	LYC 	O235 	O235C2C 	41505	EA 					ENGINE	FAILED 	H				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			EA	17	9346L				BV81060	0046	L1091515			ENGINE QUIT IN CRUISE FLIGHT. SMALL PARTICLES OF DIRT FOUND IN CARBURETOR PER OVERHAUL SHOP.						1	L	7	1 	3O	3	O		A11EA 	E223				 
1995121500470	19951215	00470		1995	12	15	95ZZZX6761 	4	19951025	G	3416	AT3000	ENCODER 			MOONEY	M20 	M20R 	5870225	SW 										COCKPIT	NOT COMPATIBLE 	B			PA1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	27	9170T				19550	290033				FAILED ENCODER REMOVED AND REPLACED. NEW ENCODER FAILED TO WORK. FOUND THAT WHILE BOTH UNITS HAD THE SAME PART NUMBER 	(0900-4099-01), THE NEW UNIT IS NOT PLUG COMPATIBLE. SUBMITTER SUGGESTS AN UNDOCUMENTED DESIGN CHANGE BY THE FACTORY IS	 THE CAUSE OF THIS PROBLEM.				1	L	7	1 	3O			RT	2A3 					 
1995121500471	19951215	00471	CE 	1995	12	15	95ZZZX6762 	1	19951117	G	5210	07110381	HINGE PIN 			CESSNA	210 	T210R 	2073459	CE 										CABIN DOOR	BROKEN 	F				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	6542U	2002 				21064957				FOUND LOWER CABIN DOOR HINGE PIN LOWER PEENED HEAD MISSING ON PILOT'S DOOR. ON DISASSEMBLY, FOUND PIN ALSO BROKEN INSID	E OF HINGE. PIN IS MADE OF BRASS AND APPARENTLY WORK HARDENS WITH LOADS. SUBMITTER SUGGESTS USING MS20392 TYPE PIN.					1	H	7	1 	3O			RT	3A21 					 
1995121500472	19951215	00472	EA 	1995	12	15	95ZZZX6763 	2	19951030	G	7310	LW120982194	INJECTOR LINE 			GULSTM	680 	680FL 	0141608	SW 	LYC 	O720 	IO720B1B 	41546	EA 					NR 3 CYL	CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	1414S	298 				1642122	RL165654A			REF TEXTRON SB 342B ISSUED 10-22-93, PAGE 32. CLAMP NR 47, CYL NR 3, RT ENG, FOUND INJECTOR LINE AND IGNITION LEAD BOTH	 DEEPLY SCORED UNDER CLAMP. SUSPECT CAUSE, INEFFECTIVE CLAMPING ACTION OF CLAMP, PN 71829, WHEN USED WITH SLEEVE TO CLA	MP LEAD AND INJECTOR LINE TOGETHER. RECOMMEND USING CLAMP, CW16266-25-13, TO CLAMP INJECTOR LINE BY ITSELF AT ORIGINAL 	PLACE, AND USE CLAMP, LW16266-25-25, TO CLAMP LEAD TO ADJOINING SCREWS.			1	H	7	2 	3O	3	O		2A4 	1E15				 
1995121500473	19951215	00473	SO 	1995	12	15	95ZZZX6764 	2	19950929	G	8540	642383	SEAL 			BEECH 	36 	A36 	1151604	CE 	CONT 	O520 	IO520BB 	17032	SO 					STARTER ADAPTER	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	13	17782	1000 				E1024				THE GARLOCK SEAL OR LIPPED SEAL ON THE AIR CONDITIONER PULLEY SHAFT WHICH STICKS OUT THE AFT SIDE OF THE STARTER ADAPTER	 (THE SHAFT WITH THE CASTELATTED NUT AND COTTER PIN ON THE AFT FORWARD OF IT), WAS LEAKING OIL. HARD TO LOCATE LEAK AT 	THIS SEAL AS IT LOOKS DRY ALL THE TIME. HAVE FOUND MANY IO520 AND IO550'S LEAKING AT THIS SEAL. SEAL REPLACEMENT STOPS	 THE LEAK.			1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995121500474	19951215	00474	SO 	1995	12	15	95ZZZX6765 	1	19951117	G	7922	75944	VALVE 			PIPER 	PA28 	PA28181 	7102807	SO 										THERMO BYPASS	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	47907	1675 			73203	287890150				INSPECTION PER SB, VERNATHERM VALVE FAILED INSPECTION. SUBMITTER STATED 80 PERCENT OF THESE VALVES INSPECTED HAVE FAILE	D SB 518B. SUBMITTER RECOMMENDS TO HAVE AN AD ADDRESS THIS.					1	L	7	1 	3O				2A13 					 
1995121500475	19951215	00475	SO 	1995	12	15	95ZZZX6766 	1	19951110	G	2823	236405	FUEL VALVE 			PIPER 	PA34 	PA34200T 	7103406	SO 										FUEL SELECT	SEAL FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	36405	2069 				347870329				O-RING SEAL APPEARS TO HAVE DISSOLVED LEAVING BLACK GUMMY SUBSTANCE INSIDE VALVE. VALVE NO LONGER SHUTS OFF FUEL FLOW.						1	L	7	2 	3O				A7SO 					 
1995121500476	19951215	00476	EA 	1995	12	15	95ZZZX6767 	2	19951031	G	8530	LW12215	CYLINDER 			PIPER 	PA31 	PA31P 	7103120	SO 	LYC 	O541 	TIGO541E1A 	41539	EA 					EXH ROCKER	BOSS BROKEN 	B			EKIR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			WP	07	26556		327 			31P7400184	L13962			EXHAUST VALVE INBOARD ROCKER ARM SHAFT BOSS BROKEN OFF CYLINDER ASSY. ROCKER ARM AND SHAFT LIFTED UP CRACKING CYLINDER 	ON OUTBOARD SIDE WHERE SHAFT PASSES THROUGH CYLINDER. SUBMITTER SUSPECTED DEFECTIVE CASTING AS THERE IS NO EVIDENCE OF 	PREVIOUS CRACK.				1	L	7	2 	3O	3	O		A8EA 	E19EA				 
1995121500477	19951215	00477	SW 	1995	12	15	95ZZZX6768 	1	19951122	G	7120	AN427A	BOLT 			MOONEY	M20 	M20J 	5870219	SW 										TOP ENG MOUNT	RUSTED 	B			S2VR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	1173A	1650 				241333				ENGINE MOUNT UPPER ATTACH POINTS TO FIREWALL; FOUND FRETTING CORROSION IN AREA. BOLTS HAD WORKED LOOSE AND BOLTS WERE R	USTING AND HAD SERIOUS PITTING.					1	L	7	1 	3O				2A3 					 
1995121500478	19951215	00478	EA 	1995	12	15	95ZZZX6769 	2	19951121	G	8530	SL10301A20	CYLINDER 			BEECH 	77 	77 	1153007	CE 	LYC 	O235 	O235L2C 	41505	EA 					NR 1,2,3,4, CYLS	GLAZED 	B			MGOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	18152		101 			WA286	L2234915			ENGINE INSTALLED WITH NEW MILLENNIUM CYLINDERS DURING MAJOR OVERHAUL. COMPRESSION CHECKS AFTER 100.5 HOURS REVEALED NR 	1 - 52 PSI, NR 2 - 64 PSI, NR 3 - 52 PSI, NR 4 - 72 PSI. ALL CYLINDERS REMOVED FOR REHONING AND PISTONS RE-RINGED. SU	BMITTER RECOMMENDS REVISED RUN-IN PROCEDURES AND OPERATING PROCEDURES DURING FIRST 50 HOURS. ENGINE TT, 4051.8 HOURS.				1	L	7	1 	3O	3	O		A30CE 	E223				 
1995121500479	19951215	00479	GL 	1995	12	15	95ZZZX6770 	3	19951110	G	6114		HUB 			PIPER 	PA24 	PA24180 	7102402	CE 						MCAULY	2D34C	2D34C* 	GL 	NR 2 BLD SOCKET	CRACKED 	B			ZJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	81LL					241338		758123		PROPELLER SUBMITTED FOR OVERHAUL DUE TO PROPELLER STRIKE WHICH RESULTED IN NR 1 BLADE BENT WELL WITHIN REPAIRABLE LIMITS	, I.E., VERY SLIGHTLY. DURING OVERHAUL, NR 2 BLADE SOCKET FOUND CRACKED BY EDDY CURRENT AND CONFIRMED WITH LIQUID PENET	RANT TESTING. SUBMITTER STATED BLADE SOCKET NR 2 CONTAINED THE UNDAMAGED BLADE, SO IT IS SUBMITTER'S OPINION THE CRACK 	RESULTED FROM FATIGUE RATHER THAN FROM THE PROP STRIKE.			1	L	7	1 	3O			NT	1A15 		5	C	P7EA	 
1995121500480	19951215	00480	SO 	1995	12	15	95ZZZX6771 	2	19951110	G	7414	6320	MAGNETO 	SLICK 		CESSNA	210 	T210N 	2073456	CE 	CONT 	O520 	TSIO520R 	17040	SO 					RT MAGNETO	CORRODED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			CE	01	6086C	961 			92080045	21063798	517711			PILOT EXPERIRENCED ROUGH RUNNING ENGINE AFTER DEPARTING AIRPORT. PILOT RETURNED TO AIRPORT AND HAD MAGNETOS CHECKED. B	OTH MAGNETOS WERE SEVERELY CORRODED INSIDE. ONE MAGNETO WAS DEAD. PILOT ELECTED TO REPLACE BOTH MAGNETOS WITH NEW UNIT	S. THIS IS THREE MAGNETOS IN TWO MONTHS. SUBMITTER SUGGESTS PROBLEM IS CAUSED BY TURBOCHARGER PRESSURIZING AIR AND MOI	STURE.			1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995121500481	19951215	00481	SO 	1995	12	15	95ZZZX6772 	2	19951110	G	7414	6320	MAGNETO 	SLICK 		CESSNA	210 	T210N 	2073456	CE 	CONT 	O520 	TSIO520R 	17040	SO 					LT MAGNETO	CORRODED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			CE	01	6086C	961 			91050026	21063798	517711			PILOT EXPERIRENCED ROUGH RUNNING ENGINE AFTER DEPARTING AIRPORT. PILOT RETURNED TO AIRPORT AND HAD MAGNETOS CHECKED. B	OTH MAGNETOS WERE SEVERELY CORRODED INSIDE. ONE MAGNETO WAS DEAD. PILOT ELECTED TO REPLACE BOTH MAGNETOS WITH NEW UNIT	S. THIS IS THREE MAGNETOS IN TWO MONTHS. SUBMITTER SUGGESTS PROBLEM IS CAUSED BY TURBOCHARGER PRESSURIZING AIR AND MOI	STURE.			1	H	7	1 	3O	3	O		3A21 	E8CE				 
1995121500482	19951215	00482	SO 	1995	12	15	95ZZZX6773 	2	19951101	G	8500	653812	CRANKSHAFT 			CESSNA	140 	140 	2071602	CE 	CONT 	C90 	C9012F 	17009	SO 					NR 1,2 JOURNAL	BROKE 	D	P			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	01	720CU	130 				9307	27862712			CRANKSHAFT BROKE BETWEEN FIRST AND SECOND ROD THROW. TOTAL TIME SINCE NEW, 129.8 HOURS.						1	H	7	1 	3O	3	O	NC	A768 	E252				 
1995121500483	19951215	00483	SO 	1995	12	15	95ZZZX6774 	1	19950918	G	3230	441990	PISTON 		441988 	LKHEED	P2V 	SP2HJOHNSON 	5269601	SO 										LATCH CYL NLG	BROKE 	D	S			K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	05	14835	7500 			35	148358				AFTER COMPLETION OF A NORMAL FLIGHT AND LANDING, THE CAPTAIN NOTICED A LARGE AMOUNT OF HYDRAULIC FLUID IN THE NOSE GEAR 	WELL AREA. UPON INSPECTION, THE NOSE GEAR JURY STRUT LATCH CYLINDER PISTON WAS FOUND DISLODGED AND HANGING FROM THE HOO	K ATTACH POINT. TEAR DOWN OF THE ASSY REVEALED THE PISTON BROKE INSIDE THE CYLINDER 3.5 INCHES FROM THE PISTON ATTACH E	YE.			2	M	7	4 	4R			J	A1RM 					 
1995121500485	19951215	00485	EA 	1995	12	15	95ZZZX6776 	2	19951114	G	8530	SL32000WA21P	CYLINDER ASSY 			PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320E2A 	41508	EA 					ENGINE	CORRODED 	G	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	6323W	70 				2820379	L1499527A			INSPECTION FOUND CYLINDER ASSY WITH EXCESS RUST AND CORROSION AFTER 70 HOURS TT IN SERVICE. SUBMITTER STATES RUST IS DU	E TO A NEW PROCESS CALLED 'MILLENNIUM CYLINDER' IN ADDITION TO IMPROPER PAINTED OR UNPAINTED CYLINDER ASSY.					1	L	7	1 	3O	3	O		2A13 	E274				 
1995121500486	19951215	00486	SO 	1995	12	15	95ZZZX6777 	2	19950116	G	8540	4378A1	GEAR 			BOEING	75 	E75N1 	1380154	CE 	CONT 	R670 	W6706A 	17016	SO 					CRANKSHAFT	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	1535M					758520	27294			WEAR FOUND ON VALVE TIMING SERRATED GEARS ON REAR CRANKSHAFT AND STARTER GEAR. SUBMITTER RECOMMENDS REMOVING TACHOMETER	 DRIVE AND INSPECT REAR CRANKSHAFT NUT FOR PROPER TORQUE AT EVERY ANNUAL INSPECTION.					1	Q	7	1 	3R	3	R		A743 	E162				 
1995121500487	19951215	00487	EA 	1995	12	15	95ZZZX6778 	2	19950905	G	7322	103007	VENTURI 	FACET 	MA45 	STOLAM	RC3 	RC3 	3080203	NM 	FRNKLN	6A8215	6A8215B9F 	27030	EA 					ENGINE CARB	LOOSE 	G				K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			WP	23	6769K	1600 				1059	23459			PILOT COMPLAINT, ENGINE RUNNING VERY RICH. DISASSEMBLED CARBURETOR, FOUND FLOAT LEVEL TOO HIGH AND TWO-PIECE VENTURI IN	STALLED. TWO OF THE THREE LEG CLIPS WERE MISSING AND VENTURI WAS LOOSE. SUBMITTER STATED AD 63-22-03 IS NOT CLEAR. DOE	S NOT INCLUDE THESE SERIES ENGINES WHICH IT SHOULD. MARVEL-SCHEBLER BULLETIN A4-63 STATES ALL MA4-5 CARBURETORS. SUBMI	TTER STATED AD 63-22-03 SHOULD HAVE ALL ENGINE REFERENCES DELETED AND JUST SAY ALL MA4-5 CARBS. THIS IS A SAFETY OF FLI	GHT ITEM.		1	H	7	1 	3O	3	O	RC	A769 	E242				 
1995121500488	19951215	00488		1995	12	15	95ZZZX6779 	4	19951026	G	3416	35346	ENCODE DISC 	UNITEDINST 	50353P1 	PIPER 	PA60 	PA60601P 	7106012	NM 										ENCODE ALT	MISMFG 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	15	12LC				10941	61P0176009				ATC ASKED PILOT SEVERAL TIMES TO TURN OFF THE ALTITUDE PORTION OF THE TRANSPONDER BECAUSE OF ERRONEOUS CODE. BENCH CHEC	KING, CODE ERRATIC AND BLANKING IN SOME ZONES. CODE TRACKS FOUND TO BE ECCENTRIC RELATIVE TO THE SHAFT PIVOTS. SUBMITT	ER STATED THIS WAS A FACTORY SEALED INSTRUMENT AFTER CODE DISC MADE CONCENTRIC, CODE OK.				1	M	7	2 	3O			RT	A17WE 					 
1995122200029	19951222	00029	NE 	1995	12	22	95ZZZX6780 	1	19951206	G	6410	7610105020045	BLADE ASSY 			SKRSKY	S76 	S76A 	8143006	NE 										BLADE	DEBOND 	B	S	A	ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	768AL	9086 	311 		3441634B	760031				TAIL ROTOR BLADE DISBOND DETECTED DURING DAILY INSPECTION. FOUND APPROXIMATELY 1 INCH BY 1 INCH SKIN DELAMINATION AT TI	P WEIGHT AREA. POSSIBLY CAUSED BY RUST FORMING ON TIP WEIGHT HARDWARE.					1	G	7	2 	3U				H1NE 					 
1995021000276	19950210	00276	CE 	1995	2	10	95ZZZX680 	1	19950104	G	5751	9913000011	SKIN 			BEECH 	90 	C90 	1152913	CE 										AILERON UPPER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	09	29EB	4204 				LJ871				DURING SCHEDULED AILERON INSPECTION, FOUND SKIN CRACKED IMMEDIATELY ADJACENT TO THE LEADING EDGE SKIN WHERE THE TOP SKIN	 AND LEADING EDGE SKIN LAP. THE CRACK WAS ABOUT 5.50 INCHES LONG AND NOT VISIBLE WITHOUT PRESSING ON THE SKIN ITSELF.					1	L	7	2 	3T				3A20 					 
1995122200402	19951222	00402	EA 	1995	12	22	95ZZZX6804 	2	19951117	G	7322	105235HA6	CARBURETOR 			CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540L3C5 	41532	EA 					FLOAT	SHAFT WORN 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CE	01					DG0229					FUEL STARTED RUNNING FROM CARBURETOR AIR INTAKE 'EXCESSIVE'. REMOVED CARBURETOR, FOUND FLOAT SHAFT WORN EXCESSIVELY AND	 SHAFT BACKED OUT.					1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1995122200403	19951222	00403	SO 	1995	12	22	95ZZZX6805 	2	19951107	G	8530	641916	CYLINDER 			CESSNA	172 	172 	2072402	CE 	CONT 	O300 	O300D 	17022	SO 					ROCKER BOSS	ROCKER BROKE 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SW	11	3864L					17254033	33771D5D			THIS CYLINDER WAS NOT WITHIN THE DIMENSIONAL SPECS REQUIRED IN AD 94-05-05, BUT WAS NOT REQUIRED TO BE INSPECTED UNTIL O	VERHAUL. THE ROCKER BOSSES BROKE IN-FLIGHT, BUT A SAFE-ON-AIRPORT LANDING WAS MADE. SUBMITTER RECOMMENDS THAT AD 94-05	-05 BE CHANGED TO REQUIRE AT LEAST A DIMENSIONAL CHECK OF THE ROCKER BOSS THICKNESS AT NEXT ANNUAL INSPECTION.				1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995122200404	19951222	00404	EA 	1995	12	22	95ZZZX6806 	2	19950905	G	7414	10382585	POINTS 	BENDIX 	BL68255514 	CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					MAGNETO	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	737HK	297 			3012041	17269428				INSPECTED MAG, FOUND POINTS NOT LUBRICATED AND PLASTIC PUSH ARMS WORN OFF. POINTS WOULD NOT OPEN AND BOTH LEFT AND RIGH	T SIDES OF MAG WERE NOT OPERATIONAL.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995122200405	19951222	00405	SO 	1995	12	22	95ZZZX6807 	1	19950920	G	3230	675100	BEARING 			PIPER 	PA28 	PA28RT201 	7102818	SO 										NLG DOWNLOCK	BINDS 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23										TWO PROBLEMS NOTED: SERVICE MANUAL STATES THAT - UNFAVORABLE CONDITION - BEARING ROTATES/WOBBLES. CHAPTER 32-20-05, PA	GE 32-25, PARA 2D. SERVICE MANUAL STATES THAT 'BEARING MUST BE FREE TO ROTATE' CHAPTER 32-20-06, PAGE 32-30, PARA 3D. B	EARING IS BASIC STEEL BUSHING THAT IS BOLTED TO A STEEL BLOCK WHEN ASSEMBLED BY GOOD MAINTENANCE PRACTICE AND TORQUED TO	 PROPER VALUE. THE BEARING WILL NOT TURN, MOST CHEROKEE ARROWS HAVE THIS SITUATION. PIPER ACFT WANTS THE BOLT LEFT LOO	SE.		1	L	7	1 	3O				2A13 					 
1995122200406	19951222	00406		1995	12	22	95ZZZX6808 	4	19950921	G	2562		ELT 	ACK 		BBAVIA	7 	7GCBC 	1220601	SW 										AUX ANTENNA	ANTENNA DETACHED	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	88110					72574				THE AUXILIARY ANTENNA THAT IS ATTACHED TO THE ELT BODY HAS FALLEN OFF TWICE AND DISAPPEARED INTO THE BELLY OF THE AIRCRA	FT. THE OWNER HAS FOUND IT EACH TIME. HOWEVER, SUBMITTER SUGGESTS AN OBJECT THIS SIZE COULD EASILY JAM CONTROL, SO IT 	IS IMPORTANT TO IMPROVE ATTACHMENT (TAPE?) AND VISUALLY INSPECT.				1	H	7	1 	3O			NC	A759 					 
1995122200407	19951222	00407	GL 	1995	12	22	95ZZZX6809 	3	19951006	G	6114	C4716C98	HUB 													MCAULY	2A34C	D2A34C98 	GL 	NR 2 SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								747975		UPON INPSECTION, HUB FOUND CRACKED IN NR 2 BLADE SOCKET. HUB HAS BEEN SCRAPPED.																5	C	P3EA	 
1995021000277	19950210	00277		1995	2	10	95ZZZX681 	4	19950124	G	3453	8010900	ANTENNA 			BEECH 	90 	E90 	1152914	CE 										LORAN	DEFECTIVE 	H			VIB3	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	666DC	56013				LW44				BOTH COMMS AND NAVS WOULD HAVE EXCESSIVE STATIC IN LIGHT PRECIPITATION. THE COMMS WOULD BECOME UNREADABLE AND BOTH NAVS	 WOULD FLAG WITH LOSS OF L/R DEVIATION VOR OR LOC. TEST AIRCRAFT WITH DAYTON GRANGIER HIGH VOLTAGE STATIC TESTER AND FO	UND LORAN ANTENNA SOURCE OF NOISE. REPLACE WITH HIGH-SPEED BLADE STYLE ANTENNA, PN 14663-03. FLIGHT TESTED AND PROBLEM	 CORRECTED.			1	L	7	2 	3T				3A20 					 
1995122200408	19951222	00408	GL 	1995	12	22	95ZZZX6810 	3	19950918	G	6111	V84337	BLADE 			PIPER 	PA24 	PA24250 	7102404	SO 						HARTZL	HCA2V	HCA2V* 	GL 	SHANK	CRACKED 	B			ZJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	7055P				A23369	242205		J453		DURING OVERHAUL AND C/W THE REPETATIVE INSPECTIONS REQUIRED BY AD 68-19-04, BLADE WAS FOUND CRACKED IN THE BLADE SHANK. 	 IN THE AREA DETAILED IN THE AD, THE CRACK WAS EXTREMELY TIGHT AND ALMOST IMPOSSIBLE TO DETECT WITH LIQUID PENETRANT INS	PECTION, HOWEVER, THE CRACK WAS VERY APPARENT WHEN SUBJECTED TO EDDY CURRENT TESTING IN THE BLADE SHANK. SUBMITTER RECO	MMENDS SHOPS BACK UP THE PENETRANT INSPECTIONS WITH EDDY CURRENT TESTING.			1	L	7	1 	3O				1A15 		5	C	P24EA	 
1995122200409	19951222	00409	CE 	1995	12	22	95ZZZX6811 	1	19951116	G	3060	B4018305	DEICE BOOT 			CESSNA	414 	414A 	2075907	CE 										RT PROP BLD NR 1	INOP 	D				A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			NE	03	300SQ	814 			L9U1596	414A0416				AIRCRAFT ENTERED ICY CONDITIONS AND AFTER SELECTING PROP DEICE, HAD A LOW DEICE METER INDICATION. AIRCRAFT RETURNED TO 	BASE. PROBLEM WAS IDENTIFIED AS RIGHT PROP NR 1 HAD DEICE BOOT OUTBOARD ELEMENT TO BE INOPERATIVE.					1	L	7	2 	3O				A7CE 					 
1995122200410	19951222	00410	SO 	1995	12	22	95ZZZX6812 	2	19951117	G	8540	640808	GEAR 		642085A2 	CESSNA	402 	402A 	207590M	CE 	CONT 	O520 	TSIO520E 	17040	SO 					START ADAPTER	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	7816Q		1254 			4020116	165122			OIL PUMP GEAR BROKE AND CRACKED THE BODY ASSEMBLY OF THE SCAVENGE PUMP, P/N 640766. REPLACED STARTER ADAPTER WITH A REB	UILT, P/N 642085A2.					1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995122200411	19951222	00411	SO 	1995	12	22	95ZZZX6813 	1	19951108	G	5320	7599300	FITTING 			PIPER 	PA32 	PA32301 	7103207	SO 										FS 73 RT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	8423P	2320 				328106086				FOUND STEEL FITTING ON RIGHT SIDE CORRODED AT STA 73. WINDOW WAS LEAKING CAUSING WATER TO SATURATE INSTALLATION. THIS 	CAUSED A CORROSIVE ENVIRONMENT. SUBMITTER RECOMMENDATIONS WOULD BE TO INSPECT STEEL FITTINGS, INSULATION, AND WINDOW. R	EPLACE AND/OR SEAL NECESSARY PARTS. AFTER DOING NECESSARY MAINTENANCE, TREAT ATTACH STEEL FITTINGS WITH DINOL AV8 CORRO	SION COMPOUND. PIPER, P/N 89500-800. INSPECT EVERY ANNUAL/100-HOUR INSPECTION, AND THEREAFTER.			1	L	7	1 	3O				A3SO 					 
1995122200412	19951222	00412	SO 	1995	12	22	95ZZZX6814 	1	19950926	G	5313	8422202	FITTING 			PIPER 	PA46 	PA46310P 	7104605	SO 										STRINGER LT	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	6914T	2384 				468508074				PIPER SB 962 DATED 9-29-93, DOES NOT COVER RE-INSPECTION OF AREA AFFECTED SOON ENOUGH. RUST CANNOT BE SEEN UNDER FITTIN	GS AND BETWEEN AIRCRAFT SKIN. DISSIMILAR CORROSION SETS UP CAUSING ADDITIONAL DAMAGE. SUBMITTER RECOMMENDS COMPLETE RE	MOVAL OF FITTINGS, AND INSTALLATION OF NEW CADMIUM PLATED FITTINGS AS WELL AS TREATMENT OF AIRCRAFT SKIN. DINITROL AV8 	SHOULD BE APPLIED AFTER INSTALLATION PER PIPER SB 962. RECOMMEND VISUAL INSPECTION EACH 500 HOURS OR 1 YEAR USING BORES	COPE AS AID UNTIL NEW PARTS ARE INSTALLED.		1	L	7	1 	3O				A25SO 					 
1995122200413	19951222	00413	SO 	1995	12	22	95ZZZX6815 	1	19951123	G	2710	63900119	BUSHING 			PIPER 	PA44 	PA44180 	7104402	SO 										AILERON CON ROD	MISMANUFACTURED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	03	2148F	698 				447995157				AILRON HAD EXCESSIVE PLAY. CLEVIS ROD END BUSHING HAD EXCESSIVE PLAY. WHEN NEW BUSHINGS, P/N 63900-119, WERE INSTALLED	, THE OUTSIDE DIAMETER OF BUSHING WAS TOO SMALL (FELL OUT OF HOLE IN CLEVIS). NEW CLEVIS, P/N 554 687, WAS CHECKED AND 	THE BUSHING COULD BE INSTALLED WITH FINGER PRESSURE. BOLT AN 3-10 WOULD NOT GO THROUGH INSIDE DIAMETER OF BEARING. HAD	 TO REAM ID OF BUSHING. BUSHING, P/N 63900-119, OUTSIDE DIAMETER IS TOO SMALL AND INSIDE DIAMETER OF BUSHING TOO SMALL.	 CONTACTED PIPER SERVICE REP 4/94 ABOUT SAME PROBLEM. TOTAL TIME OF NEW PARTS WAS 697.8 HOURS. SUBMITTER RECOMMENDS P	ART DIMENSIONS BE ADJUSTED.	1	L	7	2 	3O				A19S0 					 
1995122200414	19951222	00414	CE 	1995	12	22	95ZZZX6816 	1	19951019	G	2701		CONTROL COLUMN 			BEECH 	35 	D35 	1151510	CE 										COCKPIT	BINDING 	D				K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			GL	13	2935B					D3576				PILOT EXPERIENCED AILERON MOVEMENT RESTRICTIONS ON RUN-UP CHECK. AILERONS MOVED TO FULL RIGHT DEFLECTION, AND WOULD COM	E ONLY THREE-FOURTHS OF THE WAY BACK TO NEUTRAL POSITION, AND LOCK. WOULD ONLY MOVE TO RIGHT. AFTER MUCH T/S, DISCOVER	ED CONTROL YOKE & COLUMN ARM & SHAFT WERE FULL OF DECON MOUSE KILLER PELLETS RESTRICTING MOVEMENT OF CHAIN & SPROCKETS I	N YOKE & ROTATING SHAFT IN THE COLUMN SHAFT THAT GOES INTO THE INSTRUMENT PANEL. A GOOD CLEANING RESOLVED PROBLEM. OWN	ER REMOVED DECON BAITING STATIONS IN THE HANGAR. HE ALSO HAD METAL RINGS AROUND HIS TIRES THAT SHOULD KEEP MICE FROM GE	TTING IN.	1	L	7	1 	3O				A777 					 
1995122200415	19951222	00415	CE 	1995	12	22	95ZZZX6817 	1	19951101	G	3230		DOWNLOCK SYS 			CESSNA	172 	172RG 	2072438	CE 										NLG	MALFUNCTION 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	5177R	3200 				172RG0045				AFTER A GEAR INSPECTION (ROUTINE), THE AIRCRAFT WAS PLACED ON THE GROUND. THE GEAR HANDLE WAS 'DOWN', THE LIGHT 'GREEN'	, AND THE BREAKER 'IN'. THE STRUT WAS AT MAX EXTENSION. ROUTINE MAINTENANCE PERFORMED ON ACFT FOR THE 100-HOUR INSPECT	ION. APPROXIMATELY ONE AND ONE-HALF HOURS AFTER ACFT WAS PLACED ON THE GROUND, MASTER SWITCH WAS TURNED ON TO CHECK A L	IGHT (UNLRELATED POST-LAMP). THE PUMP MOTOR RAN, THE NOSEGEAR COLLAPSED & DAMAGED THE NOSEGEAR DOORS. GEAR HANDLE WAS 	STILL IN THE 'DOWN' POSITION. SUBSEQUENT EXHAUSTIVE SEARCH HAS NOT ISOLATED THE CAUSE.		1	H	7	1 	3O				3A17 					 
1995122200416	19951222	00416	CE 	1995	12	22	95ZZZX6818 	1	19951114	G	5220	13148308400	SEAL 			BEECH 	36 	A36 	1151604	CE 										LT EMERG EXIT	MISGLUED 	B		A	VIB6	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	03	3199G	90 				E2890				DURING THIS AIRCRAFT'S FIRST ANNUAL INSPECTION, THE LT EMERGENCY EXIT WINDOW WAS EXTREMELY DIFFICULT TO OPEN. IT WAS LA	TER DISCOVERED THE SEAL HAD BEEN GLUED ON BOTH SIDES AND, THEREFORE, HAD GLUED THE EMERGENCY EXIT CLOSED. SUBMITTER SUG	GESTS UPON DELIVERY OF ALL NEW AIRCRAFT, ALL THE EMERGENCY EXITS SHOULD BE OPENED OR FUNCTIONALLY CHECKED PRIOR TO FLIGH	T. AIRCRAFT TOTAL TIME, 89.7 HOURS.			1	L	7	1 	3O				3A15 					 
1995122200417	19951222	00417	SW 	1995	12	22	95ZZZX6819 	1	19951101	G	5541	442283	SPAR 		44006501 	GULSTM	112 	112TCA 	7630307	SW 										RUDDER	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	4666W	1195 				13303				ON INSPECTION PRIOR TO PAINT, RUDDER SPAR FOUND CRACKED BEHIND UPPER ATTACH FITTING. TOTAL CRACK LENGTH, 3 INCHES. THI	S AREA VERY DIFFICULT TO INSPECT UNLESS RUDDER AND RUDDER UPPER ATTACH FITTING ARE REMOVED. SUBMITTER STATED THIS IS TH	IRD CASE OF CRACKING OF RUDDER SPAR ON R112, R114 AIRCRAFT SEEN.				1	L	7	1 	3O				A12SO 					 
1995021000278	19950210	00278		1995	2	10	95ZZZX682 	4	19950124	G	3453	8010900	ANTENNA 			BEECH 	200 	B200 	1152922	CE 										LORAN	DEFECTIVE 	H			VIB3	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	9NA					BB1194				BOTH COMMS AND NAVS QUIT IN STATIC PRECIPITATION. THE COMM WOULD BECOME UNREADABLE AND BOTH NAV'S WOULD FLAG AND LOSS O	F L/R DEVIATION. TESTED AIRCRAFT WITH DAYTON GRANGIER HIGH-VOLTAGE TESTER AND FOUND LORAN ANTENNA SOURCE OF NOISE. REM	OVED AND REPLACED WTIH HIGH-SPEED BLADE STYLE ANTENNA, PN 14663-03. FLIGHT TESTED AND PROBLEM CORRECTED. REF WO NR A56	06.			1	L	7	2 	4T				A24CE 					 
1995122200418	19951222	00418	SO 	1995	12	22	95ZZZX6820 	2	19950926	G	7414	10357592	OIL SEAL 	BENDIX 	S6RN201 	CESSNA	402 	402B 	207590P	CE 	CONT 	O520 	TSIO520E 	17040	SO 					LT MAGNETO	LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	09	5199G		433 		K159402ER	402B0573				DURING A 100-HOUR INSPECTION, OIL WAS FOUND IN THE LT MAGNETO ON THE RT ENGINE. THE OIL SEAL WAS REPLACED AND THE MAGNE	TO WAS PUT BACK INTO SERVICE. 433.1 HOURS SINCE FACTORY OVERHAUL.					1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995122200419	19951222	00419	SO 	1995	12	22	95ZZZX6821 	2	19950926	G	7414	10357592	OIL SEAL 	BENDIX 	S6RN201 	CESSNA	402 	402B 	207590P	CE 	CONT 	O520 	TSIO520E 	17040	SO 					LT MAG	LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	09	5198J		169 		A269517ER	402B0885				DURING A 50-HOUR INSPECTION, OIL WAS FOUND IN THE LEFT MAGNETO ON THE LEFT ENGINE. THE OIL SEAL WAS REPLACED AND THE MA	GNETO WAS PUT BACK INTO SERVICE. 168.5 HOURS SINCE FACTORY OVERHAUL.					1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1995122200420	19951222	00420	CE 	1995	12	22	95ZZZX6822 	1	19951116	G	3610	2H288	VALVE 			BEECH 	58 	58P 	1152744	CE 										MANIFOLD CHECK	DISLODGED 	D				O				OTHER 				O			OTHER 			AP	APPROACH 	1			EA	05	2110A	2110 				TJ129				SHORTLY AFTER DEICE BOOTS WERE CYCLED AND AN I.F.R. LANDING APPROACH WAS ENTERED, ALL PRESSURE GYRO INSTRUMENTS FAILED A	ND SYSTEM PRESSURE WENT TO ZERO. BOTH RED INDICATOR BALLS REMAINED IN. FOUND LT CHECK VALVE IN MANIFOLD DEFECTIVE AND 	LT PUMP OUTPUT LOW. CHANGED BOTH ITEMS, BUT SUSPECT DEICE VALVE STAYED OPEN TOO LONG.				1	L	7	2 	3O				A23CE 					 
1995122200422	19951222	00422	CE 	1995	12	22	95ZZZX6824 	1	19951129	G	2436	B003062	REGULATOR 			BEECH 	76 	76 	1153005	CE 										TERMINALS	MISLABELED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	03	3734M				80029601	ME366				THE WIRING TERMINALS HAVE INCORRECT DECAL LABELING. THE DECAL IS INSTALLED 180 DEGREES OFF. THIS CAUSES THE BUS, FIELD	, GROUND, AND PARALLEL WIRE TERMINALS TO BE INCORRECTLY LABELED.					1	L	7	2 	3O				A29CE 					 
1995122200423	19951222	00423	CE 	1995	12	22	95ZZZX6825 	1	19951129	G	2436	B003062	REGULATOR 			BEECH 	76 	76 	1153005	CE 										TERMINALS	MISLABELED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	03	3734M				80029604	ME366				THE WIRING TERMINALS HAVE INCORRECT DECAL LABELING. THE DECAL IS INSTALLED 180 DEGREES OFF. THIS CAUSES THE BUS, FIELD	, GROUND, AND PARALLEL WIRE TERMINALS TO BE INCORRECTLY LABELED.					1	L	7	2 	3O				A29CE 					 
1995122200424	19951222	00424	SO 	1995	12	22	95ZZZX6826 	1	19951127	G	3610	28C444CW4	AIR PUMP 	AIRBORNE 		PIPER 	PA46 	PA46310P 	7104605	SO 										DRIVE GEAR	WORN 	B			BONR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	40PM	1300 			11AA154	4608005				AIRCRAFT DEICE BOOTS INOP. FOUND AIR PUMP DRIVE GEAR LOOSE ON CLUTCH SHAFT. GEAR WAS WORN EXCESSIVELY AND CRACKED. TH	IS ITEM DIFFICULT TO INSPECT. SUBMITTER RECOMMENDS AD REQUIRING PERIODIC INSPECTION.					1	L	7	1 	3O				A25SO 					 
1995122200425	19951222	00425	CE 	1995	12	22	95ZZZX6827 	1	19951109	G	7810	25540251	CLAMP ASSY 			CESSNA	303 	T303 	2073820	CE 										RT ENG EXHAUST	FAILED 	B	P	A	FE6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	727RT	1378 				T30300090				MAINTENANCE PERSONNEL FOUND EXHAUST STAINS ON UPPER RT COWLING COOLING LOUVERS. FOUND CLAMP, LOCATED UNDER INTAKE MANIF	OLD TO NR 3 CYLINDER, TO BE OUT OF POSITION CREATING A .3125 INCH GAP BETWEEN THE EXHAUST COLLECTOR, PN 2554018-10, TO N	RS 2, 4, AND 6 CYLINDERS AND, PN 2554020-2, EXHAUST COLLECTOR TO CYLINDERS 3 AND 5. THE CLAMP WAS FOUND TIGHTLY CLAMPED	 TOGETHER, BUT THE LOCATING DOWEL PIN (APPROX .1250 INCH) HAD FAILED ALLOWING CLAMP TO MIGRATE FORWARD. SUSPECT LOCATIN	G DOWEL PIN IS TOO SMALL. INSTALLED NEW CLAMP AND RETURNED TO SERVICE.		1	L	7	2 	3O				A34CE 					 
1995122200426	19951222	00426		1995	12	22	95ZZZX6828 	1	19951107	G	7400	M1346	WASHER 	SLICK 																P-LEAD	MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21										THE P-LEAD INSULATING WASHER IS VITAL TO PREVENT GROUNDING OF THE MAGNETO ESPECIALLY IN A WET ENVIRONMENT; RAIN OR ENGIN	E WASHING.																		 
1995021000279	19950210	00279	SO 	1995	2	10	95ZZZX683 	1	19950116	G	3610	1159AC2005537	DUCT 			GULSTM	G1159 	G1159A 	3970109	SO 										APU AIR	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	221CM	5319 				343				DUCT IS LOCATED IN THE APU SUPPLIED AIR SYSTEM USED FOR GROUND AIR CONDITIONING AND ENGINE START. THIS DUCT FAILED ON T	HE GROUND PRIOR TO ENGINE START. IT APPEARS THE DUCT COUPLING 'UNSWAGED' FROM THE DUCT CAUSING LOSS OF MANIFOLD PRESSUR	E.				2	L	7	2 	4F				A12EA 					 
1995122200428	19951222	00428	CE 	1995	12	22	95ZZZX6830 	1	19951114	G	2740	12321391	BRACKET 			CESSNA	207 	207 	2073602	CE 										HOR STAB TAB ACT	WORN 	D				O				OTHER 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			AL	03	207EX	7115 				20700100				TRIM TAB ACTUATOR MOUNTING BRACKET WORN AND CAUSED AN IN-FLIGHT VIBRATION.						1	H	7	1 	3O				A16CE 					 
1995122200429	19951222	00429		1995	12	22	95ZZZX6831 	4	19951110	G	2565	D30656126	SLIDE 	AIRCRUISERS 	757 															LINK	MISREPAIRED 	B			PX1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					0368					FRANGIBLE LINKS USED TO REGULATE DEPLOYMENT HAD APPARENTLY BEEN FUNCTIONED ONCE (NOT RE-USEABLE); HOWEVER, WHAT REMAINED	 ON THE LINK WAS RECONSTRUCTED USING UNAPPROVED WIRE, AND AT TIMES, TAPED OVER WITH GRAY DUCT TAPE. LIGHTING SYSTEM BAT	TERY LANYARD WASTIED OFF USING COPPER WIRE AS OPPOSED TO COTTON THREAD.																	 
1995122200430	19951222	00430		1995	12	22	95ZZZX6832 	4	19951110	G	2565	D30654122	SLIDE 	AIRCRUISERS 	757 															LINK	MISREPAIRED 	B			PX1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					0353					FRANGIBLE LINKS USED TO REGULATE DEPLOYMENT HAD APPARENTLY BEEN FUNCTIONED ONCE (NOT RE-USEABLE); HOWEVER, WHAT REMAINED	 ON THE LINK WAS RECONSTRUCTED USING UNAPPROVED WIRE, AND AT TIMES, TAPED OVER WITH GRAY DUCT TAPE. LIGHTING SYSTEM BAT	TERY LANYARD WAS TIED OFF USING COPPER WIRE AS OPPOSED TO COTTON THREAD. AN UNAPPROVED AND QUESTIONABLE REPAIR HAD BEEN	 PERFORMED ON AN ASPIRATOR. THE ABOVE DISCREPANCIES WOULD HAVE CAUSED IMPROPER FUNCTIONING OF THE SLIDE/RAFT SYSTEM.																 
1995122200431	19951222	00431		1995	12	22	95ZZZX6833 	4	19951110	G	2565	D30654122	SLIDE 	AIRCRUISERS 	757 															LANYARD	MISREPAIRED 	B			PX1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25					0357					LIGHTING SYSTEM BATTERY LANYARD WAS TIED OFF USING COPPER WIRE AS OPPOSED TO COTTON THREAD. FIRING CABLE WAS INCORRECTL	Y ROUTED THROUGH HOLE IN PACKBOARD.																		 
1995122200432	19951222	00432	WP 	1995	12	22	95ZZZX6834 	2	19951113	G	7250	30720142	BLADE 			ISRAEL	1124 	1124A 	4500103	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					LP 3RD STAGE	FAILED 	C				E				ENGINE SHUTDOWN 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			SW	15	1904G	3050 				436	P77629			FL 24,000 FEET CRUISE - LOUD BOOM NOISE OCCURRED WITH VIBRATION FOLLOWING. RIGHT ENGINE WAS PULLED BACK TO IDLE BY CREW	 WHICH CUT DOWN ON VIBRATION LEVEL. ENGINE WAS SHUT DOWN AS PRECAUTIONARY MEASURE.					2	M	7	2 	4F	4	F		A2SW 	E6WE				 
1995122200434	19951222	00434	EA 	1995	12	22	95ZZZX6836 	2	19951030	G	7230	3036551	VANE RING 			SKRSKY	S76 	S76B 	8143007	NE 	PWA 	PT6 	PT6B36 	52043	EA 					COMPRESSOR TURB	CRACKED 	B			CW1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	780P	2024 			5D496	760359	36130			INSPECTION FOUND CRACKS IN COMPRESSOR TURBINE VANE RING WHICH CAUSE INACCURATE POWER ASSURANCE READINGS.						1	G	7	2 	4U	4	U		H1NE 	E4EA				 
1995122200435	19951222	00435	CE 	1995	12	22	95ZZZX6837 	1	19951101	G	5313	50440012319	STRINGER 			BEECH 	90 	C90 	1152913	CE 										PRESS BLKHD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	369GA	6131 				CJ934				STRINGER NR 9R CRACKED AT FIRST RIVET HOLE AFT OF THE AFT PRESSURE BULKHEAD. BEECHCRAFT RECOMMENDED INSTALLING KIT, PN 	101-4063-4S. THIS KIT IS USED TO REPAIR STRINGER NR 9R ON THE 200 SERIES KING AIR. (REFERENCE BEECHCRAFT SB 2472, REV 	11.) FORM 337 WAS USED TO RETURN THE AIRCRAFT TO SERVICE.				1	L	7	2 	3T				3A20 					 
1995122200436	19951222	00436	CE 	1995	12	22	95ZZZX6838 	1	19951127	G	5311		FRAME 			MTSBSI	MU2 	MU2B36 	5780412	CE 										FS 4610 LT	CRACKED 	B			TUPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	500PJ	6143 				668				FRAME 4610, LEFT, CRACKED THROUGH SCREW HOLES APPROXMATELY 31MM BELOW LOWER HOLE. ALL 6 STATIONS HAD TO BE SHIMMED PER 	SB 209A.					1	H	7	2 	3T			RT	A10SW 					 
1995122200437	19951222	00437	CE 	1995	12	22	95ZZZX6839 	1	19951110	G	5740		BOLTS 			LEAR 	35 	31A 	5170531	CE 										WING ATTACH	LOST TORQUE 	B			TJ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	742E	1194 				071				DURING 1,200-HOUR INSPECTION, NOTED TORQUE PUTTY BROKEN ON WING ATTACHMENT BOLTS. CHECKED AND NOTED ALL 8 ATTACHMENT NU	TS HAD LOW TORQUE. RE-TORQUED TO MFG SPECS.					2	L	7	2 	4F			RT	A10CE 					 
1995021000280	19950210	00280	CE 	1995	2	10	95ZZZX684 	1	19950111	G	3020	625260079	INLET TUBE 			CESSNA	650 	650 	2076802	CE 										ANTI-ICE LT ENG	FRACTURED 	B	L		JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	210F	4179 				6500067				LEFT ENGINE INLET ANTI-ICE RING FOUND BROKEN AT 12:00 POSITION. REPAIRED ANTI-ICE RING BY WELDING AND INSTALLING REINFO	RCING GUSSET.					2	L	7	2 	4F				A9NM 					 
1995122200438	19951222	00438	CE 	1995	12	22	95ZZZX6840 	1	19951016	G	5510	38021041711	SUPPORT 			RKWELL	NA265 	NA26580 	7630108	CE 										HORZ STAB HINGE	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	66ED	5800 				38032				SUPPORT CRACKED AT END WHERE ELEVATOR ATTACHES. THIS CAUSES HINGE BEARINGS, PN BR4, TO BE LOOSE. THIS PART CAN ONLY BE	 SEEN BY REMOVING HINGE SUPPORT, PN 285-220401-7. RIGHT SUPPORT WAS FOUND BROKEN AND AS A PRECAUTION, LEFT SIDE WAS INS	PECTED AND FOUND CRACKED. THESE SUPPORTS WERE ACCIDENTLY FOUND, AND ARE NOT NORMALLY INSPECTED.				2	L	7	2 	4F				A2WE 					 
1995122200514	19951222	00514	SW 	1995	12	22	95ZZZX6841 	1	19951110	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3185P	543 				45775				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 543.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200515	19951222	00515	SW 	1995	12	22	95ZZZX6842 	1	19951110	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3185P	543 				45775				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 543.0 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200516	19951222	00516	SW 	1995	12	22	95ZZZX6843 	1	19951110	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	173AL	572 				52066				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 572.0 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1995122200517	19951222	00517	SW 	1995	12	22	95ZZZX6844 	1	19951110	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	173AL	572 				52066				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 572.0 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1995122200518	19951222	00518	SW 	1995	12	22	95ZZZX6845 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2755N	502 				45243				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 501.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200519	19951222	00519	SW 	1995	12	22	95ZZZX6846 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2755N	502 				45243				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 501.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200522	19951222	00522	SW 	1995	12	22	95ZZZX6849 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1081G	292 				45405				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 292.4 HOURS.				1	G	7	1 	3U				H2SW 					 
1995021000281	19950210	00281	EA 	1995	2	10	95ZZZX685 	2	19950101	G	7414	10391309	DISTRIBUTOR GEAR	BENDIX 	S6LN1209 	PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					LT ENG RT MAG	TEETH MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	4112K	1688 			3111408	318353006	L898261A			DURING RUN-UP BEFORE FLIGHT, FOUND BAD MAG CHECK ON LT ENGINE RT MAG. REMOVED MAG FOR INSPECTION AND FOUND WHITE PLASTI	C DRIVE GEAR INSIDE MAGNETO WAS MISSING NUMEROUS DRIVE TEETH, THE REST OF MAGNETO APPEARS SERVICEABLE.					1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1995122200523	19951222	00523	SW 	1995	12	22	95ZZZX6850 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1081G	292 				45405				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 292.4 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200524	19951222	00524	SW 	1995	12	22	95ZZZX6851 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27545	284 				45234				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 284.1 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200525	19951222	00525	SW 	1995	12	22	95ZZZX6852 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27545	284 				45234				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 284.1 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200526	19951222	00526	SW 	1995	12	22	95ZZZX6853 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5011F	647 				2564				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 647.4 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200527	19951222	00527	SW 	1995	12	22	95ZZZX6854 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5011F	647 				2564				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 647.4 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200528	19951222	00528	SW 	1995	12	22	95ZZZX6855 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	349AL	497 				51388				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 497.3 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200529	19951222	00529	SW 	1995	12	22	95ZZZX6856 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	349AL	497 				51388				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 497.3 HOURS.				1	G	7	1 	3U				H2SW 					 
1995021000282	19950210	00282	NM 	1995	2	10	95ZZZX686 	1	19950105	G	2430	F0C4003A24V	OVERVOLT RELAY 	PRESTOLITE 		PIPER 	PA60 	PA60600 	7106001	NM 										LT ALT LT FS 176	FAILED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	138TS					60138058				RELAY FAILED TO OPERATE UNTIL 36 VOLTS, DID NOT PROTECT SYSTEM ALLOWING DAMAGE TO NUMEROUS COMPONENTS. SEE MDR ON SAME 	SUBJECT CONCERNING LAMAR REGULATOR. RECOMMEND REMOVAL AND TEST OF OVERVOLT RELAYS AT ANNUAL INSPECTIONS.					1	M	7	2 	3O			RT	A17WE 					 
1995122200534	19951222	00534	SW 	1995	12	22	95ZZZX6861 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	170AL	380 				52063				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 380.2 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1995122200535	19951222	00535	SW 	1995	12	22	95ZZZX6862 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	170AL	380 				52063				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 380.2 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1995122200536	19951222	00536	SW 	1995	12	22	95ZZZX6863 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3912Q	477 				3271				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 477.4 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200537	19951222	00537	SW 	1995	12	22	95ZZZX6864 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3912Q	477 				3271				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 477.4 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200538	19951222	00538	SW 	1995	12	22	95ZZZX6865 	1	19951109	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2755N	502 				45243				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 501.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200539	19951222	00539	SW 	1995	12	22	95ZZZX6866 	1	19951109	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2755N	502 				45243				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 501.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200540	19951222	00540	SW 	1995	12	22	95ZZZX6867 	1	19951108	G	6230	06010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A	518 				45256				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200541	19951222	00541	SW 	1995	12	22	95ZZZX6868 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A	518 				45256				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200542	19951222	00542	SW 	1995	12	22	95ZZZX6869 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D	518 				45280				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1995021000283	19950210	00283	EA 	1995	2	10	95ZZZX687 	2	19950118	G	8530	LW19001	VALVE 			PIPER 	PA32 	PA32260 	7103206	SO 	LYC 	O540 	O540E4B5 	41532	EA 					NR 3 CYCLINDER	BROKEN 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			AL	01	4803S	1000 				321188	L2331840A			THE AIRCRAFT RETURNED SHORTLY AFTER TAKEOFF WITH A ROUGH RUNNING ENGINE. THE EXHAUST VALVE, THE UPPER VALVE SPRING SEAT	, PN LW-16475, AND THE VALVE STEM CAP, PN 17C19386, WERE FOUND BROKEN.					1	L	7	1 	3O	3	O		A3SO 	E295				 
1995122200543	19951222	00543	SW 	1995	12	22	95ZZZX6870 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D	518 				45280				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200544	19951222	00544	SW 	1995	12	22	95ZZZX6871 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5734M	481 				45449				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 480.8 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200545	19951222	00545	SW 	1995	12	22	95ZZZX6872 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5734M	481 				45449				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 480.8 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200546	19951222	00546	GL 	1995	12	22	95ZZZX6873 	2	19951120	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					TURB 3RD STAGE	RIM BREAK OUT 	G	L	A		K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	27702	12073	635 		HX91198	45300	CAE860520			LOUD ROAR AND WHINE FOLLOWED BY ENGINE CHIP LIGHT. TEAR DOWN INSPECTION REVEALED 3RD STAGE WHEEL EXHIBITED RIM BREAK OU	T OF 1.75 INCH AND .25 INCH OF 3 EACH BLADES. SUSPECT CAUSE OF FAILURE TO BE A STRESS CRACK ORIGINATING ON THE LEADING E	DGE SIDE OF BREAK OUT IN REFERENCE TO DIRECTION OF ROTATION, ON THE TRAILING EDGE OF RIM SHROUD AND PROGRESSED APPROXIMA	TELY ONE-HALF OF CHORDAL LENGTH UNTIL OVERLOAD. POWER TURBINE SECTION EXHIBITS EXCESSIVE KNIFE AND SEAL CONTACT, FOD, A	ND BEARING AREA DAMAGE. TOTAL CYCLES, 1,140.		1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200547	19951222	00547	GL 	1995	12	22	95ZZZX6874 	2	19951126	G	7250	23001977	WHEEL 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					TURB 3RD STGE	RIM BREAK OUT 	G	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	21240	558 			HX91192	45647	CAE860702			LOUD GRINDING, HIGH PITCH SQUEAL ACCOMPANIED BY TORQUE FLUCTUATIONS. TEAR DOWN INSPECTION REVEALED 3RD STAGE WHEEL EXHI	BITED RIM BREAK OUT OF 1.50 INCHES AND .25 INCH OF 2 EACH BLADES. SUSPECT CAUSE OF FAILURE TO BE A STRESS CRACK ORIGINA	TING ON THE LEADING EDGE SIDE OF BREAK OUT IN REFERENCE TO DIRECTION OF ROTATION, ON THE TRAILING EDGE OF RIM SHROUD AND	 PROGRESSED APPROXIMATELY ONE-HALF OF CHORDAL LENGTH UNTIL OVERLOAD. POWER TURBINE SECTION EXHIBITS EXCESSIVE KNIFE AND	 SEAL CONTACT AND BEARING AREA DAMAGE. TOTAL CYCLES 980.		1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200548	19951222	00548	SW 	1995	12	22	95ZZZX6875 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	175AL	481 	359 			52117				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 480.8 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1995122200549	19951222	00549	SW 	1995	12	22	95ZZZX6876 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	175AL	481 	359 			52117				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 480.8 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1995122200550	19951222	00550	SW 	1995	12	22	95ZZZX6877 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	348AL	481 	335 			51386				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 480.8 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200551	19951222	00551	SW 	1995	12	22	95ZZZX6878 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	348AL	481 	335 			51386				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 480.8 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200552	19951222	00552	SW 	1995	12	22	95ZZZX6879 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	346AL	503 				51378				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 502.6 HOURS.				1	G	7	1 	3U				H2SW 					 
1995021000284	19950210	00284	SO 	1995	2	10	95ZZZX688 	1	19950129	G	7922	53E29600	VERNATHERM VALVE			PIPER 	PA31 	PA31350 	7103110	SO 										ENGINE OIL	DEFECTIVE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	3582X				41677	318052105				VERNATHERM VALVE DOES NOT MOVE UNTIL OIL TEMPERATURE REACHES 235 DEGREES FAHRENHEIT. RED-LINE IS 245 DEGREES FAHRENHEIT	.					1	L	7	2 	3O				A20SO 					 
1995122200553	19951222	00553	SW 	1995	12	22	95ZZZX6880 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	346AL	503 				51378				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 502.6 HOURS.				1	G	7	1 	3U				H2SW 					 
1995122200554	19951222	00554	SW 	1995	12	22	95ZZZX6881 	1	19951110	G	6510	206040370011	DRIVESHAFT 			BELL 	206 	206L1 	1182107	SW 										T/R DRIVE TRAIN	DEBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3185P	9681 	4783 		VNMK47352	45775				DURING 4,800-HOUR INSPECTION, FOUND T/R DRIVE SHAFT FORWARD BONDED COUPLING DEBONDING.						1	G	7	1 	3U				H2SW 					 
1995122200555	19951222	00555	SW 	1995	12	22	95ZZZX6882 	1	19951110	G	6510	206040370011	DRIVESHAFT 			BELL 	206 	206L1 	1182107	SW 										T/R DRIVE TRAIN	DEBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	206SL	9224 	4428 		VNMK48551	45245				DURING UNSCHEDULED MAINTENANCE, FOUND T/R DRIVESHAFT FORWARD BONDED COUPLING DEBONDING.						1	G	7	1 	3U				H2SW 					 
1995122200556	19951222	00556	GL 	1995	12	22	95ZZZX6883 	2	19951109	G	7240	23038218	1ST STAGE NOZZLE		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					HOT SECTION	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2785R	1635 			ER220597	S642	CAE270093			DURING PRE-FLIGHT OF AIRCRAFT, FOUND BURNED AND CRACKED AIRFOIL VANES AND CRACKS IN OUTER BAND. PART IS SCRAPPED.						1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995122200557	19951222	00557	SW 	1995	12	22	95ZZZX6884 	1	19951110	G	6230	206010450117	SWASHPLATE 			BELL 	206 	206L3 	1182108	SW 										MAST	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	365AL				JIJG09608	51376				DURING MAINTENANCE, FOUND AND SCRAPPED 1 EACH WORN BEARING SET P/N 206-010-440-001, S/N NH21854, TT 1973.7, 2 EACH WORN 	BEARING SLEEVES P/N 206-010-459-001, TT 1973.7, 2 EACH WORN BUSHINGS P/N 206-010-421-011, TT 1973.7, 2 EACH WORN BEARING	S P/N 206-010-441-001, TT 1973.7, 2 EACH WORN BEARINGS P/N 206-010-470-101, TT 1973.7 IN OUTER HOUSING.				1	G	7	1 	3U				H2SW 					 
1995122200558	19951222	00558	GL 	1995	12	22	95ZZZX6885 	2	19951109	G	7250	23008054	1ST NOZZLE 		23031899 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					G.P. SECTION	ERODED VALVE 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27554	2929 	1444 		MK194600AL1	45246	CAE860443			UPON DISASSEMBLY OF TURBINE, INSPECTION OF PARTS FOR LOWER POWER FOUND BURNED AND ERODED VANE L.E. AND T.E.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200559	19951222	00559	GL 	1995	12	22	95ZZZX6886 	2	19951110	G	7250	23031866	NR 2 NOZZLE 		23031899 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					G.P. SECTION	ERODED VANE 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27554	2926 	1444 		X49954AL1	45246	CAE860443			UPON DISASSEMBLY OF TURBINE, INSPECTION OF PARTS FOR LOW POWER FOUND BURNED AND ERODED VANE L.E. AND T.E.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200560	19951222	00560	GL 	1995	12	22	95ZZZX6887 	2	19951109	G	7250	6851531	4TH STG NOZZLE 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					P.T. SECTION	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2785R		1638 		H23736	S642	CAE270093			DURING PRE-FLIGHT OF AIRCRAFT, FOUND 4TH STAGE NOZZLE WITH CRACKED DIAPHRAGM.						1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995122200561	19951222	00561	NE 	1995	12	22	95ZZZX6888 	1	19951109	G	6210	7615009043051	TIP CAP 			SKRSKY	S76 	S76 	8143010	NE 										M/R	DEBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	703AL		500 		A17500231	760266				FOUND AT 500-HOUR INSPECTION, INNER CRESCENT DOUBLER DEBONDED UNDER C-CHANNEL. COMPONENT MODEL NR 7615009000049.						1	G	7	2 	3U				H1NE 					 
1995122200562	19951222	00562	NE 	1995	12	22	95ZZZX6889 	1	19951109	G	6210	7615009043051	TIP CAP 			SKRSKY	S76 	S76 	8143010	NE 										M/R	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	703AL		500 		A17500742	760266				DURING 500-HOUR M/R INSPECTION, CRACK FOUND AT HOLE ON UPPER INNER CRESCENT DOUBLER. COMPONENT NR 7615009100051.						1	G	7	2 	3U				H1NE 					 
1995021000285	19950210	00285	SO 	1995	2	10	95ZZZX689 	2	19950123	G	8520	646476	CONNECT ROD 			CESSNA	310 	310R 	2074245	CE 	CONT 	O520 	IO520MB 	17032	SO 					NR 6 CYLINDER	BROKE 	H				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SW	17	3208M	2352 	690 			310R1875	236373R			NR 6 CYLINDER CONNECTING ROD ASSY, PN 646476, BROKE MIDWAY DOWN ROD. AIRCRAFT WAS IN LEVEL FLIGHT AT 3,000 AGL. FIFTEE	N MINUTES AFTER TAKEOFF, CAUSE UNKNOWN.					1	L	7	2 	3O	3	O		3A10 	E5CE				 
1995122200563	19951222	00563	GL 	1995	12	22	95ZZZX6890 	2	19951109	G	7323	2526146	SPOOL BUSHING 		252466712 	AEROSP	AS355 	AS355F 	8680806	EU 	ALLSN 	250C 	250C20 	03013	GL 					DRIVE SHAFT	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5787E	1288 			27192	5058				DURING TEAR DOWN, FOUND GOVERNOR HAD WORN SPOOL BUSHING. CAUSES POSSIBLE ENGINE VIBRATION.						1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1995122200564	19951222	00564	SW 	1995	12	22	95ZZZX6891 	1	19951110	G	3213	206030104023	FITTING 			BELL 	206 	206L1 	1182107	SW 										LT CROSS TUBE	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2755N					45243				DURING DAILY SERVICE CHECK, FOUND LT CROSS-TUBE FITTING WAS CRACKED IN THE SAME MANNER AS REPORTED ON MDR'S SUBMITTED ON	 7-31-95 AND 5-8-95, AND FURTHER REPORTED CRACKED FITTINGS.					1	G	7	1 	3U				H2SW 					 
1995122200565	19951222	00565	NE 	1995	12	22	95ZZZX6892 	1	19951117	G	2611	30326E7	CONTROL AMP 			SKRSKY	S76 	S76A 	8143006	NE 										BAGGAGE	INOPERATIVE 	A			ALGA	O				OTHER 				N			FALSE WARNING 			CR	CRUISE 	1			SW	03	741SW				8579	760070				BAGGAGE COMPARTMENT SMOKE DETECTOR LIGHT ILLUMINATED DURING FLIGHT. NO FIRE. DURING TROUBLESHOOTING, FOUND SMOKE DETEC	TOR CONTROL AMP INOPERATIVE. REPLACED CONTROL AMP.					1	G	7	2 	3U				H1NE 					 
1995122200566	19951222	00566	SW 	1995	12	22	95ZZZX6893 	1	19951110	G	6410	206010765001	BEARING 		206011810139	BELL 	206 	206L4 	1182110	SW 										OUTER RACE	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	170AL	1387 				52063				FOUND ON DAILY INSPECTION, 4 EACH FEATHERING BEARINGS ON BLADES WORN BEYOND LIMITS.						1	G	7	1 	3U			NC	H2SW 					 
1995122200567	19951222	00567	GL 	1995	12	22	95ZZZX6894 	2	19951114	G	7210	6898785	PTO GEAR 		23035179 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					GEARBOX	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	709AL		2850 		CG56557	760278	CAE890465S			4-24-95 - RECEIVED GEARBOX FROM A/C N709AL-PTN WITH PTO GEAR CRACKED. CONDITION - FOUND PTO GEAR CRACKED AT FWD END ABO	VE SPLINED AREA. SUSPECT OVERTORQUE ON OUTPUT SHAFT.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995122200568	19951222	00568	GL 	1995	12	22	95ZZZX6895 	2	19951114	G	7250	23055438	NR 2 NOZZLE 		23035128 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					G.P. SECTION	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	708AL	4566 	1514 		X57635AL2	760277	CAE890101S			AIRCRAFT POWER CHECK PROBLEM. FOUND CRACKED OUTERBAND AND BURNED VANE L.E. AND T.E.						1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995122200569	19951222	00569	SW 	1995	12	22	95ZZZX6896 	1	19951114	G	6310	206040015103	DRIVE SHAFT 			BELL 	206 	206B 	1181511	SW 										INPUT DRIVE	OVERHEAT 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	209AL	6487 	85 		A2001806	1044				DURING DAILY INSPECTION FOUND INDICATORS TURNED BLACK (YELLOW) BOTH COUPLINGS, GREASE FOUND NORMAL CONDITION. PROSEAL S	HOWED SIGNS OF OVERHEAT.					1	G	7	1 	3U				H2SW 					 
1995122200570	19951222	00570	SW 	1995	12	22	95ZZZX6897 	1	19951114	G	6310	206040015103	DRIVE SHAFT 			BELL 	206 	206B 	1181511	SW 										ROTOR BRAKE END	OVERHEAT 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	209AL	7343 	3 		A2001085	1044				LOW TEMP INDICATOR TURNED BLACK ON ROTOR BRAKE END OF SHAFT. PROSEAL ON INSIDE OF COUPLING SHOWS SIGNS OF OVERHEATING. 	 CAUSE UNKNOWN, GREASE IN NORMAL CONDITION.					1	G	7	1 	3U				H2SW 					 
1995122200571	19951222	00571	SW 	1995	12	22	95ZZZX6898 	1	19951114	G	2913	206076030101	PUMP 			BELL 	206 	206L4 	1182110	SW 										DRIVE	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	171AL	2214 			272555	52064				DURING A GROUND RUN, HYDRAULICS WOULD NOT COME ON LINE. DURING TROUBLESHOOTING, FOUND THE SPLINES ON HYDRAULIC PUMP WER	E WORN. HYDRAULIC PUMP AND MAIN ROTOR TACH GENERATOR WERE REPLACED. THE PUMP IS MOUNTED ON THE TACH GENERATOR AND DRIV	EN BY SAME. THE SPLINES ON THE TACH GENERATOR WERE WORN ALSO.				1	G	7	1 	3U			NC	H2SW 					 
1995122200572	19951222	00572	SW 	1995	12	22	95ZZZX6899 	1	19951114	G	6230	206010450117	SWASHPLATE 			BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350AL				RE45	51429				DURING NIGHT INSPECTION, FOUND WORN BEARINGS AND BUSHINGS CAUSING INNER RING AND SLEEVE PLAY. PARTS REQUIRING REPLACEME	NT: 2 EACH 206-010-470-101 BEARINGS, 1 EACH 206-010-459-001 BEARING, 2 EACH 206-010-421-001 BUSHINGS, 2 EACH 206-010-42	1-003 BUSHINGS, 2 EACH 206-010-441-001 BEARINGS.				1	G	7	1 	3U				H2SW 					 
1995021000286	19950210	00286	CE 	1995	2	10	95ZZZX690 	1	19950113	G	2140	B3040	HEATER 	JANITROL 		BEECH 	58 	58 	1152740	CE 										COMB LINER	LINER CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	472TL	2400 				TH1112				WHILE COMPLYING WITH AD 82-07-3, FOUND COMBUSTION LINER CRACKED. REPLACED LINER WITH NEW. HEATER OPERATION CHECKED GOO	D. AD IS 13 YEARS OLD, PERHAPS RE-ISSUE, SO IT IS NOT FORGOTTEN.					1	L	7	2 	3O				3A16 					 
1995122200573	19951222	00573	SW 	1995	12	22	95ZZZX6900 	1	19951114	G	6410	206016201127	BLADE 			BELL 	206 	206L1 	1182107	SW 										T/R HUB	PAINT PEEL 	B			ALGR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	1084Y	814 			C6668	45433				DURING NORMAL MAINTENANCE, FOUND PAINT PEELING FROM LEADING EDGE OF BLADES, BEARINGS WORN.						1	G	7	1 	3U				H2SW 					 
1995122200574	19951222	00574	SW 	1995	12	22	95ZZZX6901 	1	19951114	G	6410	206016201127	BLADE 			BELL 	206 	206L1 	1182107	SW 										T/R HUB	PAINT PEEL 	B			ALGR	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	1084Y	814 			CS6500	45433				DURING NORMAL MAINTENANCE, FOUND PAINT PEELING FROM LEADING EDGE OF BLADES, BEARINGS WORN.						1	G	7	1 	3U				H2SW 					 
1995122200575	19951222	00575	SW 	1995	12	22	95ZZZX6902 	1	19951114	G	6510	206040339009	BEARING 		206040930009	BELL 	206 	206B 	1181511	SW 										HANGAR ASSY	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5008K	1979 				2524				DURING DAILY INSPECTION, FOUND BEARING HAS PLAY AND GREASE LOSS - REPLACED BEARINGS.						1	G	7	1 	3U				H2SW 					 
1995122200576	19951222	00576	SW 	1995	12	22	95ZZZX6903 	1	19951030	G	7120	206062101001	ENGINE LEG 			BELL 	206 	206B 	1181511	SW 										LT FWD ENG MT	DEFECTIVE 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27574					2562				WHEN INSTALLING LEGS TO AIR FRAME, FOUND UPPER END OF LEG AT WELD CONTACTS OTHER LEG.						1	G	7	1 	3U				H2SW 					 
1995122200577	19951222	00577	SW 	1995	12	22	95ZZZX6904 	1	19951108	G	6230	206010450117	SWASHPLATE 			BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	365AL				JIJG09608	51376				DURING MAINTENANCE, SCRAPPED 1 EACH WORN BEARING SET P/N 206-010-440-001, S/N NH21854, TT 1973.7, 2 EACH WORN BEARINGS S	LEEVES, P/N 206-010-459-001, TT 1973.7, 2 EACH WORN BUSHINGS P/N 206-010-421-011, TT 1973.7, 2 EACH WORN BEARINGS, P/N 2	06-010-441-001, TT 1973.7, 2 EACH WORN BEARINGS P/N 206-010-470-101, TT 1973.7 IN OUTER HOUSING.				1	G	7	1 	3U				H2SW 					 
1995122200578	19951222	00578	SW 	1995	12	22	95ZZZX6905 	1	19951108	G	6510	206040370011	DRIVESHAFT 			BELL 	206 	206L1 	1182107	SW 										T/R	DEBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57334	10880	4470 		TMK50251	45445				UPON REMOVAL FROM HELICOPTER, FOUND T/R DRIVESHAFT FORWARD BONDED COUPLING DEBONDED.						1	G	7	1 	3U				H2SW 					 
1995122200579	19951222	00579	SW 	1995	12	22	95ZZZX6906 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D	518 				45280				DAILY INSPECTIONS FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 	SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.7.				1	G	7	1 	3U				H2SW 					 
1995122200580	19951222	00580	SW 	1995	12	22	95ZZZX6907 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2762D	518 				45280				DAILY INSPECTIONS FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 	SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.7.				1	G	7	1 	3U				H2SW 					 
1995122200581	19951222	00581	SW 	1995	12	22	95ZZZX6908 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A	518 				45256				DAILY INSPECTIONS FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 	SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.7.				1	G	7	1 	3U				H2SW 					 
1995122200582	19951222	00582	SW 	1995	12	22	95ZZZX6909 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2756A	518 				45256				DAILY INSPECTIONS FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 	SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-1	01 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 517.7.				1	G	7	1 	3U				H2SW 					 
1995021000287	19950210	00287	CE 	1995	2	10	95ZZZX691 	1	19950130	G	7712	AE366161L50113	HOSE 			CESSNA	208 	208B 	2073701	CE 	PWA 	PT6 	PT6A114 	52043	NE 					TORQUE PSI	LEAKING 	B		A	MJ7R	O				OTHER 				K	B		FLUID LOSS 	SMOKE/FUMES/ODORS/SPARKS 		NR	NOT REPORTED 	1			GL	05	4667B	1078 			00624	208B0163				PILOT REPORTED SMOKE IN CABIN DURING HEATER OPERATION. TROUBLESHOT SYSTEM, FOUND ENGINE OIL IN HEATER. FOUND OIL LEAKI	NG OUT OF TORQUE PSI LINE. THE OIL SPRAY WAS INJESTED BY HEATER. REPLACE TORQUE PSI LINE AND HEATER SYSTEM, CHECKED OK	AY. LINE WAS MFG IN 1988 AND WAS TEFLON RATED TO 1500 PSI.				1	H	7	1 	3T	3	T		A37CE 	E4EA				 
1995122900050	19951229	00050	SW 	1995	12	29	95ZZZX6910 	1	19951109	G	5302	A3050	SKIN 			BELL 	206 	206BELL 	1181502	SW 										TAILBOOM	MISMANUFACTURED 	B			ALGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03					384					WHEN TRYING TO LAY OUT RIVET PATTERN ON SEAMS, FOUND FORWARD END IS NOT WIDE ENOUGH FOR PROPER EDGE DISTANCE ON RIVET PA	TTERN (CIRCUMFERENCE). PART WAS TRIMMED TOO NARROW AT MFG.					1	G	7	1 	3U				H2SW 					 
1995122900051	19951229	00051	SW 	1995	12	29	95ZZZX6911 	1	19951130	G	2823	610289003	VALVE 			MOONEY	M20 	M20J 	5870219	SW 										FUEL SELECTOR	SEIZED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	201BS	1556 				241306				PRIOR TO TAKEOFF WHILE SWITCHING FROM LEFT TO RIGHT FUEL TANK, THE SELECTOR VALVE FROZE IN THE RIGHT TANK POSITION.						1	L	7	1 	3O				2A3 					 
1995122900052	19951229	00052	CE 	1995	12	29	95ZZZX6912 	1	19951018	G	5312	24130013	BULKHEAD 			CESSNA	172 	172RG 	2072438	CE 										RUD BAR ATTACH	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	6280R	4557 				172RG0141				DURING ANNUAL INSPECTION, IT WAS DETERMINED THAT BOTH UPPER AND LOWER BULKHEADS WERE CRACKED NEAR RUDDER BAR ATTACH POIN	TS. P/N 241001-3, 241001-4, 241001-5, AND 241001-6. BULKHEADS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 	 SUBMITTER SUGGESTS CLOSE ATTENTION BE PAID TO THIS AREA DURING ROUTINE INSPECTIONS. POSSIBLE RE-ENFORCEMENT IS NEEDED 	IN THIS AREA.			1	H	7	1 	3O				3A17 					 
1995122900053	19951229	00053	CE 	1995	12	29	95ZZZX6913 	1	19951101	G	5313	002440029	STRINGER 			BEECH 	58 	58 	1152740	CE 										AFT PAX AREA	CORRODED 	E	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	8180R	7400 	7400 			TH522				REMOVED FLOORBOARDS IN AFT PASSENGER AREA AND FOUND TOPS OF STRINGER SEVERELY CORRODED. P/N 95-43038-119, DASH 120, DAS	H 36, DASH 35. P/N 002-440029-3, DASH 4. SUSPECT CAUSE, URINE SEEPAGE INTO AFT SECTOR. AIR AMBULANCE OPERATION.					1	L	7	2 	3O				3A16 					 
1995122900054	19951229	00054	CE 	1995	12	29	95ZZZX6914 	1	19951112	G	2140	8259	HEATER 	STWARNER 		CESSNA	310 	310R 	2074245	CE 										TERMINAL BLOCK	MISREPAIRED 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	07	2FOR				HR2	310R0912				CABIN HEAT WAS TOO HOT. NOT ABLE TO CONTROL HEAT. DURING TROUBLESHOOTING, FOUND THAT DURING SOME PREVIOUS 'REPAIR', JU	MPER WIRES WERE ADDED TO TERMINAL BLOCKS TO MAKE HEATER RUN CONTINUOUSLY. THIS ACTION NEGATED ALL THE HEAT REGULATING S	AFETY DEVICES, (THERMOSTAT, DUCT LIMIT SWITCH, AND OVERHEAT SWITCH); THUS, ALLOWING HEATER TO RUN TO VERY HIGH UNCONTAIN	ED TEMPERATURES. SEVERE HEAT DAMAGE WAS FOUND TO HEATER AND HEAT DUCTING, (THERMOSTAT SENSOR SPRING HAD MELTED OFF). A	DDITIONAL DAMAGE WAS FOUND TO SURROUNDING WIRING AND AIRCRAFT STRUCTURES. FOUND SEVERAL PLACES WHERE INSULATION HAD BEE	N ON FIRE AND THEN SELF-EXTINGUISHED. REQUIRED EXTENSIVE REPLACEMENT OF COMPONENTS.	1	L	7	2 	3O				3A10 					 
1995122900055	19951229	00055		1995	12	29	95ZZZX6915 	1	19951120	G	7714	KT7	TACHOMETER 																	ENGINE	ERRORS 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	27					940319					NEW TACHOMETER RECEIVED FROM WAG AERO, INC. NO MAKE, MODEL, OR S/N ON HOUSING. CERTIFICATE WHICH ACCOMPANIED TACHOMETE	R SUPPLIED, MODEL AND S/N TO TSO NUMBER. TACHOMETER WOULD NOT INDICATE PROPER RPM (500-600 RPM ERROR).																		 
1995122900056	19951229	00056	CE 	1995	12	29	95ZZZX6916 	1	19951113	G	5711	0426300	SPAR 			CESSNA	150 	150K 	2071822	CE 										LT WING	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	6141G	2500 				15071641				AFTER FLIGHT WHILE PERFORMING ACCELERATED STALLS, 6 RIVETS WERE FOUND MISSING FROM TOP OF SPAR BETWEEN STRUT ATTACH AND 	THE LANDING LIGHT AREA. A HOLE WAS MADE PER CESSNA MANUAL INSTUCTIONS AND THE SPAR CAP ANGLE WAS FOUND SEVERELY CORRODE	D. NO ACCESS AVAILABLE IN THIS AREA FOR REGULAR INSPECTION. INSPECTION PANELS WILL BE INSTALLED PER C150 SERIES MM, TO	 ACCESS FOR INSPECTION AND CORROSION CONTROL.			1	H	7	1 	3O				3A19 					 
1995122900057	19951229	00057	SO 	1995	12	29	95ZZZX6917 	1	19951104	G	2710	4270204	CONTROL CABLE 			PIPER 	PA25 	PA25260 	7102508	SO 										RT/LT AILERON	WORN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	8578L	5347 				255004				INSPECTION FOUND SEVERELY WORN RT AND LT UPPER AILERON CABLES RIGHT INSIDE THE WING ROOT WHERE CABLE ROLLS WITH A PULLEY	. THERE WAS NO WORN PULLEYS. CABLE WAS SO BADLY WORN - 6 OF THE 7 BUNDLES OF STRANDS WERE BROKEN. IT IS IN AN AREA THA	T IS HARD TO SEE. SUBMITTER STATED SHOULD BE INSPECTED AND, IF NECESSARY, REPLACE AILERON CABLES.				1	L	7	1 	3O			 	2A10 					 
1995122900058	19951229	00058	CE 	1995	12	29	95ZZZX6918 	1	19950908	G	2913	12805101	POWER PACK VALVE	OZONE 		CESSNA	210 	210E 	2073416	CE 										MLG HYD	FAILED 	D				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			NM	11	2331F					21058531				PILOT ATTEMPTED TO LOWER LANDING GEAR. PILOT WAS UNABLE TO LOWER LANDING GEAR USING NORMAL OR EMERGENCY PROCEDURES WHIC	H RESULTED IN A GEAR-UP LANDING. FURTHER INVESTIGATION REVEALED THAT POWER PACK SECONDARY RELIEF VALVE WAS STUCK OPEN, 	THEREFORE, BYPASSING THE HYDRAULIC FLUID. HYDRAULIC POWER PACK WAS SENT IN FOR A TEAR DOWN AND OVERHAUL AT WHICH TIME S	ECONDARY RELIEF VALVE WAS REMOVED AND PLUGGED. SECONDARY RELIEF VALVE IS NOT NECESSARY FOR POWER PACK TO FUNCTION NORMA	LLY.		1	H	7	1 	3O				3A21 					 
1995122900059	19951229	00059		1995	12	29	95ZZZX6919 	4	19951024	G	2210	Q211	TRANSISTOR 	KING 	KC192 	CESSNA	208 	208B 	2073701	CE 										AP PITCH CONTROL	FAILED 	B			MT9R	O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	05	9469B				51268	208B0079				AUTOPILOT WOULD NOT DISENGAGE IN PITCH CONTROL DUE TO SHORTED Q-211 (PITCH ENGAGE TRANSISTOR) SUPPLYING CONTINUOUS POWER	 TO PITCH SERVO-CLUTCH. AUTOPILOT WAS ABLE TO BE DISENGAGED BY HOLDING DOWN AUTOPILOT DISCONNECT BUTTON AND PULLING AUT	OPILOT CIRCUIT BREAKER.				1	H	7	1 	3T				A37CE 					 
1995021000288	19950210	00288	CE 	1995	2	10	95ZZZX692 	1	19950126	G	5551		ATTACH 			CESSNA	421 	421B 	2076014	CE 										STAB TO FUSELAGE	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11										DURING INSPECTION AND LOADING OF HORIZONTAL STABILIZER, STRUCTURAL NOISE IN FORM OF KNOCKS, SNAPPING, AND/OR CREAKING (O	UTSIDE OF NORMAL SKIN OIL CANNING EVIDENT ON THIS MODEL A/C) EXISTING IN HORIZ STAB. NOISE HAS BEEN TRACED TO MOVEMENT 	AT HORIZ. STAB. FRONT SPAR-TO-FUSELAGE ATTACH, NAS 1306-3, BOLTS (2 EACH). BOLT REMOVAL HAS DISCLOSED NO CRACKS IN STRU	CTURE TO DATE. IT APPEARS THIS IS A DESIGNED LOOSE FIT JOINT WITH BOLT GRIP THAT IS SLIGHTLY TOO LONG. ADDITION OF ONE	 WASHER AND RETORQUE OF NUT WILL RESTORE BOLT CLAMP-UP AND RESOLVE PROBLEM.		1	L	7	2 	3O				A7CE 					 
1995122900060	19951229	00060	SW 	1995	12	29	95ZZZX6920 	1	19951125	G	3211	12266	ATTACH LUG 			BBAVIA	7 	7EC 	2110120	SW 										MLG	FAILED 	G				K				NONE 				O			OTHER 			LD	LANDING 	1			GL	19	7433B	3139 				7EC471				LANDING GEAR ATTACHMENT POINT LUGS WERE WORN TO THE POINT OF FAILURE. THE BOLT HOLES WERE ELONGATED. THE RIGHT FORWARD	 LUG CRACKED AT THE BOLT HOLE. THE LANDING GEAR FOLDED ON LANDING. THE PILOT REPORTED A DIFFERENT PILOT HAD DONE A 'WH	EELS ON' LANDING ON THE TURF RUNWAY WHICH CROSSES THE HARD SURFACE RUNWAY AND STILL HAD A BIT OF SPEED WHEN CROSSING THE	 HARD SURFACE.			1	H	7	1 	3O				A759 					 
1995122900061	19951229	00061	CE 	1995	12	29	95ZZZX6921 	1	19951114	G	5321	04102381	FLOOR PAN 			CESSNA	150 	152 	2071835	CE 										COPILOT SIDE	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	757YQ	10794				15280113				COPILOT INBOARD SEAT RAIL AFT END, STA 27.02 TO STA 56.69, FOUND FLOORBOARD CRACKED AT AFT END OF INBOARD SEAT RAIL (COP	ILOT SIDE). THE CRACK WAS 2 INCHES IN LENGTH AND CORRESPONDED DIRECTLY WITH THE AFT END OF THE SEAT RAIL. THE FLOOR BE	GINS TO CONTOUR UPWARD AT THIS LOCATION. SUBMITTER RECOMMENDATION: PUT A SLIGHT BEVEL ON THE AFT END OF SEAT RAILS, TH	EREBY, PREVENTING A STRESS RISER IN THE AREA. NOTE: THIS DEFECT HAS BEEN FOUND ON SEVERAL C-152'S IN FLEET.			1	H	7	1 	3O			NT	3A19 					 
1995122900062	19951229	00062	SO 	1995	12	29	95ZZZX6922 	2	19950929	G	7322	AN123956	O-RING 		6467661 	BEECH 	36 	A36 	1151604	CE 	CONT 	O550 	IO550B 		SO 					FUEL INJ PUMP	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	13	4736M	821 				E2243				FUEL STAINS NOTED ON OIL FILTER, LOWER LEFT FIREWALL. FUEL WAS LEAKING IN A HIGH PRESSURE STREAM FROM A BAD 'AN' 123956	 O-RING ON THE LEFT SIDE OF ENGINE DRIVEN FUEL INJECTOR PUMP HIGH PRESSURE METERING SCREW. THIS FUEL GLANCED OFF THE OI	L FILTER, HIT THE LOWER LT CORNER OF THE FIREWALL JUST ABOVE THE COWL FLAP OPENING, AND POURED DOWN ON THE EXHAUST PIPE.	 STAINS INDICATED IT HAD BEEN LEAKING FOR PROBABLY SEVERAL FLIGHTS. COULD HAVE CAUSED A MAJOR IN-FLIGHT FIRE AT ANY TI	ME. NO REASON FOR SUDDEN LEAKAGE, AS SCREW HAD NOT BEEN ADJUSTED AT ANY RECENT TIME.		1	L	7	1 	3O	3	O		3A15 	E3SO				 
1995122900063	19951229	00063	SO 	1995	12	29	95ZZZX6923 	1	19951019	G	5313	86454003	STRINGER 			PIPER 	PA44 	PA44180 	7104402	SO 										NOSE AREA	CRACKED 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	192ND	3826 				4495004				FOUND NOSE GEAR TUNNEL STRINGERS BOTH CRACKED WHERE NOSE GEAR DRAG BRACE BOLTS TO TUNNEL SIDEWALLS. SUBMITTER STATED TH	IS IS 3RD AIRCRAFT IN FLEET OF 9 TO HAVE THIS PROBLEM. OTHER AIRCRAFT HAD APPROXMATELY 3,300 HOURS ON THEM.					1	L	7	2 	3O				A19S0 					 
1995122900064	19951229	00064	SO 	1995	12	29	95ZZZX6924 	1	19951102	G	7160	8624531	AIR BOX ASSY 			PIPER 	PA44 	PA44180 	7104402	SO 										FLAPPER VALVE	GROMMET MISSING 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	694CB	994 				447995305				THE FLAPPER VALVE ON THE PA44180 AIR BOX PIVOTS ON TWO COMBINATION RUBBER GROMMET/NYLON BUSHINGS (MS35189). DURING A 10	0-HOUR INSPECTION, THIS GROMMET/BUSHNG COMBINATION WAS FOUND MISSING FROM THE BOTTOM OF THE ASSY LEAVING A GAPPING HOLE 	IN THE BOTTOM OF THE AIR BOX THROUGH WHICH UNFILTERED AIR COULD PASS. IN ADDITION, THE ABSENCE OF THE GROMMET REVEALED 	THE FLAPPER VALVE SHAFT HAD WORN TO ONE-HALF ITS ORIGINAL DIAMETER.			1	L	7	2 	3O				A19S0 					 
1995122900065	19951229	00065	SO 	1995	12	29	95ZZZX6925 	1	19951124	G	3230	67031003	FITTING 			PIPER 	PA34 	PA34200 	7103405	SO 										RT MLG RETRACT	CRACKED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	1025U	3441 				347250005				RIGHT GEAR RETRACTION FITTING FOUND CRACKED AROUND BOTH BOLT HOLES WHERE EXTENSION ROD ATTACHES TO FITTING. FOUND INSID	E LEG OF FITTING TO HAVE BEEN PREVIOUSLY CRACKED.					1	L	7	2 	3O				A7SO 					 
1995122900067	19951229	00067	CE 	1995	12	29	95ZZZX6927 	1	19951104	G	3720	C668519L0105	GAUGE 	AIRBORNE 	44CW 	CESSNA	210 	P210N 	2073454	CE 										INST PANEL VAC	CONTAMINATED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			WP	01	4706A	717 			12AB1760	P21000817				THE AIRCRAFT IS EQUIPPED WITH A DUAL VACUUM SYSTEM. THE SUCTION GAUGE FILLED WITH CARBON DUST DURING A VACUUM PUMP FAIL	URE. THIS OBSCURED THE PILOT'S INDICATION OF A LEFT OR RIGHT VACUUM PUMP FAILURE (RED BALL), SINCE THE GAUGE STILL SHOW	ED VACUUM IN THE GREEN ARC UNTIL THE SECOND VACUUM PUMP FAILED AND THE GAUGE WENT TO ZERO.				1	H	7	1 	3O				3A21 					 
1995122900068	19951229	00068	EA 	1995	12	29	95ZZZX6928 	2	19950915	G	7414	10382681	CAPACITOR 		D6LN3000 	CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540J3C5 	41532	EA 					LT MAG	FAULTY 	B			DF1R	K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			EA	17	6562S	163 			B249501G	R18201691	L2232240A			ENGINE EXPERIENCED EXTREME ROUGHNESS AND HIGH RPM DROP ON LEFT POSITION OF 1800 RPM MAG CHECK. NR 4 AND NR 5 CYLINDERS 	WENT COLD ON G.E.M. FOR 3 SUCCESSIVE CHECKS. PLUGS AND WIRES CHECKED OK TO BOTH CYLINDERS. MAG WAS REMOVED AND INSPECT	ED WITH NO OBVIOUS DEFECTS NOTED. INSTALLED NEW TCM MAGNETO AND CAPACITORS AND RAN UP, OPERATIONALLY CHECKED OK. FURTH	ER DISASSEMBLY OF REMOVED MAGNETO REVEALED NO COIL, ROTOR, POINT, OR DISTRIBUTOR BLOCK DEFECTS, BUT ONE CAPACITOR WILL I	NTERMITTENTLY CHECK ABNORMALLY LOW MICROFARAD READINGS.		1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1995021000289	19950210	00289		1995	2	10	95ZZZX693 	4	19950101	G	3421	5171196	BASE ASSY 	JET 	501120401 															VERT GYRO	PLATING PEEL 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09										PLATING IS BLISTERING AND PEELING ON THE INSIDE AND OUTSIDE OF BASE ASSEMBLY. LOOSE PLATING CAN POTENTIALLY CAUSE CIRCU	IT SHORTS AND INTERFERE WITH GYRO AXIS FUNCTIONS.																		 
1995122900071	19951229	00071	SO 	1995	12	29	95ZZZX6931 	1	19951122	G	3213	27053005	TRUNNION 			PIPER 	PA24 	PA24260 	7102406	SO 										RT MLG	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	8803P					244258				FOUND SECOND TRUNNION THAT HAS BEEN CRACKED. THIS ONE WAS THE RIGHT MLG. OTHER CRACK ON MODEL PA30, LEFT GEAR. REPLAC	ED WITH 27053-001, WITH SPRING CLAMP DIFFERENT.					1	L	7	1 	3O				1A15 					 
1995122900072	19951229	00072	SO 	1995	12	29	95ZZZX6932 	2	19950927	G	8520	641931981	BOLT 								CONT 	O470 	IO470N 	17026	SO 					CASE THRU-BOLT	FAILED 	B	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99										CRANKCASE THROUGH-BOLT WAS TORQUED TO THE MANUFACTURER'S SPECIFICATIONS. THE NEXT DAY, FOUND IT IN TWO PIECES. SUBMITT	ER STATED THIS IS THE SECOND NEW BOLT TO DO THIS. BROKE AT O-RING GROOVE.										3	O			3E1				 
1995122900073	19951229	00073	CE 	1995	12	29	95ZZZX6933 	1	19951102	G	5741	NAS150R	BOLT 			BEECH 	33 	F33A 	1151425	CE 										WING ATTACH	CRACKED 	B		A	RTAR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	9179Q					CE331				WING ATTACH BOLTS REMOVED FOR 5-YEAR MAGNAFLUX INSPECTION. ONE BOLT, THE UPPER AFT SHOWED INDICATIONS OF A CRACK.						1	L	7	1 	3O				3A15 					 
1995122900074	19951229	00074	GL 	1995	12	29	95ZZZX6934 	2	19951124	G	7250	23056130	COMBUSTION LINER			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					TURB 1ST STAGE	CRACKED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V		520 		278175	490487D	CAE830976			FOUND CRACKS IN THE 1ST SECTION CONE BEYOND LIMITS. RETURNED LINER FOR OVERHAUL ON ALLISON 250, REPORT 159678.						1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995122900075	19951229	00075	GL 	1995	12	29	95ZZZX6935 	2	19951124	G	7250	6890040	SHIELD 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					NR 1 NOZZLE	WARPED 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	4571V		520 		984276	490487D	CAE830976			DURING REPLACEMENT OF NR 1 NOZZLE, THE NR 1 NOZZLE SHIELD WAS FOUND WARPED. SENT IN FOR REPAIR ON ALLISON 250 REPORT NR	 A159679.					1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1995122900076	19951229	00076	WP 	1995	12	29	95ZZZX6936 	1	19951114	G	3213	369H60024	STRUT 			HUGHES	369 	369D 	4470706	WP 										BRACE ATTACH	CRACKED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	8625F					470111D				INSPECTION FOUND STRUT CRACKED AT HOLE FOR THE BRACE ATTACH POINT.						1	G	7	1 	3U				H3WE 					 
1995122900077	19951229	00077		1995	12	29	95ZZZX6937 	1	19951030	G	2432	TB20024	CHARGER 																	BATTERY	BURNED 	B			TI1R	K				NONE 				A			FLAME/FIRE 			NR	NOT REPORTED 	1			SW	05					053534					FIRE AND SMOKE COMING OUT OF CHARGER. BURN MARK ON CASE CAME AFTER THE CHARGER FAILED. THIS WAS A REPLACEMENT PART AGA	INST P. O. 89263.																		 
1995021000290	19950210	00290	SO 	1995	2	10	95ZZZX694 	1	19950116	G	7810		SHROUD 			PIPER 	PA46 	PA46350P 		SO 										EXH CROSSOVER	CLAMPS FAIL 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	888DC	88 				4622067				INVESTIGATION FOR BURNED WIRING IN AREA OF EXHAUST CROSSOVER PIPE, FOUND WORM GEAR TYPE CLAMPS ON SHROUD BROKEN. SHROUD	 WORKS FREE AND CHAFES HOLE IN CROSSOVER PIPE. HOT GASES THEN BURN WIRING. SUBMITTER REPORTS SEEING 4 ACFT WITH THIS C	ONDITION.				1	L	7	1 	3O			RT	A25SO 					 
1995122900305	19951229	00305	SW 	1995	12	29	95ZZZX6945 	1	19951018	G	3340	A469B	FLASH TUBE 			BELL 	206 	206L1 	1182107	SW 										STROBE	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	400SL	36 				45235				STROBE LIGHT INOP. IT WAS A NEW UNIT LESS THAN 2 YEARS OLD PLUS 35.8 HOURS.						1	G	7	1 	3U				H2SW 					 
1995122900306	19951229	00306	SW 	1995	12	29	95ZZZX6946 	1	19951025	G	6710	206062721113	LINEAR ACTUATOR 			BELL 	206 	206B3 	1181506	SW 										M/R	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	705SD	1317 			1746	4291				LINEAR ACTUATOR BECAME INTERMITTENT.						1	G	7	1 	3U				H2SW 					 
1995122900307	19951229	00307	SW 	1995	12	29	95ZZZX6947 	1	19951025	G	7714	206075682105	INDICATOR 			BELL 	206 	206B3 	1181506	SW 										N1 TACHOMETER	ERRATIC 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	705SD	1351 			0370	4291				N1 TACHOMETER HAS ERRATIC NEEDLE ON START.						1	G	7	1 	3U				H2SW 					 
1995122900308	19951229	00308	EU 	1995	12	29	95ZZZX6948 	1	19951025	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL QUANTITY	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	626MB				1150	7109				FUEL QUANTITY INDICATOR DEFECTIVE. NR 1 AND NR 2 SUPPLY GOES TO ZERO.						1	G	7	2 	3U				H13EU 					 
1995122900309	19951229	00309		1995	12	29	95ZZZX6949 	4	19951013	G	3444	066305401	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										RADAR ALTIMETER	LIGHT INOP 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	118LL	34 			5363	7097				RADAR ALTIMETER'S INTERNAL LIGHT INOP.						1	G	7	2 	3U				H13EU 					 
1995021000291	19950210	00291	SO 	1995	2	10	95ZZZX695 	1	19950116	G	7810	40B19974	PIPE 			PIPER 	PA46 	PA46350P 		SO 										EXH CROSSOVER	HOLE CHAFED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	888DC	88 				4622067				INVESTIGATION FOR BURNED WIRING IN AREA OF EXHAUST CROSSOVER PIPE, FOUND WORM GEAR TYPE CLAMPS ON SHROUD BROKEN. SHROUD	 WORKS FREE AND CHAFES HOLE IN CROSSOVER PIPE. HOT GASES THEN BURN WIRING. SUBMITTER REPORTS SEEING 4 ACFT WITH THIS C	ONDITION.				1	L	7	1 	3O			RT	A25SO 					 
1995122900310	19951229	00310	SW 	1995	12	29	95ZZZX6950 	1	19950907	G	6410	206016201127	BLADE 			BELL 	206 	206L1 	1182107	SW 										T/R	BEARING CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	519EH	370 			CS6502	45429				BLADE BEARINGS CRACKED AT 370.4 HRS TT. INSTALLATION DATE WAS 11-30-94.						1	G	7	1 	3U				H2SW 					 
1995122900311	19951229	00311	SW 	1995	12	29	95ZZZX6951 	1	19950907	G	6410	206016201127	BLADE 			BELL 	206 	206L1 	1182107	SW 										T/R	BEARING CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	519EH	370 			CS6161	45429				BLADE BEARINGS CRACKED AT 370.4 HRS TT. INSTALLATION DATE WAS 11-30-94.						1	G	7	1 	3U				H2SW 					 
1995122900312	19951229	00312	SW 	1995	12	29	95ZZZX6952 	1	19951020	G	6230	206010335001	DRIVE LINK 			BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ZV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5759M		256 		RH41576	45555				PLAY IN EXCESS OF .25 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. AT TEAR DOWN, FOUND BEARINGS AND SPACERS WORN.						1	G	7	1 	3U				H2SW 					 
1995122900313	19951229	00313	SW 	1995	12	29	95ZZZX6953 	1	19951007	G	6230	206010335001	DRIVE LINK 			BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ZV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2654		276 		RH0682	45482				PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. AT TEAR DOWN, FOUND BEARINGS AND SPACERS WORN	.					1	G	7	1 	3U				H2SW 					 
1995122900314	19951229	00314	SW 	1995	12	29	95ZZZX6954 	1	19951026	G	6230	206010443001	DUPLEX BEARING 			BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	PITTED 	B			ZV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2618	915 			17910	45503				SWASHPLATE REMOVED DUE TO BEARING ROUGHNESS. FOUND DUPLEX BEARING RACE PITTED DURING DISASSEMBLY AND INSPECTION.						1	G	7	1 	3U				H2SW 					 
1995122900316	19951229	00316	EU 	1995	12	29	95ZZZX6956 	1	19951107	G	6240	117945641	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										MAST MOMENT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	215AE	126 			E080698	7216				INDICATOR UNRELIABLE AND INTERMITTENTLY WILL NOT CALIBRATE. UNIT WAS OVERHAULED IN JULY, 1995, STILL UNDER WARRANTY.						1	G	7	2 	3U				H13EU 					 
1995122900317	19951229	00317	EU 	1995	12	29	95ZZZX6957 	1	19951108	G	2140	HTE920018	VALVE 			BOLKMS	BK117 	BK117C1 	5626025	EU 										ACTUATOR	STUCK 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	347 			255	7505				VALVE STUCK OPEN. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995122900318	19951229	00318	EU 	1995	12	29	95ZZZX6958 	1	19951108	G	2140	HTE920018	VALVE 			BOLKMS	BK117 	BK117C1 	5626025	EU 										ACTUATOR	STUCK 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	903 			237	7505				VALVE STUCK CLOSED. REMOVED AND REPLACED						1	G	7	2 	3U			NC	H13EU 					 
1995122900319	19951229	00319	EU 	1995	12	29	95ZZZX6959 	1	19951108	G	2900	2811T10001	MIXING VALVE 			BOLKMS	BK117 	BK117C1 	5626025	EU 										HYD	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	212 			012	7505				VALVE OPERATION INTERMITTENT. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995021000292	19950210	00292	SO 	1995	2	10	95ZZZX696 	1	19950116	G	7810	40B19850	PIPE 			PIPER 	PA46 	PA46350P 		SO 										EXH CROSSOVER	HOLE CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	888DC	88 				4622067				INVESTIGATION FOR BURNED WIRING IN AREA OF EXHAUST CROSSOVER PIPE, FOUND WORM GEAR TYPE CLAMPS ON SHROUD BROKEN. SHROUD	 WORKS FREE AND CHAFES HOLE IN CROSSOVER PIPE. HOT GASES THEN BURN WIRING. SUBMITTER REPORTS SEEING 4 ACFT WITH THIS C	ONDITION.				1	L	7	1 	3O			RT	A25SO 					 
1995122900320	19951229	00320	EU 	1995	12	29	95ZZZX6960 	1	19951020	G	6210	1051585403	BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R BLADE	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	212AE	284 				7222				INSIDE COATING WORN ON BUSHING. TOTAL OF 8 EACH. SEE MMIR 78451, 78452, AND 78453. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995122900321	19951229	00321	EU 	1995	12	29	95ZZZX6961 	1	19951020	G	6210	10513103505	BLADE PIN 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	SCORED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	212AE	430 				7222				SCORED BLADE PIN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995122900322	19951229	00322	EU 	1995	12	29	95ZZZX6962 	1	19951020	G	6410	134615P	BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	212AE	140 				7222				INSIDE COATING WORN ON BUSHING. REMOVED AND REPLACED 4 EACH.						1	G	7	2 	3U				H13EU 					 
1995122900323	19951229	00323		1995	12	29	95ZZZX6963 	4	19951023	G	2562	E0115	ANTENNA 			BOLKMS	105 	BO105S 	5626006	EU 										ELT	BROKEN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105NG	98 				S632				ELT ANTENNA BROKEN AT BASE. REMOVED AND REPLACED.						1	G	7	2 	3U				H3EU 					 
1995122900324	19951229	00324	EU 	1995	12	29	95ZZZX6964 	1	19951108	G	3310	1179203903	POWER SUPPLY 			BOLKMS	117 	BK117B1 	5626012	EU 										LIGHTING	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	460H				1217	7142				POWER SUPPLY WORKED FOR ABOUT 5 SECONDS. ZERO HOURS SINCE OVERHAUL.						1	G	7	2 	3U				H13EU 					 
1995122900325	19951229	00325	EU 	1995	12	29	95ZZZX6965 	1	19951017	G	3310	1179203103	DIMMER 			BOLKMS	117 	BK117A1 	5626010	EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117LF	52 			0107	7013				DIMMER BUZZES WHEN THE LIGHTS ARE TURNED ON.						1	G	7	2 	3U				H13EU 					 
1995122900326	19951229	00326	EU 	1995	12	29	95ZZZX6966 	1	19951013	G	7110	742Z0	GOOSENECK 			BOLKMS	105 	BO105S 	5626006	EU 										COWL	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105NG	201 				S632				GOOSENECK WORN AND LOOSE. WILL NOT KEEP POSITION FOR FLIGHT.						1	G	7	2 	3U				H3EU 					 
1995122900327	19951229	00327		1995	12	29	95ZZZX6967 	4	19951104	G	3453	4530103	LORAN 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	224LF	29 			29481	45199				LORAN HAS WEAK RECEPTION. STILL HAVING PROBLEMS WITH THIS UNIT. THE LAST TIME IT WAS IN, IT WOULD NOT POWER-UP AND NOW	, WEAK RECEPTION. PLEASE CHECK OUT.					1	G	7	1 	3U				H2SW 					 
1995122900328	19951229	00328		1995	12	29	95ZZZX6968 	4	19951031	G	2312	4000103000	TRANSMITTER 		RT450 	AEROSP	SA365 	SA365N1 	8680668	EU 										COCKPIT	FAULTY 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	365SC	8 			795	6298				WHEN TRANSMITTING, GOES TO TRANSMIT FOR ABOUT 2 SECONDS, THEN, SWITCHES BACK TO NO TRANSMIT.						1	G	7	2 	3U				H10EU 					 
1995122900329	19951229	00329	EU 	1995	12	29	95ZZZX6969 	1	19951023	G	7714	117902111	INDICATOR 			BOLKMS	BK117 	BK117C1 	5626025	EU 										TRIPLE TACH	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	275 			704	7505				TRIPLE TACHOMETER NEEDLES SPLIT. NR 2 ENGINE NEEDLE FLUTTERS IN FLIGHT. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1995122900331	19951229	00331	GL 	1995	12	29	95ZZZX6971 	2	19950512	G	7250	6898764	SEAL 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					OIL BELLOWS	LEAKING 	B			R7MA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	301LG	480 				5065	CAT24238			OIL BELLOWS SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995122900332	19951229	00332	GL 	1995	12	29	95ZZZX6972 	2	19950512	G	7250	6898764	SEAL 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					OIL BELLOWS	LEAKING 	B			R7MA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	301LG	355 				5065	CAE40356			OIL BELLOWS SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995122900333	19951229	00333	GL 	1995	12	29	95ZZZX6973 	2	19950801	G	7250	A6871505	BEARING 	SUPAIRPART 		BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					NR 5 MAIN	MAKING METAL 	B			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	105NC	96 			104	790	CAT37299			C/W SUPERIOR AIR PARTS SB T95-SB001. FOUND 13 METAL FLAKES IN FACET FILTER BOWL. TURBINE ASSY CAT37299. REPLACED WITH	 ALLISON MANUFACTURED BEARING.					1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995122900335	19951229	00335	EU 	1995	12	29	95ZZZX6975 	1	19950906	G	7712	10590952	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT TORQUE	FAULTY 	B			JSNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	204PC	429 				S895				NR 2 ENGINE FAILED POWER ASSURANCE CHECK WHEN PERFORMED IAW ACFT FLIGHT MANUAL. ENGINE CHECKED FOR BLEED AIR LEAKS AND 	BLEED VALVE WAS SWAPPED. BURNER CAN, NR 1 NOZZLE, AND WHEEL WERE VISUALLY INSPECTED WITH A BORESCOPE. FOUND OK. TORQU	E GAUGE CHECKED AND FOUND TO BE OUT OF TOLERANCE (MINUS 5 PERCENT) WITH INFO PROVIDED BY A.E.C., THIS INFORMATION IS NOT	 FOUND IN MM. COMPRESSOR WAS WASHED. SUBSEQUENT POWER CHECK SHOWED REASONABLE POWER MARGIN FOR ENGINE TIME WHEN TAKING	 TORQUE GAUGE OUT OF TOLERANCE FACTOR IN CONSIDERATION. SUBMITTER STATES THESE GAUGES CANNOT BE FIELD CALIBRATED. EURO	COPTER SHOULD PUBLISH THE DEADWEIGHT TEST CHECK IN THE MAINTENANCE MANUAL.	1	G	7	2 	3U				H3EU 					 
1995122900360	19951229	00360	EU 	1995	12	29	95ZZZX7002 	1	19950822	G	7714	1179405303	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										NR 2 ENG N2	INOP 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	460H	214 			460	7142				NR 2 N2 NEEDLE WILL NOT MOVE WITH ENGINE RUNNING.						1	G	7	2 	3U				H13EU 					 
1995122900361	19951229	00361		1995	12	29	95ZZZX7003 	4	19950827	G	3421	071105304	GYRO 		KA51A 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	495LF	15 			18275	S645				GYRO READING INCORRECTLY STAYING FAR LEFT TO THE SIDE.						1	G	7	2 	3U				H3EU 					 
1995122900362	19951229	00362		1995	12	29	95ZZZX7004 	4	19951002	G	2312	4000103002	TRANSCEIVER 		RT450 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	INOP 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	495LF				442	S645				TRANSCEIVER STILL INOP (WILL NOT TRANSMIT ON CHANNEL 'A').						1	G	7	2 	3U				H3EU 					 
1995122900363	19951229	00363	EU 	1995	12	29	95ZZZX7005 	1	19950101	G	2620	18602	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FIRE EXT SYS	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	118LL					7097				INDICATOR CRACKED AND DETERIORATED. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995122900267	19951229	00267		1995	12	29	95ZZZX7007 	2	19951128	G	7322	8211	COTTER PIN 	FACET 	MA45 															FLOATSHAFT	MISSING 	B			NE2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	07										RECEIVED CARBURETOR FROM CUSTOMER WITH THE FOLLOWING SQUAWK: AIRCRAFT WILL NOT IDLE, CANNOT SHUT DOWN WITH FUEL MIXTURE	. SEEMS TO RUN AT HIGH RPM. WHEN SHUT OFF WITH SWITCH, FUEL RUNS OUT OF CARBURETOR. 6.0 HOURS SINCE INSTALLED ON AIRC	RAFT. TESTED CARBURETOR FOR FLOAT VALVE LEAKAGE, CARBURETOR OVERFLOWED. DISASSEMBLY REVEALED COTTER PIN MISSING FROM F	LOATSHAFT, ALLOWING SHAFT TO SLIDE OUT OF BRACKET.																 
1995122900268	19951229	00268	EA 	1995	12	29	95ZZZX7008 	2	19951201	G	8530	7380685	PUSH ROD 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2C 	41505	EA 					ENGINE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	01	6379M		1100 			15284701	L1703215			FOUND BALL END IN PUSH ROD LOOSE AND PUSH ROD TUBE CRACKED ABOUT .75 INCH ON SAME END.						1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1995122900269	19951229	00269	SO 	1995	12	29	95ZZZX7009 	1	19951020	G	7160		AIR BOX 			MAULE 	M5 	M5180C 	5460204	SO 										INDUCTION AIR	SPLIT 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	5640S	65 				8009C				INDUCTION AIR BOX SPLIT ALONG WELD ON LEFT SIDE OF CARBURETOR MOUNT FLANGE. SUBMITTER STATED INDUCTION AIR BOX NEEDS TO	 BE REDESIGNED AND INDUCTION AIR HOSE NEEDS SUPPORTS OR CLAMPS INSTALLED TO PREVENT ALL WEIGHT FROM BEING CARRIED BY AIR	 BOX. AIR BOX WAS REPLACED DURING LAST ANNUAL FOR SAME DEFECT.				1	H	7	1 	3O				3A23 					 
1995122900270	19951229	00270	CE 	1995	12	29	95ZZZX7010 	1	19951204	G	5620	71256	WINDOW 			BBAVIA	8 	8KCAB 	2110612	CE 										RT AFT	DEPARTED 	B		A	OG5R	O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			GL	21	68ND	1622 				66892				RIGHT REAR WINDOW DEPARTED AIRCRAFT DURING FLIGHT. LEADING EDGE OF WINDOW IS HELD DOWN BY A METAL STRIP WITH 3 SCREWS. 	 WINDOW AND NEW SEAL INSTALLED. OPERATOR SUGGESTS USE OF SEALANT BETWEEN FRAME AND WINDOW ON LEADING EDGE WILL PREVENT 	AIRFLOW FROM PEELING WINDOW OUT IF SCREWS COME LOOSE. LEFT WINDOW SHOWED SAME SIGNS AND WAS ALSO REPAIRED/REPLACED BEFO	RE FLIGHT.			1	H	7	1 	3O				A21CE 					 
1995122900271	19951229	00271	CE 	1995	12	29	95ZZZX7011 	1	19951202	G	3250	S18233	ROD END 			CESSNA	172 	172 	2072402	CE 										STRUT	BROKE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	3000U	4000 				17250600				HEIM JOINT ON STEERING PART OF STRUT BROKE. SUBMITTER STATED FOUND SEVERAL BENT, AND SOME CRACKED, SUSPECT CAUSE IS EXC	EEDING THE TURN LIMIT OF THE STRUT WITH A TOW BAR AND ALSO A TOW VEHICLE. SUBMITTER RECOMMENDS MANDATORY INSPECTIONS ON	 THIS PARTICULAR AIRCRAFT. IT BROKE WHEN TAXIING, CAUSED LOSS OF STEERING CONTROL, AND AIRCRAFT WAS NOT DAMAGED, BUT IF	 IT WERE TO HAPPEN ON LANDING, IT COULD HAVE CAUSED SEVERE DAMAGE.			1	H	7	1 	3O			NT	3A12 					 
1995122900272	19951229	00272	SW 	1995	12	29	95ZZZX7012 	1	19951101	G	2710		CONTROL CABLE 			TMPSON	NAVION	NAVION* 	6150130	SW 										AILERON	CORRODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16										SUBMITTER FOUND THE AILERON CABLE, JUST OUTBOARD OF THE WHEELWELLS, ALMOST RUSTED COMPLETELY THROUGH ON SEVERAL AIRPLANE	S. ONE HAD ONLY TWO STRANDS HOLDING. SUBMITTER STATED THE ONLY WAY TO INSPECT THESE CABLES IS TO DISCONNECT THEM AT TH	E AILERON BELLCRANK AND PULL THEM IN THE WHEELWELL.				1	L	7	1 	3O			 	A782 					 
1995122900274	19951229	00274	CE 	1995	12	29	95ZZZX7014 	1	19951202	G	3250	S18233	ROD END 			CESSNA	172 	172 	2072402	CE 										STRUT	BROKE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	4192F	4000 				46092				HEIM JOINT ON STEERING PART BROKE OFF STRUT. HAVE FOUND SEVERAL BENT ON 172'S, AND HAVE FOUND CRACKS. SUSPECT CAUSE IS	 EXCEEDING THE TURN LIMIT WITH A TOW BAR OR TOW VEHICLE. RECOMMEND MANDATORY INSPECTIONS.					1	H	7	1 	3O			NT	3A12 					 
1995122900275	19951229	00275	CE 	1995	12	29	95ZZZX7015 	1	19951124	G	2430	6041H193	RELAY 			CESSNA	421 	421B 	2076014	CE 										DC POWER	STUCK 	D				K				NONE 				M	H		OVER TEMP 	ELECT. POWER LOSS-50 PC 		IN	INSP/MAINT 	1			GL	21	421NP					421B0418				CONTACT STUCK IN CLOSED POSITION AFTER ENGINE STARTED CAUSING STARTER TO OVERHEAT AND SHORT OUT. SHORT CAUSED BATTERY T	ERMINAL TO MELT OFF. TOTAL ELECTRICAL FAILURE FOLLOWED.					1	L	7	2 	3O				A7CE 					 
1995122900276	19951229	00276	EA 	1995	12	29	95ZZZX7016 	2	19951121	G	8530		VALVE 			PIPER 	PA28 	PA28181 	7102807	SO 	LYC 	O360 	O360A4M 	41514	EA 					NR 3 CYL EXH	SEPARATED 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			NM	09	47451	2405 				287890076	L2369036A			NR 3 CYLINDER EXHAUST VALVE SEPARATED THE STEM FROM THE HEAD. AIRCRAFT WAS FORCED TO LAND. ENGINE HAD GOOD HISTORY OF 	MAINTENANCE. THE ENGINE WAS NEW IN 1977. SUBMITTER SUGGESTS THE INDUSTRY SHOULD BE REQUIRED TO REMOVE THE EXHAUST SYST	EM AND INSPECT VALVES FOR CORROSION IN A CALENDER TIME FRAME.				1	L	7	1 	3O	3	O		2A13 	E286				 
1995122900277	19951229	00277	CE 	1995	12	29	95ZZZX7017 	1	19951214	G	3340	1520024	POWER SUPPLY 			CESSNA	208 	208B 	2073701	CE 										LT STROBE	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	1040W	1780 				208B0336				PILOT REPORTED NON-FUNCTIONING LEFT WING STROBE. INVESTIGATION FOUND BURNED FLASH TUBE. TUBE RELACED WITH NEW, UNIT ST	ILL WOULD NOT OPERATE. POWER SUPPLY WAS REMOVED FROM WING, CONNECTORS AND WIRING INSPECTED FOR SECURITY AND CONDITION. 	 ALL SATISFACTORY. POWER SUPPLY WAS REINSTALLED, AND FUNCTION CHECK FAILED AGAIN. POWER SUPPLY REPLACED WITH REMANUFAC	TURED UNIT. ALL CHECKS OK.			1	H	7	1 	3T				A37CE 					 
1995122900280	19951229	00280	CE 	1995	12	29	95ZZZX7020 	1	19951129	G	2913	9881128	MOTOR 		98811241 	CESSNA	172 	172RG 	2072438	CE 										POWER PACK	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	4809V	2003 			2967	172RG0385				DURING A ROUTINE ANNUAL INSPECTION, THE MLG HYD POWER PACK MOTOR WOULD NOT SHUT OFF AT THE END OF THE RETRACT OR EXTEND 	CYCLE WHILE ON JACKS USING ONLY SHIPS ELECTRICAL POWER (24V). THE MLG CYCLED PROPERLY DURING FLIGHT AND PILOT NOTICED N	O DISCREPANCIES BEFORE THE INSPECTION. T/S REVEALED MLG SYSTEM FUNCTIONED PROPERLY WHEN AT 26V WERE APPLIED TO ACFT. N	OTE: ACFT SYS IN-FLIGHT VOLTAGE IS 28V. MLG HYD POWER PACK REMOVED FROM ACFT AND SENT OUT FOR O/H. O/H SHOP CONFIRMED	 MOTOR AND PUMP COULD NOT FUNCTION PROPERLY, NOT ABLE TO BUILD UP PRESSURE. SUBMITTER SUGGESTS SIMULATING ALTERNATOR 'O	UT' DURING ANNUAL TO SEE IF ACFT SYSTEMS WORK PROPERLY.	1	H	7	1 	3O				3A17 					 
1995122900281	19951229	00281	CE 	1995	12	29	95ZZZX7021 	1	19951115	G	3240	99141362	BRAKE ASSY 	BFGOODRICH 	244537 	CESSNA	650 	650 	2076802	CE 										RT INBD NR 3	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	40N		533 		0128	6507031				AIRCRAFT TT 738.7 HRS. DURING NR 3 RIGHT INBOARD TIRE CHANGE, FOUND INBOARD, FIRST CARRIER AND LINING ASSYS BROKEN IN 2	 PIECES. BRAKE ASSY PN 21502 BF GOODRICH CESSNA PN 9914136-1. MANUAL NR 32-46-41, PAGE 1006, ITEM NR 90. APR 28/89 DA	TED. DEFECTED PART CARRIER AND LINING PN 244-537.				2	L	7	2 	4F				A9NM 					 
1995122900282	19951229	00282	CE 	1995	12	29	95ZZZX7022 	1	19951127	G	2150	206SZZC	BEARING 		115555024 	BEECH 	300 	300BEECH 	1152930	CE 										AIR COND PULLEY	FAILED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	194LJ	4791 				FA89				DURING ROUTINE LUBRICATION SCHEDULE OF 600 HRS, REMOVED AIR CONDITIONER QUILL SHAFT PULLEY AND HAD BALL BEARING FALL OUT	. FOUND BEARING HAD COME APART. BALLS HAD FLAT SPOTS. QUILL SHAFT WAS ALSO KNIFE EDGED AS WELL AS THE PULLEY. THIS C	ONDITION DID NOT EXIST LAST TIME LUBED. SUBMITTER STATED HAVE NO SUGGESTIONS AS TO CAUSE OR PREVENTION.				2	L	7	2 	4T				A24CE 					 
1995122900283	19951229	00283	CE 	1995	12	29	95ZZZX7023 	1	19951120	G	3231	035A38864	SAFETY PIN 		030A38423 	MTSBSI	MU2 	MU2B60 	5780460	CE 										MLG DOOR	SHEARED 	D		A		O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			SW	99	100BY					1565SA				LANDING GEAR WOULD NOT EXTEND NORMALLY. LDG GEAR WAS EXTENDED MANUALLY USING EMERGENCY GEAR HANDLE AND GEAR WAS SECURED	 DOWN AND LOCKED. MAINTENANCE JACKED ACFT AND DISCOVERED SHEARED SAFETY PIN FOR FORWARD MAIN GEAR DOORS. NOTE: SHEAR 	PIN IS DESIGNED TO SHEAR IF FORWARD GEAR DOORS ARE UNLATCHED OUT OF SEQUENCE TO PREVENT DOOR DAMAGE. SAFETY (SHEAR PIN)	 SHOWED SIGNS OF WEAR WHICH MAINTENANCE ATTRIBUTED TO FAILURE. SHEAR PIN REPLACED. LDG GEAR OPERATION CHK PERFORMED NO	RMALLY. DOOR'S OPENING SEQUENCE VERIFIED AS NORMAL. AIRCRAFT WAS RETURNED TO SERVICE.		1	H	7	2 	3T			RT	A10SW 					 
1995122900284	19951229	00284	CE 	1995	12	29	95ZZZX7024 	1	19951121	G	2510		ARM 			CESSNA	425 	425 	2076018	CE 										PILOT SEAT	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	77YP	3413 				4250111				PILOT SEAT BACK FELL BACK AFTER SUPPORT ARM BROKE, WHILE PILOT WAS DEPARTING AIRCRAFT. SUSPECT CAUSE IS METAL FATIGUE.						1	L	7	2 	3T			RT	A7CE 					 
1995122900285	19951229	00285	WP 	1995	12	29	95ZZZX7025 	2	19950310	G	7200		ENGINE 			MTSBSI	MU2 	MU2B60 	5780460	CE 	GARRTT	TPE331	TPE33110 	01514	WP 					LT ENGINE	DAMAGED 	D				E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			CR	CRUISE 	1			NM	11	479MA	5697 	1883 			1553SA	P36379			AIRCRAFT LEVEL FLIGHT 17,000 FEET NORMAL TORQUE FOR BOTH ENGINES. TEMPS NORMAL, FUEL FLOW NORMAL. LEFT ENGINE WENT TO 	ZERO TORQUE, FLUCTUATED SOME. EGT REMAINED BELOW RED LINE, FUEL FLOW WAS STILL NORMAL. OIL PRESSURE NORMAL. PILOT USE	D EMERGENCY CUT-OFF, FEATHERED PROP. ENGINE CAME TO A QUICKER THAN NORMAL STOP. AIRCRAFT LANDED AT SLC WITH NO PROBLEM	. EXTREME HOT SECTION DAMAGE FROM EXTERNAL VIEW. NOT DISASSEMBLED AT THIS TIME.			1	H	7	2 	3T	4	T	RT	A10SW 	E4WE				 
1995122900286	19951229	00286	CE 	1995	12	29	95ZZZX7026 	1	19951129	G	7820		MUFFLER 			BEECH 	33 	3533 	1151402	CE 										FLAME CONE	FAILED 	D	L			A				UNSCHED LANDING 				E	R	W	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	INADEQUATE Q C 	CR	CRUISE 	1			NE	05	9046S					CD133				PILOT REPORTED SUDDEN ENGINE ROUGHNESS AND POWER LOSS. UNABLE TO MAINTAIN ALTITUDE, AN UNEVENTFUL ON-AIRPORT LANDING WA	S MADE. INSPECTION REVEALED HEATER/MUFFLER HAD BEEN REPAIRED, BUT INSTEAD OF A 'FLAME CONE' BEING WELDED IN, A FLAME TU	BE WITH SOLID END PLATE HAD BEEN INSTALLED. THIS TUBE HAD BROKEN FREE, AND UPON SLIDING AFT, THE SOLID END PLATE BLOCKE	D OFF THE MUFFLER OUTLET.			1	L	7	1 	3O				3A15 					 
1995122900287	19951229	00287	SO 	1995	12	29	95ZZZX7027 	1	19951101	G	5551	2116100	BRACKET 			PIPER 	PA18 	PA18150 	7101828	SO 										HORZ STAB ATTACH	CRACKED 	H	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	4375Z	6071 				188697				BRACKET IS THE HORIZONTAL STABILIZER REAR ATTACH POINT. IT IS WELDED TO THE FUSELAGE TOP'S TWO TUBES. THE RIGHT SIDE B	RACKET FLANGE IS CRACKED IN 3 PLACES AROUND WHERE THE STABILIZER CARRY-THROUGH TUBE ATTACHES TO THE FLANGE. AT THE POIN	T WHERE THE LEFT SIDE FLANGE OF THE BRACKET IS WELDED TO FUSELAGE, THE FUSELAGE TUBE IS CRACKED 75 PERCENT OF THE WAY AR	OUND ITS CIRCUMFERENCE.			1	H	7	1 	3O				1A2 					 
1995122900288	19951229	00288	SO 	1995	12	29	95ZZZX7028 	1	19951024	G	2750	95504000	BRACKET 			PIPER 	PA34 	PA34200T 	7103406	SO 										FLAP HANDLE	CRACKED 	B		A	APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	8407C	14839				347670137				FLAP HANDLE BRACKET IS CRACKED AT BOTH LOWER FORWARD BEND RADIUS NEXT TO ATTACH POINTS TO AIRFRAME. SECOND UNIT IN FLEE	T IN SAME CONDITION.					1	L	7	2 	3O				A7SO 					 
1995122900289	19951229	00289	EU 	1995	12	29	95ZZZX7029 	1	19951130	G	7920	T67C50807	HOSE 			SLNSBY	T67 	T67M260 	8323006	EU 										OIL COOLER	DETACHED 	D		A		A				UNSCHED LANDING 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			SW	17	31880	104 				2206				PARTIAL ENGINE FAILURE, RPM DROPPED FROM 2700 RPM TO 2100 RPM AND BACK TO 27 RPM FOLLOWED BY LOSS OF OIL PRESSURE. ENGI	NE RAN FOR APPROXIMATELY 4 TO 5 MINUTES WITH VIBRATIONS AND DETERIORATING POWER LOSS FOLLOWED BY TOTAL POWER LOSS. ACFT	 LANDED SAFELY. INSPECTION FOUND LOWER OIL COOLER HOSE BROKE LOOSE AND ENGINE'S OIL LEAKED OUT WHICH CAUSED MAJOR ENGIN	E DAMAGE. FIFTY-ONE OTHER ACFT WERE INSPECTED WITH NO DEFECTS NOTED.			1	L	7	1 	3O			NT	A73EU 					 
1995122900290	19951229	00290	SO 	1995	12	29	95ZZZX7030 	1	19951103	G	5551		SPAR TUBE 			PIPER 	PA25 	PA25260 	7102508	SO 										H STAB LT SIDE	CRACKED 	H	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	9878P	4592 				257556217				THE FUSELAGE REAR SPAR TUBE FOR THE HORIZONTAL STABILIZER WAS FOUND CRACKED THREE-FOURTHS THROUGH ON LT SIDE AND ONE-HAL	F THROUGH ON RT SIDE. THIS DEFECT WAS FOUND ON 2 ACFT IN A FLEET OF 3. THIS DEFECT APPEARS TO HAVE OCCURRED FROM HEAVY	 DOWNLOADS ON HORIZ STAB. SUBMITTER STATED COULD NOT DETECT THIS BY THE NORMAL INSPECTION PROCESS, HAVE TO PULL THE HOR	IZ STAB AND PULL THE FABRIC BACK TO SEE IT.			1	L	7	1 	3O				2A10 					 
1995122900292	19951229	00292	SO 	1995	12	29	95ZZZX7032 	1	19951106	G	2434	ALU8421LS	ALTERNATOR 	PRESTOLITE 		PIPER 	PA31 	PA31350 	7103110	SO 										DC SYSTEM	SEIZED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	627HA				3070737	317952241				WHEN REPLACING THROWN ALTERNATOR DRIVE BELT, MECHANICS NOTICED ALTERNATOR DAMAGE DUE TO FAILED BEARINGS, ROTOR CONTACTS,	 STATOR FRAME, AND BINDS.					1	L	7	2 	3O				A20SO 					 
1995122900293	19951229	00293	CE 	1995	12	29	95ZZZX7033 	1	19951124	G	2810	S149563	LINE 			CESSNA	150 	152 	2071835	CE 										FUEL VENT	DETERIORATED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	21	4847B	5500 	1979 			15283670				WHILE REPAIRING FUEL LEAK ON RT FUEL TANK INTERCONNECT HOSE WHICH WAS INCORRECTLY INSTALLED AND LEAKING, IT WAS NOTICED 	THAT THE LT HOSE WAS ORIGINAL EQUIPMENT, SEVERELY AGED, AND READY TO FAIL. RECOMMENDATION: ALL FLEX FUEL LINES BE REPL	ACED AT MINIMUM OF 20-YEAR PERIODS.				1	H	7	1 	3O			NT	3A19 					 
1995122900294	19951229	00294		1995	12	29	95ZZZX7034 	1	19951030	G	3060	RA2111V	BRUSH BLOCK 																	PROPELLER DEICE	MISMANUFACTURED 	B			APCR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	01										RAPCO MANUFACTURES 'CLONES' OF B. F. GOODRICH DEICER PRODUCTS. RAPCO MODULAR BRUSH ASSY IS MADE IMPROPERLY. THIS UNIT 	IS A COPY OF B.F.G., PN 3E2011. B.F.G. SPECIFIES A CARBON BRUSH WITH INTEGRAL LOCATING PIN FOR THIS APPLICATION. RAPCO	 USES 'NON-PINNED' BRUSHES WHICH COCK SIDEWAYS AND CAUSE EXTRA WEAR ON BRUSH BLOCK/HOLDER.																	 
1995122900295	19951229	00295	SO 	1995	12	29	95ZZZX7035 	1	19951009	G	2750	9550400	BRACKET 			PIPER 	PA34 	PA34200T 	7103406	SO 										FLAP HANDLE	CRACKED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	5384F	10300				347770013				DURING INSPECTION, THE FLAP HANDLE BRACKET WAS FOUND CRACKED IN 2 PLACES ALONG GUIDE PIN TRACKS AT THE 10 DEGREE FLAP NO	TCH AND AT THE 25 DEGREE FLAP NOTCH. BOTH CRACKS RADIATE FROM THE NOTCHES FORWARD TOWARD THE FORWARD EDGE OF THE BRACKE	T. THERE IS ALSO 1 CRACK AT THE BASE OF THE BRACKET ON THE RT SIDE FORWARD CORNER RADIUS.				1	L	7	2 	3O				A7SO 					 
1995122900296	19951229	00296	SW 	1995	12	29	95ZZZX7036 	1	19951102	G	3240		BRAKE 	GOODYEARAERO		GULSTM	560 	560 	0141402	SW 										MLG	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										AIRCRAFT HAD BEEN TO NUMEROUS SHOPS WITH WEAK OR NO BRAKES (THE BRAKES WOULD NOT HOLD THE AIRCRAFT STILL WITH MORE THAN 	1700 RPM). MAINTENANCE MANUAL SAYS THAT ALL THICK PADS MAY BE NEEDED OR IT MAY NEED THIN PADS ON ANVIL SIDE AND THICK P	ADS ON PISTON SIDE. THIS ONE NEEDED ALL THICK PADS. SUBMITTER STATED COMPOUNDING THIS PROBLEM IS A LACK OF INFORMATION	 IN THE PARTS MANUAL AND BOGUS PARTS.			1	H	7	2 	3O				6A1 					 
1996010500002	19960105	00002	NE 	1996	1	5	95ZZZX7037 	2	19951122	G	7250	414129001	PT ROTOR 			BELL 	222 	222B 	1182124	SW 	LYC 	LTS101	LTS101750C1 	41560	NE 					TURBINE	BLADE SHIFT 	H		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	911RA	1360 	47 			47150	LE47228			THIS PART WAS INSPECTED EARLY AT CONVENIENCE OF OPERATOR, TO MAINTAIN ACFT AVAILABILITY. DURING C/W ALLIED SIGNAL AEROS	PACE (FORMERLY TEXTRON LYCOMING) SB LT-101-72-50-0153 AND BELL ASB 222-93-63, USING DIAL INDICATOR INSPECTION METHOD TO 	DETECT BLADE SHIFT, FOUND ONE BLADE SHIFTED .014 INCH (MAX IS .010 INCH FOR ANY ONE BLADE). THE PT ROTOR HAD A TOTAL OF	 46.9 HRS/192 CYCLES SINCE INSTALLATION. PER ALLIED SIGNAL, BLADE SHIFT IS CAUSED BY BLADE ATTACH RIVET WORKING LOOSE. 	 SUBMITTER STATED MANUFACTURER NEEDS TO COME UP WITH A PERMANENT FIX TO THE PROBLEM. CYCLES, 192.		1	G	7	2 	3U	3	U		H9SW 	E5NE				 
1996010500004	19960105	00004	SW 	1996	1	5	95ZZZX7039 	1	19951115	G	5320		AIRFRAME 			KAMAN 	K1200 	K1200 	05625F6	SW 										LT XMSN MT PAD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	133KA	1707 				940005				HELICOPTER USED IN LOGGING OPERATION. DURING DAILY INSPECTION, SHEET METAL CRACK ABOUT 3 INCHES IN LENGTH WAS DISCOVERE	D ON THE STRUCTURAL SUPPORT FOR THE LEFT FORWARD TRANSMISSION MOUNT PAD. THE CRACK IS RADIATING OUTWARD FROM A RIVET. S	USPECT CAUSE, IMPROPER RIVETING PRACTICE. KNOWLEDGE AND USE OF RIVET METHOD AND TECHNIQUE WOULD PREVENT RECURRENCE.				1	G	7	1 	4F			NT	TR7BO 					 
1996010500005	19960105	00005	SW 	1996	1	5	95ZZZX7040 	1	19951011	G	6730	206706031107	SERVO 			BELL 	206 	206B 	1181511	SW 										CONTROL	DEFECTIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	221GP	466 			HR7184	4309				SERVO DEFECTIVE. CATCHING WHEN LEVER IS LIFTED. REPLACED WITH NEW SERVO.						1	G	7	1 	3U				H2SW 					 
1996010500006	19960105	00006	SW 	1996	1	5	95ZZZX7041 	1	19951115	G	2841	206075740113	INDICATOR 			BELL 	206 	206B3 	1181506	SW 										FUEL QUANTITY	DEFECTIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	403H	16 			95040019A	4348				FUEL QUANTITY INDICATOR DEFECTIVE. REPLACED WITH NEW FUEL QUANTITY INDICATOR.						1	G	7	1 	3U				H2SW 					 
1996010500007	19960105	00007	GL 	1996	1	5	95ZZZX7042 	2	19951031	G	7314	2C271	PUMP 			BELL 	206 	206L4 	1182110	SW 	ALLSN 	250C 	250C30P 	03013	GL 					ENGINE	INOPERATIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	64050	9 			1AC22	52145				FUEL PUMP INOP. REPLACED WITH NEW FUEL PUMP.						1	G	7	1 	3U	3	U	NC	H2SW 	E1GL				 
1996010500008	19960105	00008	SW 	1996	1	5	95ZZZX7043 	1	19951025	G	6730	206076062101	SERVO 			BELL 	206 	206L4 	1182110	SW 										CONTROLS	LEAKING 	B			GS1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	03	64070	10 			RH835A	52144				SERVOS LEAKING. REPLACED WITH NEW CYLINDERS.						1	G	7	1 	3U			NC	H2SW 					 
1996010500009	19960105	00009	SW 	1996	1	5	95ZZZX7044 	1	19951025	G	6730	206076062101	SERVO 			BELL 	206 	206L4 	1182110	SW 										CONTROLS	LEAKING 	B			GS1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	03	64070	10 			RH4715A	52144				SERVOS LEAKING. REPLACED WITH NEW CYLINDERS.						1	G	7	1 	3U			NC	H2SW 					 
1996010500010	19960105	00010	SW 	1996	1	5	95ZZZX7045 	1	19951025	G	6730	206076062101	SERVO 			BELL 	206 	206L4 	1182110	SW 										CONTROLS	LEAKING 	B			GS1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	03	64070	10 			RH4664A	52144				SERVOS LEAKING. REPLACED WITH NEW CYLINDERS.						1	G	7	1 	3U			NC	H2SW 					 
1996010500011	19960105	00011	SW 	1996	1	5	95ZZZX7046 	1	19951115	G	6310	214040659005	COUPLING 			BELL 	412 	412 	1182202	SW 										DRIVE	PITTED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	3292X	17 			A962	36111				DRIVE COUPLINGS PITTED. REPLACED WITH NEW COUPLING.						1	G	7	2 	4U				H4SW 					 
1996010500012	19960105	00012	SW 	1996	1	5	95ZZZX7047 	1	19951115	G	6310	214040659005	COUPLING 			BELL 	412 	412 	1182202	SW 										DRIVE	PITTED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	3292X	17 			A955	36111				DRIVE COUPLINGS PITTED. REPLACED WITH NEW COUPLING.						1	G	7	2 	4U				H4SW 					 
1996010500013	19960105	00013		1996	1	5	95ZZZX7048 	4	19951115	G	3414	412075009105	INDICATOR 			BELL 	412 	412 	1182202	SW 										AIR SPEED	DEFECTIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	3292R	22 			261281	36110				COCKPIT AIR SPEED INDICATOR DEFECTIVE. REPLACED WITH NEW INDICATOR.						1	G	7	2 	4U				H4SW 					 
1996010500014	19960105	00014	SW 	1996	1	5	95ZZZX7049 	1	19951115	G	2430	1101461	RELAY 			BELL 	412 	412 	1182202	SW 										GENERATOR	INOPERATIVE 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	3292X	17 				36111				GENERATOR RELAY INOP. REPLACED WITH NEW RELAY.						1	G	7	2 	4U				H4SW 					 
1996010500015	19960105	00015	SW 	1996	1	5	95ZZZX7050 	1	19951115	G	6310	214040657003	COUPLING 			BELL 	412 	412 	1182202	SW 										DRIVE	PITTED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	2FOR	17 			A678	36111				DRIVE COUPLING PITTED. REPLACED WITH NEW COUPLINGS.						1	G	7	2 	4U				H4SW 					 
1996010500016	19960105	00016	SW 	1996	1	5	95ZZZX7051 	1	19951115	G	6310	214040657003	COUPLING 			BELL 	412 	412 	1182202	SW 										DRIVE	PITTED 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	2FOR	17 			A679	36111				DRIVE COUPLING PITTED. REPLACED WITH NEW COUPLINGS.						1	G	7	2 	4U				H4SW 					 
1996010500017	19960105	00017	SW 	1996	1	5	95ZZZX7052 	1	19951011	G	6700	412062728101	BELLCRANK 			BELL 	412 	412 	1182202	SW 										CONTROL	MISINSTALLED 	B			GS1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	03	2FOR	31 				36107				BELLCRANK IMPROPERLY INSTALLED. REPLACED WTIH NEW BELLCRANK.						1	G	7	2 	4U				H4SW 					 
1996010500018	19960105	00018	SW 	1996	1	5	95ZZZX7053 	1	19951011	G	7714	GEU7A	GENERATOR 			BELL 	412 	412 	1182202	SW 										ENG TACHOMETER	ERRATIC 	B			GS1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	32929	16 			250113	36113				TACHOMETER GENERATOR ERRATIC. REPLACED WITH NEW GENERATOR.						1	G	7	2 	4U				H4SW 					 
1996010500020	19960105	00020	SW 	1996	1	5	95ZZZX7055 	1	19951026	G	6720	206010793101	PITCH LINK 		206011720017	BELL 	206 	206B 	1181511	SW 										T/R	CRACKED 	E	P			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	01	333PJ	1445 				2785				FOUND CRACK ON OUTBOARD PITCH CHANGE LINK NEXT TO BEARING. SUBMITTER STATED PART WAS NEW FROM BELL, PROBLEM MAY BE FROM	 OVERSTAKING OF BEARING AT ASSEMBLY.					1	G	7	1 	3U				H2SW 					 
1996010500022	19960105	00022	EU 	1996	1	5	95ZZZX7057 	1	19951129	G	7600	355A57248921	BALL END 			AEROSP	AS355 	AS355F1 	8680810	EU 										ANTICIPATE RELAY	MISINSTALLED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	07	5779U	3141 				5059				DURING IN-FLIGHT ENGINE TREND CHECK OF ACFT ENGINES, PILOTS DISCOVERED REVERSE OPERATION OF THE NR 2 ENGINE TRIM OR ANTI	CIPATOR CONTROL AT MID-POINT OF ACTUATION. AFTER RIGGING ACFT PER N.W.C., AND THOROUGH TROUBLESHOOTING, DETERMINED THE 	ECCENTRIC BALL END LOCATED AT THE LOWER OFFSET OF THE ANTICIPATOR RELAY ASSY WAS NOT POSITIONED CORRECTLY, WAS 90 DEGREE	S OFF. THE ERROR WAS DONE AT AN EARLIER DATE.			1	G	7	2 	3U				H11EU 					 
1996010500023	19960105	00023	EU 	1996	1	5	95ZZZX7058 	1	19950301	G	6120		CABLE 			SOCATA	TBM 	TBM700 	8682000	EU 										PROPELLER GOV	CHAFED 	B		A	MZER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	300WC	1500 				82				DURING 100-HOUR INSPECTION, FOUND PROPELLER GOVERNOR CABLE CHAFING ON THE C-FLANGE OF THE POWER PLANT. SUBMITTER RECOMM	ENDS PUTTING BRACKET WITH CLAMP ON C-FLANGE TO LIFT PROP GOVERNOR CABLE AWAY FROM FLANGE TO PREVENT CHAFING. RE: MANUA	L, CHAPTER 76, SUB-CHAPTER 10, ITEM NR T700A7610049000.				1	L	7	1 	3T			RT	A60EU 					 
1996010500024	19960105	00024	EU 	1996	1	5	95ZZZX7059 	1	19951102	G	6120		CABLE 			SOCATA	TBM 	TBM700 	8682000	EU 										PROPELLER GOV	CHAFED 	B			MZER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	300AE	399 				97				DURING 100-HOUR INSPECTION, FOUND PROPELLER GOVERNOR CABLE CHAFES ON C-FLANGE OF POWER PLANT. SUBMITTER RECOMMENDS PUTT	ING BRACKET WITH CLAMP TO KEEP FROM CHAFING. RE: MANUAL, CHAPTER 76, SUB-CHAPTER 10, ITEM NR T700A7610049000.					1	L	7	1 	3T			RT	A60EU 					 
1996010500025	19960105	00025	NE 	1996	1	5	95ZZZX7060 	2	19951207	G	7250	797957	SEAL RING 								PWA 	JT9 	JT9D7 	52054	NE 					NR 3 BEARING	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99			1171 				662836			DURING TEAR DOWN OF ENGINE TO INVESTIGATE THE CAUSE OF HIGH OIL CONSUMPTION, THE NR 3 BEARING SEAL RING WAS FOUND LIBERA	TED FROM ITS SUPPORT (DUCT) ASSY, PN 75663U. ALL 30 RIVETS, PN AN123320, HAD FAILED UNDER MANUFACTURED HEAD. INVESTIGA	TION INTO CAUSES OF FAILURE ONGOING.									4	F			E20EA				 
1996010500026	19960105	00026	NM 	1996	1	5	95ZZZX7061 	1	19951128	G	5330		SKIN 			BOEING	727 	72723 	1384004	NM 										FS 481 STR 4L	CORRODED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972	72212				18428				WHILE PERFORMING INSPECTION OF THE BONDED CIRCUMFERENTIAL DOUBLER AT BS 481 PER AD 90-26-09 (SB 727-53-0084), MATERIAL L	OSS RANGING FROM 10-30 PERCENT WAS DETECTED IN THE AREA BOUNDED BY STR 4L TO STR 4R. UPON OPENING UP OF AREA FOR REPAIR	, PHYSICAL MEASUREMENT OF SKIN REVEALED MAXIMUM MATERIAL LOSS OF APPROXIMATELY 1 PERCENT. SUSPECT CAUSE: DELAMINATION 	OF BOND.			2	L	7	3 	4F				A3WE 					 
1996010500027	19960105	00027	NM 	1996	1	5	95ZZZX7062 	1	19951128	G	5712		RIB 			BOEING	727 	72723 	1384004	NM 										RT WS 601.5	CRACKED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972					18428				DURING INSPECTION OF AIRCRAFT PER AD 94-07-08 (SB 727-57-127), THE HYDROPRESSED RIB AT RT WS 601.5 WAS FOUND CRACKED IN 	2 PLACES ON THE LOWER FLANGE. ONE CRACK WAS AT THE AFT END FASTENER HOLE AND THE OTHER WAS AT THE THIRD FASTENER HOLE F	ORWARD OF THE AFT END. ALSO, UPPER FLANGE WAS FOUND CRACKED AT THE THIRD FASTENER HOLE AFT OF THE FORWARD END OF RIB. S	USPECT CAUSE: FATIGUE.			2	L	7	3 	4F				A3WE 					 
1996010500028	19960105	00028	NM 	1996	1	5	95ZZZX7063 	1	19951128	G	5320		SHEAR WEB 			BOEING	727 	72723 	1384004	NM 										FS 1168-1178	CORRODED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972	72212				18428				DURING INSPECTION OF AIRCRAFT PER CPC TASK CARD C53-224-04, THE FLOOR STRUCTURE SHEAR WEB WAS FOUND CORRODED BEYOND SRM 	LIMITS BETWEEN BS 1168 -BS 1178 AND LBL 30-LBL 36 (UNDER LT AFT LAVATORY).					2	L	7	3 	4F				A3WE 					 
1996010500029	19960105	00029	NM 	1996	1	5	95ZZZX7064 	1	19951128	G	5712		RIB 			BOEING	727 	72723 	1384004	NM 										LT WS 546.5	CRACKED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972					18428				WHILE INSPECTING AIRCRAFT PER AD 94-07-08 (SB 727-57-127), THE HYDROPRESSED WING RIB AT LT WS 546.5 WAS FOUND CRACKED ON	 ITS LOWER FLANGE ADJACENT TO THIRD FASTENER HOLE FORWARD OF THE AFT END OF RIB. SUSPECT CAUSE: FATIGUE.					2	L	7	3 	4F				A3WE 					 
1996010500030	19960105	00030	NM 	1996	1	5	95ZZZX7065 	1	19951128	G	5531		CLOSURE RIB 			BOEING	727 	72723 	1384004	NM 										BS 1570	CORRODED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972	72212				18428				WHILE PERFORMING CPC TASK CARD C55-391-30, THE VERTICAL STABILATOR'S UPPER RT CLOSURE RIB WAS FOUND EXFOLIATED ON ITS OU	TBOARD SIDE JUST FORWARD OF THE FORKED END OF THE AFT HINGE POINT FITTING FOR THE HORIZONTAL STABILIZER. CORROSION WAS 	REMOVED AND FOUND TO BE WITHIN LIMITS PER SRM 55-30-1, FIGURE 1. SUSPECT CAUSE: UNKNOWN.				2	L	7	3 	4F				A3WE 					 
1996010500031	19960105	00031	NM 	1996	1	5	95ZZZX7066 	1	19951128	G	5712		RIB 			BOEING	727 	72723 	1384004	NM 										LT WS 686.5	CRACKED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972					18428				DURING INSPECTION OF AIRCRAFT PER AD 94-07-08 (SB 727-57-127), THE HYDROPRESSED WING RIB AT LT WS 686.5 WAS FOUND CRACKE	D IN 2 PLACES AT THE LOWER FLANGE. ONE CRACK WAS AT THE AFTMOST FASTENER HOLE, THE OTHER WAS AT THE THIRD FASTENER HOLE	 FORWARD FROM THE AFT END OF RIB. SUSPECT CAUSE: FATIGUE.				2	L	7	3 	4F				A3WE 					 
1996010500032	19960105	00032	NM 	1996	1	5	95ZZZX7067 	1	19951128	G	5313		STRINGER 			BOEING	727 	72723 	1384004	NM 										FS 740 STR 21R	CORRODED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972	72212				18428				DURING THE COURSE OF ROUTINE MAINTENANCE, FUSELAGE STR 21R WAS FOUND EXFOLIATED, REQUIRING SRM REPAIR. SUSPECT CAUSE: A	REA IS DIRECTLY BELOW GALLEY, ALTHOUGH NO DIRECT EVIDENCE OF LEAKAGE WAS FOUND.					2	L	7	3 	4F				A3WE 					 
1996010500033	19960105	00033	NM 	1996	1	5	95ZZZX7068 	1	19951128	G	5712		RIB 			BOEING	727 	72723 	1384004	NM 										LT WS 601.5	CRACKED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972					18428				DURING INSPECTION OF AIRCRAFT PER AD 94-07-08 (SB 727-57-127), THE HYDROPRESSED WING RIB AT LT WS 601.5 WAS FOUND CRACKE	D IN 4 PLACES. THE UPPER FLANGE WAS CRACKED AT THE 2ND FASTENER HOLE FORWARD OF THE AFT END. THE LOWER FLANGE WAS CRAC	KED AT THE 3RD, 4TH, AND 5TH FASTENER HOLES AFT OF THE FORWARD END. SUSPECT CAUSE: FATIGUE.				2	L	7	3 	4F				A3WE 					 
1996010500034	19960105	00034	NM 	1996	1	5	95ZZZX7069 	1	19951128	G	5330		SKIN 			BOEING	727 	72723 	1384004	NM 										FS 360 STR 19R	CORRODED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972	72212				18428				WHILE INSPECTING AIRCRAFT PER AD 91-06-06 (SB 727-53-0072), THE FUSELAGE SKINS AT THE LAP JOINT AT STR 19R, BS 360 WERE 	FOUND CORRODED INSIDE THE LAP JOINT. SUSPECT CAUSE: DELAMINATION OF COLD BOND LAP JOINT.					2	L	7	3 	4F				A3WE 					 
1996010500035	19960105	00035	NM 	1996	1	5	95ZZZX7070 	1	19951128	G	5712		RIB 			BOEING	727 	72723 	1384004	NM 										RT WS 546.5	CRACKED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972					18428				WHILE INSPECTING AIRCRAFT PER AD 94-07-08 (SB 727-57-127), THE HYDROPRESSED WING RIB AT RT WS 546.5 WAS FOUND CRACKED ON	 LOWER FLANGE ADJACENT TO THE SECOND FASTENER HOLE FROM FORWARD END OF RIB. SUSPECT CAUSE: FATIGUE.					2	L	7	3 	4F				A3WE 					 
1995021700508	19950217	00508	EU 	1995	2	17	95ZZZX734 	1	19950201	G	2130	14640113	VALVE 			AMD 	FALC20	FALCON 	2720302	EU 										AIR COND	DEFECTIVE 	B			MJ7R	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	05	45MR					20123				PILOT REPORTED PRESSURIZATION FAILED IN-FLIGHT. PILOT SET EMERGENCY PRESSURIZATION. TROUBLESHOT SYSTEM, FOUND A/C VALV	E FAILED. REPLACED A/C VALVE, SYSTEM CHECKS GOOD. THIS UNIT REQUIRES INSPECTION EVERY 600 HOURS. OPERATOR AAIP HAS TH	IS VALVE ON CONDITION. RASMARK JOGA.				2	L	7	2 	4F				A7EU 					 
1995021700510	19950217	00510	SW 	1995	2	17	95ZZZX736 	1	19950120	G	3230	030A384932	BRACKET 			MTSBSI	MU2 	MU2B30 	5780410	SW 										MLG FWD DR ACT	FAILED 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			AP	APPROACH 	1			SO	04	134MA					507				FORWARD MLG DOOR ACTUATOR SUPPORT BRACKET TORN OUT. SB NR 172 WAS PREVIOSULY COMPLIED WITH, BUT SB 197A HAD NOT BEEN DO	NE. IF SB NR 197A IS COMPLIED WITH, THIS WILL NOT HAPPEN. THIS IS CAUSED BY THE LACK OF STRUCTURE STRENGTH OF THE FORW	ARD SUPPORT BRACKET, PN 030A-38493-2.				1	H	7	2 	3T				A2PC 					 
1995021700512	19950217	00512	CE 	1995	2	17	95ZZZX738 	1	19950123	G	3222	16981001127	HOUSING ASSY 		16981001127 	BEECH 	23 	C23 	1151242	CE 										NLG	DAMAGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	6007D					M2123				TOP OF NOSE GEAR STRUT, WHERE STEERING COLLAR ATTACHES, IS SHEARED OFF. ONE STEERING LIMIT STOP BOLT IS SHEARED OFF. O	THER STOP BOLT IS DAMAGED. THE STOP STRIKE IS DAMAGED (BENT). SHIMMY DAMPENER IS BENT AND DISTORTED. NOSE STEERING RO	D END, WHERE IT ATTACHES TO COLLAR, IS BENT.				1	L	7	1 	3O				A1CE 					 
1995021700513	19950217	00513	EA 	1995	2	17	95ZZZX739 	2	19950122	G	8530	LW16812	PUSHROD 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					NR 3 CYL INT	BENT 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			EA	11	6468F	2245 	2 			17273227	RL687276T			DURING FLIGHT, PILOT EXPERIENCED SUDDEN LOSS OF POWER AND ENGINE ROUGHNESS. AN UNEVENTFUL AIRPORT LANDING WAS MADE. IN	SPECTION BY MAINTENANCE PERSONNEL REVEALED NR 3 CYLINDER INTAKE PUSHROD BENT. OIL ADDITIVE, LW16702, ADDED 2 HOURS PREV	IOUSLY. ENGINE MAJOR OVERHAULED 2 HOURS PREVIOUSLY.				1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995021700516	19950217	00516	SO 	1995	2	17	95ZZZX742 	2	19950105	G	8540	652406	SHAFT GEAR 		643259A8 						CONT 	O520 	TSIO520R 	17040	SO 					STARTER CLUTCH	GALLED 	B			QX2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11							269515R			'NEW STYLE' STARTER CLUTCH SHAFT GEAR TEETH STARTING TO GALL. COMPLETE ENGINE FAILURE IS A RESULT OF THIS. REASON FOR 	'NEW STYLE' CLUTCH IS TO ELIMINATE THIS GALLING PROBLEM.										3	O			E8CE				 
1995021700518	19950217	00518	CE 	1995	2	17	95ZZZX744 	1	19950202	G	3260	1003818061	SWITCH 			BEECH 	76 	76 	1153005	CE 										LT MLG DOWNLOCK	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	6636L					ME256				PILOTS REPORTED LT DOWN AND LOCK LIGHT BLINKING INTERMITTENTLY. TROUBLEHSOT SYSTM FINDING DEFECTIVE GEAR DOWN SWITCH. R	EPLACED SWITCH IAW MM, SWUNG LANDING GEAR ON JACKS, OPS CHECKED OKAY.					1	L	7	2 	3O				A29CE 					 
1995021700519	19950217	00519	SO 	1995	2	17	95ZZZX745 	2	19950107	G	8520	6461402	STUD 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520M 	17032	SO 					NR 5 CYL	SHEARED 	B			EB1R	A				UNSCHED LANDING 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			EA	13	593C					421C0226	606951			AIRCRAFT MADE AN EMERGENCY LANDING DUE TO PROBLEM WITH LT ENGINE. 1) INVESTIGATION REVEALED NR 5 CYL TOP 4 CYL HOLD-DO	WN STUDS SHEARED OFF AND MOVEMENT OF CYL TOP AWAY FROM ENG CASE CAUSED A LARGE CRACK IN THE ENG CASE COMING FROM LOWER C	YL FLANGE AREA. 2) FURTHER INSPECTION OF ENG REVEALED UPPER FWD HOLD-DOWN STUD ON NR 4 CYL HAD BACKED OUT TO THE POINT	 WHERE IT CONTACTED A COOLING FIN OF CYL BENDING IT SLIGHTLY. 3) ENGINE REMOVED TO OVERHAUL FACILITY. FAA FORM 8020-2	 AFFIXED TO ENG BY FAA INSPECTOR.		1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995021700520	19950217	00520	SO 	1995	2	17	95ZZZX746 	2	19950107	G	8520	6461401	STUD 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520M 	17032	SO 					NR 5 CYL	SHEARED 	B			EB1R	A				UNSCHED LANDING 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	NR	NOT REPORTED 	1			EA	13	593C					421C0226	606951			AIRCRAFT MADE AN EMERGENCY LANDING DUE TO PROBLEM WITH LT ENGINE. 1) INVESTIGATION REVEALED NR 5 CYL TOP 4 CYL HOLD-DO	WN STUDS SHEARED OFF AND MOVEMENT OF CYL TOP AWAY FROM ENG CASE CAUSED A LARGE CRACK IN THE ENG CASE COMING FROM LOWER C	YL FLANGE AREA. 2) FURTHER INSPECTION OF ENG REVEALED UPPER FWD HOLD-DOWN STUD ON NR 4 CYL HAD BACKED OUT TO THE POINT	 WHERE IT CONTACTED A COOLING FIN OF CYL BENDING IT SLIGHTLY. 3) ENGINE REMOVED TO OVERHAUL FACILITY. FAA FORM 8020-2	 AFFIXED TO ENG BY FAA INSPECTOR.		1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995021700521	19950217	00521	NE 	1995	2	17	95ZZZX747 	3	19950130	G	6111	7863504	BLADE 													HAMSTD	5500	65500F1 	NE 	BUTT AREA	DAMAGED 	B			H2SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		5406 			863636					SUBJECT BLADE RECEIVED WITH SCORING DAMAGE AROUND THE O.D. OF THE BUTT AREA. DAMAGE EXITS 360 DEGREES AROUND THE BUTT A	ND IS APPROXIMATELY .010 INCH DEEP BY .025 INCH HIGH. DAMAGE APPEARS TO HAVE BEEN CAUSED BY RESIDUAL SHOT PEEN BALLS WH	ICH WERE TRAPPED INSIDE BLADE PIN.														6	C	P13NE	 
1995021700522	19950217	00522	NE 	1995	2	17	95ZZZX748 	3	19950130	G	6111	7863504	BLADE 													HAMSTD	5500	65500F1 	NE 	BUTT AREA	DAMAGED 	B			H2SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13		3200 	802 		863620					BLADE WAS RECEIVED WITH SCORING DAMAGE AROUND THE O.D. OF THE BUTT AREA. DAMAGE EXISTS 360 DEGREES AROUND BUTT AND IS A	PPROXIMATELY .020 INCH DEEP BY .025 INCH HIGH. DAMAGE APPEARS TO HAVE BEEN CAUSED BY RESIDUAL SHOT PEEN BALLS WHICH WER	E TRAPPED INSIDE BLADE PIN.														6	C	P13NE	 
1995021700523	19950217	00523	SW 	1995	2	17	95ZZZX749 	1	19950109	G	2710	010A610039	CHAIN 			MTSBSI	MU2 	MU2B30 	5780410	SW 										AIL CONTROL	SEPARATED 	D		A		A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			CL	CLIMB 	1			GL	03	211RV	6900 				502				AFTER A NORMAL LIFT OFF AND CLIMB OUT, FLYING PILOT NOTED HE WAS GETTING NO ROLL RESPONSE TO RT CONTROL (ROLL COLUMN INP	UT AND LITTLE RESPONSE TO LT WHILE IT SEEMED TO BE 'CATCHING'. THE CONTROL COLUMN LOST ALL 'FEEL' AND WOULD TURN A FULL	 360 DEGREES WITH NO RESPONSE IN AIRCRAFT ROLL. ELEVATOR CONTROL HAD NOT BEEN AFFECTED. CREW DECLARED AN EMERGENCY AND	 MADE AN UNEVENTFUL LANDING. UPON INSPECTION, ONE OF CONTROL CHAIN JOINT LINKS WAS FOUND SEPARATED FROM THE CHAIN. ALL	 LINK COMPONENTS FOUND BETWEEN FLOOR BOARDS. COMPONENTS INSPECTED, FOUND SERVICEABLE. CONTROL CHAIN REASSEMBLED, SPOIL	ER SYSTEM RIGGED. AIRCRAFT TEST FLOWN.	1	H	7	2 	3T				A2PC 					 
1995021700524	19950217	00524	EU 	1995	2	17	95ZZZX750 	1	19950101	G	2720	T67M45245	SUPPORT BRACKET 			SLNSBY	T67 	T67M260 	8323006	EU 										RUDDER BAR	SCREWS LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	3022C	295 				2129				RUDDER BAR SUPPORT BRACKETS ARE HELD ON BY SCREWS AND ARE COMING LOOSE. THERE ARE NO LOCKWASHERS INSTALLED. REOCMMEND 	INSTALLING LOCKWASHERS UNDER HEAD OF SCREW TO PREVENT SCREW FROM COMING LOOSE.					1	L	7	1 	3O			NT	A73EU 					 
1995021700526	19950217	00526	NE 	1995	2	17	95ZZZX752 	2	19950131	G	7230	C14	DISK 								PWA 	JT3D 	JT3D3B 	52039	NE 					N2 COMP	BLADE FAILURE 	B			ENVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19					J49382		668553			THE ENGINE HAD A N2 COMPRESSOR FAILURE. ALL REMAINING BLADES, STAGES 14 THROUGH 16, ARE SCRAP INCLUDING A SET OF 130 EA	CH T-1 BLADES; ALSO, STATORS FROM 13TH THROUGH 16TH ARE SCRAP DUE TO THE C-14 BLADE FAILURE UNKNOWN.										4	F			1E8				 
1995021700527	19950217	00527	EU 	1995	2	17	95ZZZX753 	1	19950104	G	4930	28616	HOSE 			BRAERO	1000 	BAE1251000 	1500287	EU 										APU FUEL	BURNED 	B			DXTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	533QS	920 				259033				FOUND DURING PRE-FLIGHT. APU HOSE (FUEL FEED) WAS BURNED THROUGH THE PLASTIC SHIELD. THE FIRE RETARDANT COATING HAD NO	T BEEN DAMAGED. CAUSE: HOSE LOCATED TOO CLOSE TO HOT AIR LINE. FIX: ROUTE LINE IN NEW POSITION.					2	L	7	2 	4F			RT	A3EU 					 
1995021700531	19950217	00531	SO 	1995	2	17	95ZZZX757 	1	19950101	G	7810	40B19850	CROSSOVER 			PIPER 	PA46 	PA46350P 		SO 										LT EXHAUST	BENT 	D	S			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	11	9210F					4022119				EXHAUST CROSSOVER IS BENT AT A DIFFERENT ANGLE THAN THE ORIGINAL PART. THE MANUFACTURER SAYS NOTHING HAS CHANGED IN THE	 MAKING OF THAT PIPE. WHILE TRYING TO INSTALL THIS PIPE, FOUND ALL THE COMPONENTS IT ATTACHES TO ARE PUT UNDER STRESS B	ECAUSE OF MISALIGNMENT.				1	L	7	1 	3O			RT	A25SO 					 
1995021700532	19950217	00532	SO 	1995	2	17	95ZZZX758 	1	19950101	G	7810	47C19848	TRANSITION 			PIPER 	PA46 	PA46350P 		SO 										LT EXH WASTEGATE	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	9210F	856 				4622119				EXHAUST TRANSITION APPEARED TO BE UNDER MISALIGNMENT STRESS. THREE EXHAUST COMPONENTS ATTACH TO THIS TRANSITION; THEREF	ORE, IT WOULD BE A HIGH STRESS AREA. SUBMITTER SUGGESTS TRANSITION MATERIAL MAY BE TOO THIN FOR THIS APPLICATION.					1	L	7	1 	3O			RT	A25SO 					 
1995021700534	19950217	00534	SO 	1995	2	17	95ZZZX760 	2	19950101	G	8530	649543	CYLINDER 			CESSNA	172 	172F 	2072414	CE 	CONT 	O300 	O300D 	17022	SO 					ROCKER BOSS	EXCESS CLEARANCE	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	5358R					17252889	29849D5D			DURING 100-HOUR ENGINE INSPECTION FOR AIRCRAFT ANNUAL INSPECTION, LOW COMPRESSION WAS NOTED ON CYLINDER NR 6. WHEN CYLI	NDER WAS REMOVED, SEVERE EXCESSIVE CLEARANCE WAS NOTED BETWEEN ROCKER SHAFT AND UNBUSHED ROCKER BOSSES ON A CYLINDER WIT	H 380 HOURS TT SINCE TCM. NEW CLEARANCE MEASURED .055 INCH. ALL OTHER CYLINDERS CHECKED. NR 2 CYLINDER FOUND WITH .03	5 INCH CLEARANCE - ALL OTHERS LESS THAN .020 INCH. INSTALLED 24, PN 22949, BUSHINGS PER TCM SB M73-13 AND C/W AD94-05-0	5. HEAVY ACCUMULATION OF BLACK SLUDGE FROM NOSE. AV-1 LUB. OIL FLUSHED FROM ENGINE INTERIOR.		1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995021700535	19950217	00535	SO 	1995	2	17	95ZZZX761 	2	19950101	G	8520		CRANKSHAFT 			CESSNA	172 	172F 	2072414	CE 	CONT 	O300 	O300D 	17022	SO 					FLANGE	DOWEL MISSING 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	01	5358R					17252889	29849D5D			DURING ANNUAL INSPECTION WHEN INSPECTING ENGINE CRANKSHAFT EXPOSED, NOTED THE 2 DOWEL HOLES IN THE CRANKSHAFT FLANGE HAD	 NO VISIBLE DOWELS INSTALLED. UPON PROPELLER REMOVAL FOR FURTHER INSPECTION, NO DOWELS WERE FOUND INSTALLED IN PROPELLE	R HUB. DOWELS WERE PROCURED AND INSTALLED AND SMOOTHER OPERATION NOTED WITH DOWELS INSTALLED.				1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1995021700536	19950217	00536	CE 	1995	2	17	95ZZZX762 	1	19950131	G	2810	963800363	ADAPTER 			BEECH 	55 	E55 	1152732	CE 										FILLER NECK	LEAKS 	B			RT2R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	11	163SP	3978 				TE872				LEFT MAIN FUEL TANK HAD PERSISTENT LEAKAGE EVIDENT AT LOWER WING SKIN ADJACENT TO DRAIN. INVESTIGATION FOUND SOURCE TO 	BE IN THE AREA OF THE FILLER NECK ADAPTER ASSY. SEALS AND GASKETS WERE REPLACED WITH NO POSITIVE RESULTS. SUBSEQUENT R	EMOVAL AND TESTING OF THE ADAPTER ASSY FOUND LEAKAGE TO BE FROM AROUND THE SEAM WHERE UPPER AND LOWER FLANGE HALVES WERE	 MATED. THIS JOINT IS FACTORY MADE AND APPEARS BRAZED OR SOLDERED. FUEL WOULD LEAK FROM THAT POINT ONLY WHEN TANK WAS 	COMPLETELY FULL AND WOULD TRAVEL UNDER THE FUEL CELL TO THE LOWER WING ROOT AREA BEFORE BECOMING VISIBLE. SUBMITTER REC	OMMENDS AREA BE INVESTIGATED AS POSSIBLE SOURCE WHEN OTHER AREAS FAIL TO REVEAL SOURCE OF FUEL LEAKAGE.	1	L	7	2 	3O				3A16 					 
1995021700537	19950217	00537	SO 	1995	2	17	95ZZZX763 	2	19950130	G	7421	PHB32E	SPARK PLUG 	CHAMPION 		CESSNA	185 	185A 	2072804	CE 	CONT 	O550 	IO550* 		SO 					ENGINE	FAULTY 	H				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SW	99	1650Z					1850450	284092R			INSTALLED FACTORY NEW CONTINENTAL IO-550D ON CESSNA, N1650Z. ABOUT 15 TO 20 MINUTES INTO THE TEST FLIGHT, ENGINE BEGAN 	RUNNING ROUGH. OFF AIRPORT LANDING WAS MADE. THE PLUGS WERE CLEANED, TESTED, AND RESINTALLED. GROUND RUN OKAY AND THE	 AIRCRAFT WAS RETURNED TO SERVICE.				1	H	7	1 	3O	3	O		3A24 	E3SO				 
1995021700538	19950217	00538	SO 	1995	2	17	95ZZZX764 	2	19950101	G	8540	635048A1	ADAPTER 			PIPER 	PA28 	PA28RT201T 	7102817	SO 	CONT 	O360 	TSIO360FB 	17025	SO 					STARTER	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	8271Z					28R8331001	310810			STARTER ADAPTER FAILED. FOUND SPRING, PN 539800, BROKE AT LOCATION OF LOCK SCREW, PN 633845.						1	L	7	1 	3O	3	O		2A13 	E9CE				 
1995021700539	19950217	00539	EA 	1995	2	17	95ZZZX765 	2	19950207	G	8520	67514	GEAR 			PIPER 	PA32 	PA32300 	7103212	SO 	LYC 	O540 	IO540K1A5 	41532	EA 					CRANKSHAFT	FAILED 	D				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			EA	05	55682		1300 			327340108	L1063448			ENGINE LOST POWER AT 80 KNOTS. ENGINE WAS REMOVED AND CRANK GEAR FOUND BROKEN AND BOLT STRIPPED.						1	L	7	1 	3O	3	O		A3SO 	1E4				 
1995021700540	19950217	00540	SO 	1995	2	17	95ZZZX766 	2	19950106	G	8540		ADAPTER 			CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					STARTER	BEARING FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	421BR		175 			421B0110	235283R			THE STARTER ADAPTER FORWARD SHAFT SUPPORT BEARING WAS FOUND IN THE OIL FILTER AND HAD DISPERSED INTO THOUSANDS OF PIECES	. THE CASE WAS DAMAGED BY THE SHAFT SLAPPING AROUND. SUBMITTER BELIEVES THE DAMPENER WAS OLD AND POSSIBLY OUT OF BALAN	CE. THE ADAPTER IS NEW LOOKING AS IF CLEANED AT ENGINE OVERHAUL, BUT THE DAMPENER IS CLEARLY OLDER THAN STARTER ADAPTER	.			1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995021700541	19950217	00541	SO 	1995	2	17	95ZZZX767 	1	19950130	G	2730		CONTROL 			PIPER 	PA38 	PA38112 	7103812	SO 										ELEVATOR	BINDING 	G		A		A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			TO	TAKEOFF 	1			SW	15	4279E					3878A0527				INVESTIGATION OF OFF AIRPORT LANDING FOUND EVIDENCE OF VACUUM FILTER LINES BEING CHAFED. IT WAS REPORTED ELEVATOR CONTR	OL FAILED TO RESPOND DURING TAKEOFF. SUBMITTER SUSPECTS CHAFE ON HOSE LINES IS INDICATIVE OF BINDING OR A CONTRIBUTING 	FACTOR TO LOSS OF ELEVATOR CONTROL. RECOMMENDS MORE ATTENTION TO CONTROL CLEARANCES DURING INSPECTION. HOSE LINE, PN 7	791005.			1	L	7	1 	3O				A18SO 					 
1995021700542	19950217	00542	CE 	1995	2	17	95ZZZX768 	1	19950202	G	7922	75944	BYPASS VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	13FC		1583 		119679	M2017				WHILE COMPLYING WITH LYCOMING SB 518, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. CRIMP NUT LOOSE DUE TO POOR	 DESIGN.					1	L	7	1 	3O				A1CE 					 
1995021700543	19950217	00543	SO 	1995	2	17	95ZZZX769 	1	19950202	G	7922	53E19600	BYPASS VALVE 			PIPER 	PA28 	PA28R201 	7102816	SO 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	9436C		397 		48602	28R7837198				WHILE COMPLYING WITH LYCOMING SB 518, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. CRIMP NUT LOOSE DUE TO POOR	 DESIGN.					1	L	7	1 	3O				2A13 					 
1995021700544	19950217	00544	SO 	1995	2	17	95ZZZX770 	1	19950131	G	5712	4042313	RIB 			PIPER 	PA31 	PA31350 	7103110	SO 										RT WS 49.0	CRACKED 	B			J8SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	2QC	3984 				317752124				WHILE PERFORMING A 200-HOUR INSPECTION, FOUND RIB CRACKED IN WHEELWELL, RT WING STA 49.0 INCH. FOUND RUBBER BUMPER ASSY	, PIPER PN 42746-00, WORN OUT AND LANDING GEAR HITTING RIB WHEN LANDING GEAR SELECTED UP (IN-FLIGHT) COULD NOT DUPLICATE	 ON GROUND. SUGGEST REPLACING RUBBER BUMPERS WHEN THEY SHOW WEAR.				1	L	7	2 	3O				A20SO 					 
1995021700545	19950217	00545	SO 	1995	2	17	95ZZZX771 	1	19950131	G	5751	4019016	SPAR 			PIPER 	PA31 	PA31350 	7103110	SO 										LT AILERON	CRACKED 	B			J8SR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	2QC	3984 				317752124				WHILE COMPLYING WITH PIPER SB NR 974, AILERON HINGE REPLACEMENT AND INSPECTION, FOUND SPAR AND DOUBLER CRACKED UNDER INB	OARD AILERON HINGE. SUBMITTER SUGGESTS THIS SHOULD NOT OCCUR AGAIN AFTER COMPLIANCE WITH THIS SB AS THE NEW HINGE BRACK	ET IS WIDER.				1	L	7	2 	3O				A20SO 					 
1995021700546	19950217	00546	EU 	1995	2	17	95ZZZX772 	1	19950203	G	3210	TB1009098100	SCISSORS 		TB1041013000	SOCATA	TB9 	TB9 	8680694	EU 										MLG	CORRODED 	B			DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	175ER	3336 				1352				INSPECTION OF LANDING GEAR FOUND LOWER SCISSORS WITH SEVERE CORROSION NEAR OUTBOARD BOLT HOLE.						1	L	7	1 	3O			NT	AS1EU 					 
1995021700547	19950217	00547	CE 	1995	2	17	95ZZZX773 	1	19950202	G	7922	75944	BYPASS VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	5115R		534 			M1974				WHILE COMPLYING WITH LYCOMING SB 518, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. CRIMP NUT LOOSE DUE TO POOR	 DESIGN.					1	L	7	1 	3O				A1CE 					 
1995021700548	19950217	00548	NM 	1995	2	17	95ZZZX774 	1	19950208	G	8120	6007440002	TURBOCHARGER 			PIPER 	PA60 	PA60601P 	7106012	NM 	LYC 	O540 	TIO540U2A 	41532	EA 					CENTER SECTION	OIL LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	13	6067Y	204 				61P066079633	L941961A			DURING ANNUAL INSPECTION, CENTER SECTION OF TURBO LEAKING OIL. REMOVED FITTINGS, FOUND SEVERAL CHUNKS OF METAL INSIDE C	ENTER SECTION. NO EVIDENCE OF METAL CONTAMINATION IN OIL FILTER OR ENGINE SCAVENGE PUMP. TURBO REPLACED. NOTE: OIL W	AS LEAKING INTO INDUCTION SYSTEM.				1	M	7	2 	3O	3	O	RT	A17WE 	E14EA				 
1995021700549	19950217	00549	NE 	1995	2	17	95ZZZX775 	2	19950102	G	7230		ENGINE 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					COMPRESSOR	LOCK UP 	B	L		DYRD	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	94LG	391 				2728	9288			ENGINE MALFUNCTION, COMPRESSOR LOCK UP AFTER SHUT DOWN. ENGINE START SUCCESSFUL AFTER 3.5 HOURS COOL DOWN. INSPECTION 	FOUND LARGE AMOUNTS OF CARBON FROM LABYRINTH ENVELOPE.					1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995021700569	19950217	00569	CE 	1995	2	17	95ZZZX786 	1	19950209	G	2820	10138901157	CHECK VALVE 			BEECH 	B300 	B300 	1159232	CE 										FUEL DIST	DEFECTIVE 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	100BG	1620 				FL6				CHECK VALVE LEAKS INTERNALLY AND CAUSES THE AUXILIARY TANK TO GRAVITY FILL OVERNIGHT. TWO VALVES FAILED IN THE LAST 200	 HOURS.					2	L	7	2 	4T			RT	A24CE 					 
1995021700570	19950217	00570	CE 	1995	2	17	95ZZZX787 	1	19950207	G	5210	29093	HANDLE 			CESSNA	500 	550 	2076604	CE 										CABIN DOOR	BROKE 	B			DXTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	31RC	6975 				5500155				WHEN PILOT CLOSED DOOR, DOOR HANDLE BROKE OFF (OUTSIDE HANDLE OF DOOR).						1	L	7	2 	4F				A22CE 					 
1995021700571	19950217	00571	CE 	1995	2	17	95ZZZX788 	1	19950207	G	5260	651900948	STEP ASSY 			CESSNA	500 	S550 	2076607	CE 										CABIN DOOR	CRACKED 	B			DXTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	98QS	7580 				S5500098				UPON INSPECTION, FOUND STEP ASSY STOW DETENT BLOCK SUPPORT CRACKED. SUBMITTER SUGGESTED MANUFACTURE PART WITH DIFFERENT	 MATERIAL OR STRONGER DESIGN.					1	L	7	2 	4F			RT	A22CE 					 
1995021700572	19950217	00572	CE 	1995	2	17	95ZZZX789 	1	19950207	G	5260	651900934	STEP ASSY 			CESSNA	500 	550 	2076604	CE 										CABIN DOOR	BLOCK BROKE 	B			DXTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	07	31RC	6988 				5500155				UPON STOWING OF STEP ASSY, DETENT BLOCK SUPPORT BROKE. FOUND EXCESSIVE WEAR ON DETENT BLOCK CATCHES AND BLOCK. SUBMITT	ER SUGGESTS MORE FREQUENT LUBE OF CATCHES AND BETTER DEFINITION OF ALLOWABLE WEAR.					1	L	7	2 	4F				A22CE 					 
1995021700573	19950217	00573	EA 	1995	2	17	95ZZZX790 	2	19950206	G	7414	10382952	IMPULSE COUPLING	BENDIX 	D6LN3000 	CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540J3C5 	41532	EA 					FLYWEIGHTS	FAILED 	B			UIVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	7348X	863 			85230256	R18200083	L1984040A			AIRCRAFT WOULD NOT START. FLYWEIGHTS WORE OUT PER INSPECTION REQUIRED IN AD 78-09-07. THIS WAS THE NEW SNAP-ON TYPE CO	UPLING ALSO.					1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1995021700574	19950217	00574	NE 	1995	2	17	95ZZZX791 	2	19950121	G	7321	72995110	CAM LEVER 	HAMSTD 	JF2602 						PWA 	JT8 	JT8* 	52044	NE 					FUEL CONTROL	DISENGAGED 	B			BN4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05		8194 	261 		F6179					FUEL CONTROL FAILURE TO REACH REVERSE POSITION. POWER LEVER HUNG UP INTERMITTENLY AT RECEIVING INSPECTION - NO PROBLEMS	 DURING AS-IS TEST. TEAR-DOWN OF THE UNIT REVEALED CAM LEVER ROLLER DISENGAGEMENT.										4	F			E2EA				 
1995021700575	19950217	00575	WP 	1995	2	17	95ZZZX792 	2	19950101	G	7200		ENGINE 			SWRNGN	SA227 	SA227AC 	8780603	SW 	GARRTT	TPE331	TPE33111U 	01514	WP 					LT ENGINE	FOD DAMAGE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	3116F					AC594				RAG INGESTION ON ENGINE START. ENGINE REMOVED, SENT TO 'THE TURBINE GROUP 1389GRG AVIATION DR., HANGAR 16, MELBOURNE, F	L. AERO-CONDOR S.A., LIMA, PERU, AR 129.14 OPERATOR.					1	L	7	2 	4T	4	T		A8SW 	E4WE				 
1995021700577	19950217	00577	CE 	1995	2	17	95ZZZX794 	1	19950209	G	5511		SPAR 			LEAR 	25 	25 	5170506	CE 										HORIZ STAB	DELAMINATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	65RC	12373				055				SCHEDULED INSPECTION REVEALED DELAMINATED LT UPPER FORWARD MAIN SPAR CAP FROM BL42.25 TO BL55.30. FURTHER INSPECTION RE	VEALED SAME ON RT SIDE FROM BL41.52 TO BL51.77. SUBMITTER SUGGESTS CAUSE MAY HAVE BEEN FROM INADEQUATE HEAT TREATMENT A	T TIME OF MANUFACTURE. RECOMMEND USING ULTRASONIC OR EDDY CURRENT INSPECTIONS TO ENTIRE LENGTH OF SPAR.				2	L	7	2 	4J				A10CE 					 
1995021700579	19950217	00579	CE 	1995	2	17	95ZZZX796 	1	19950101	G	2821	369200581	PLATE 			BEECH 	35 	V35B 	1151548	CE 										FUEL STRAINER	MISMANUFACTURED 	B			DDNR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	27	23583					D10087				DURING AN ANNUAL INSPECTION, COMPLIED WITH BEECH MANDATORY SB NR 2518 BY ORDERING A NEW FUEL STRAINER PLATE. UPON RECEI	VING THE PLATE, IT WAS NOTED THE SCREEN WOULD NOT SEAT AGAINST THE PLATE PROPERLY. FURTHER INVESTIGATION SHOWED THAT AN	 EXCESS OF EPOXY TO ATTACH THE SPRING TO THE PLATE WAS INTERFERING WITH THE SCREEN POSITIONING. THE EXCESS EPOXY WAS RE	MOVED AND SCREEN POSITIONING WAS NORMAL. SUBMITTER STATED IF THE PLATE HAD BEEN INSTALLED AS RECEIVED FROM BEECH, PROPE	R FUEL FILTERING WOULD NOT HAVE EXISTED.		1	L	7	1 	3O				3A15 					 
1995021700580	19950217	00580	CE 	1995	2	17	95ZZZX797 	1	19950123	G	7120	505403042	BEAM 			CESSNA	421 	421C 	2076016	CE 										LT ENG AFT	CRACKED 	B			DDNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	27	58ZP	6073 				421C0705				UPON REMOVING LEFT ENGINE FOR TBO REPLACEMENT, INSPECTION OF THE NACELLE STRUCTURE REVEALED THE AFT ENGINE BEAM WAS CRAC	KED AT THE BEND WHERE THE OUTBOARD TAB ATTACHES TO THE FORE AND AFT ENGINE BEAM. THE CRACK IS APPROXIMATELY ONE INCH LO	NG AND ORIGINATES FROM THE AFT END OF THE BEND.				1	L	7	2 	3O				A7CE 					 
1995021700581	19950217	00581	CE 	1995	2	17	95ZZZX798 	1	19950130	G	2160	45AS63018093	SENSOR 			BEECH 	MU300 	400BEECH 		CE 										CABIN DUCT TEMP	DAMAGED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	56BE	1515 	643 			RK13				THE GASKET SEALING THIS VALVE TO THE DUCTING BLEW OUT. THE AIR GOING THROUGH THIS DUCT IN THIS AREA IS EXTREMELY HOT (B	LEED AIR). THIS VALVE IS MADE OUT OF PLASTIC AND AFTER THE GASKET BLEW OUT, IT MELTED SEVERELY AROUND ITS MOUNTING BASE	. THIS VALVE IS VERY HARD TO SEE AND GET AT. HOT AIR WAS ESCAPING INTO THE BACK OF THE AIRCRAFT. SUBMITTER SUGGESTS T	HESE VALVES NOT BE MADE OUT OF PLASTIC. PRESSURIZATION AND CONDITIONED AIR WAS AFFECTED BY THIS.			2	H	7	2 	4F			RT	A16SW 					 
1995021700582	19950217	00582	GL 	1995	2	17	95ZZZX799 	3	19950210	G	6114		HUB 			CESSNA	185 	A185F 	2072821	CE 						MCAULY	D3A34	D3A34C403 	GL 	PROP	CRACKED 	B	S		UF2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	5263E	3025 	325 			18503947		796630		PROPELLER IN FOR OVERHAUL. LAST DONE WAS 11-88. SB'S 154, 154A, 154B HAD BEEN COMPLIED WITH. THESE ADDRESS POLISH AND	 RADIUS THE SLOT AREAS AND APPLY CHROMATE FOR CORROSION PROTECTION.					1	H	7	1 	3O				3A24 		5	C	P47GL	 
1995021700583	19950217	00583	SO 	1995	2	17	95ZZZX800 	1	19950110	G	2731	8281530	CONTROL CABLE 			PIPER 	PA46 	PA46310P 	7104605	SO 										ELEVATOR TRIM	FRAYED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	166CP	5855 				468408023				DURING ANNUAL INSPECTION, FOUND AFT ELEVATOR TRIM CABLE SEVERELY FRAYED AT PITCH SERVO CAPSTAN. CABLE WAS ROUTED CORREC	TLY AND TENSIONED PROPERLY. THIS IS SECOND AIRCRAFT FOUND WITH THIS CONDITION. PROBLEM SEEMS TO BE UNAVOIDABLE DUE TO 	NORMAL WEAR. RECOMMEND INSPECTION OF THIS AREA MORE CLOSELY ON AIRCRAFT WITH MORE THAN 2,500 HOURS TT.				1	L	7	1 	3O			RT	A25SO 					 
1995021700584	19950217	00584	CE 	1995	2	17	95ZZZX801 	1	19950109	G	3230	25410801	EXTEND ARM 			CESSNA	303 	T303 	2073820	CE 										LT MLG	BROKE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	9382C	3170 				T30300175				DURING ANNUAL, FOUND LT MLG RETRACT/EXTEND ARM CRACKED THREE-FOURTHS AROUND WELD WHERE SHORT ARM IS WELDED TO MAIN ARM. 	 PART BROKE COMPLETELY UPON REMOVAL. SUSPECT CRACK IN WELD FOR LONG TIME.					1	L	7	2 	3O				A34CE 					 
1995021700585	19950217	00585	SO 	1995	2	17	95ZZZX802 	1	19950130	G	5310		STRUCTURE 			MAULE 	M4 	M4210 	5460108	SO 										FUSELAGE	CORRODED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	9808M	1845 				1041				WHEN AIRCRAFT'S INTERIOR WAS REMOVED TO FACILITATE FUSELAGE FRAME REPAIR, CORROSION WAS FOUND ON ALL OF THE 4130 STEEL F	USELAGE STRUCTURE THAT WAS COVERED BY THE INSULATION. THE INSULATION APPEARED TO BE ORIGINAL FACTORY INSTALLATION, IT W	AS FIBERGLASS BATT THAT HAS A PROPENSITY TO ATTRACT AND HOLD MOISTURE. MOST OF THE INSULATION IN THIS A/C WAS DAMP OR W	ET (COULD WRING WATER OUT OT IT). THIS A/C IS TIED DOWN OUT IN THE WEATHER. ACCOMPLISH FREQUENT (AT LEAST TWICE A YEAR	) INSPECTIONS OF STRUCTURE UNDER THE INSULATION AND CHECK INSULATION CONDITION.		1	H	7	1 	3O				3A23 					 
1995021700586	19950217	00586	SO 	1995	2	17	95ZZZX803 	2	19950131	G	8530	625393	RETAINER 		642343 	CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520L 	17032	SO 					VALVE SPRING	BROKEN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	234CN	977 				421C0404	272380R			ANOTHER OPERATOR OF CESSNA 421'S ADVISED THE NEED TO REMOVE VALVE SPRINGS TO CHECK THE SPRING RETAINER (PN 642343) FOR B	REAKAGE DUE TO VALVE GUIDE NOT BEING INSTALLED ALL THE WAY - THEREBY CAUSED 'ROCKING' AS SEAT IS HELD OFF OF CYLINDER. T	HIS OPERATOR DISCOVERED THIS PROBLEM AFTER INSTALLATION OF MAGNETIC PICK-UP DRAIN PLUGS (AND LENGTHY SEARCHING).				1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995021700587	19950217	00587	CE 	1995	2	17	95ZZZX804 	1	19950120	G	5343	05411212	BRACKET 			CESSNA	172 	172F 	2072414	CE 										RT MLG OUTB	CRACKED 	G		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	5207F	9637 				17253206				RIGHT OUTBOARD GEAR SUPPORT BRACKET CRACKED. CRACK IS ON U-BOLT MOUNT HOLE (FORWARD) AND EXTENDS TO OUTBOARD SIDE OF BR	ACKET. CRACK FOUND DURING ROUTINE INSPECTION. SPECIFIC CAUSE UNKNOWN, BUT MAY BE DUE TO HIGH AIRFRAME HOURS AND THE AI	RCRAFT BEING USED AS PRIMARY TRAINER SINCE NEW. SUBMITTER RECOMMENDS OTHER SERIES AIRCRAFT WITH THIS SIMILAR GEAR DESIG	N TO HAVE CLOSE INSPECTION FOR THIS DEFECT AT NEXT SCHEDULED INSPECTION.			1	H	7	1 	3O			NT	3A12 					 
1995021700588	19950217	00588	CE 	1995	2	17	95ZZZX805 	1	19950121	G	3230	084012515	PUSH/PULL ROD 			CESSNA	340 	340A 	2076405	CE 										RT MLG WELL	FAILED 	D		A		O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			SO	15	341SC	968 				340A1810				RIGHT LANDING GEAR DOWN LIGHT DID NOT COME ON AFTER GEAR EXTENSION. PILOT TRIED SEVERAL RETRACTIONS AND EXTENSIONS, BUT	 LIGHT WOULD NOT COME ON. SOUNDS DURING EXTENSION SEEMED NORMAL. WHEN A/C TOUCHED DOWN AND STARTED ROLL-OUT, THE RT GE	AR FOLDED ONTO INBOARD DOOR. PROPELLER STRUCK GROUND AND FLAPS WERE DAMAGED. FOUND GEAR LOCK BELLCRANK PUSH/PULL ROD B	ROKE AT OTBD ROD END ALLOWING GEAR TO COME UNLOCKED. APPEARS TO BE SOME STRESS CRACKS IN ROD WHERE BEARING IS MOUNTED.			1	L	7	2 	3O				3A25 					 
1995021700589	19950217	00589	CE 	1995	2	17	95ZZZX806 	1	19950207	G	7922	75944	VALVE 			BEECH 	76 	76 	1153005	CE 										THERMO BYPASS	CRIMP NUT LOOSE 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	3868N		820 		122249	ME407				WHILE COMPLYING WITH LYCOMING SB 518, FOUND CRIMP NUT LOOSE AS SHOWN IN STEP 2 OF BULLETIN. CRIMP NUT LOOSE DUE TO POOR	 DESIGN.					1	L	7	2 	3O				A29CE 					 
1995021700594	19950217	00594	SO 	1995	2	17	95ZZZX811 	2	19950101	G	8520	642001	CRANKCASE 			BEECH 	58 	58 	1152740	CE 	CONT 	O520 	IO520CB 	17032	SO 					NR 2	CYL SEPARATED 	D	P			E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	CL	CLIMB 	1			CE	03	66518	2889 	540 		9A198PL	TH1044	571291			AFTER TAKEOFF, PILOT NOTICED ROUGHNESS IN RIGHT ENGINE, HE REDUCED POWER, ENGINE RAN SMOOTH FOR A SHORT TIME THEN BECAME	 ROUGH AGAIN. AT THIS TIME, OIL WAS NOTED ON THE TOP OF RIGHT COWL. THE PILOT FEATHERED THE ENGINE AND LANDED. NR 2 C	YLINDER WAS FOUND SEPARATED FROM THE CASE AND TOP THROUGH-BOLT FOUND BROKEN. CANNOT DETERMINE WHICH FAILED FIRST, THE B	OLT OR THE CASE.			1	L	7	2 	3O	3	O		3A16 	E5CE				 
1995021700595	19950217	00595	CE 	1995	2	17	95ZZZX812 	1	19950125	G	3240	30100	BRAKE 	PARKERHANFIN		CESSNA	421 	421B 	2076014	CE 										RT MLG	DAMAGED 	D				K				NONE 				M	B		OVER TEMP 	SMOKE/FUMES/ODORS/SPARKS 		IN	INSP/MAINT 	1			EA	25	616D					421B0140				AIRCRAFT WAS TOWED WITH PARKING ON. RIGHT BRAKE GENERATED SO MUCH HEAT THAT TIRE SIDEWALL STARTED BURNING. REPLACED TI	RE, TUBE, AND BRAKE LININGS. OPERATION CHECKED OKAY.					1	L	7	2 	3O				A7CE 					 
1995021700596	19950217	00596	CE 	1995	2	17	95ZZZX813 	1	19950129	G	3210	NAS464P5A42	BOLT 		12435191 	CESSNA	206 	U206B 	2073322	CE 										NLG DRAG BRACE	FAILED 	G				K				NONE 				O			OTHER 			LD	LANDING 	1			WP	09	3817G	8044 				U2060817				ON LANDING ROLL-OUT, NORMALLY FIXED NOSE LANDING GEAR DRAG BRACE AFT ATTACH BOLT FAILED ALLOWING LANDING GEAR TO PARTIAL	LY RETRACT IN FORWARD DIRECTION. INSPECTION OF BOLT INDICATED THAT A PREVIOUS FRACTURE IN THE THREADED AREA EXISTED. P	REVIOUS NLG MAINTENANCE OCCURRED 10-93. AS A PRECAUTION, THE FORWARD BOLT/NUT WAS REPLACED ALSO.				1	H	7	1 	3O				A4CE 					 
1995021700597	19950217	00597	CE 	1995	2	17	95ZZZX814 	1	19950201	G	2810	3538013511	CELL 			BEECH 	36 	A36 	1151604	CE 										LT MAIN FUEL	DELAMINATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	3696Y	1539 	740 		W4710	E1699				DURING A SCHEDULED INSPECTION OF THE AIRCRAFT, THE LT MAIN FUEL CELL INTERIOR WAS STARTING TO DELAMINATE. UPON REMOVAL 	OF THE FUEL CELL, INSPECTION OF THE INTERIOR DISCLOSED THAT CELL MATERIAL WAS PARTIALLY OBSTRUCTING THE FUEL CELL OUTLET	 STRAINER. SUBMITTER STATED IT IS SUSPECTED THE AIRCRAFT WAS IDLE FOR A PERIOD OF TIME WITH LESS THAN FULL FUEL.				1	L	7	1 	3O				3A15 					 
1995021700598	19950217	00598	CE 	1995	2	17	95ZZZX815 	1	19950207	G	7922	53E19600	VALVE 			BEECH 	23 	C23 	1151242	CE 										THERMO BYPASS	DEFECTIVE 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	3829X		1769 		2872	M2306				WHILE COMPLYING WITH LYCOMING SB 518, FOUND VALVE ASSEMBLY LOOSE IN VALVE HOUSING. SNAP RING GROOVE IN VALVE WORN OUT. 	 FOUND SEVERE NICKS IN RETURN SPRING AND BELLOWS. NICKS APPEAR TO BE CAUSED BY EXCESSIVE SIDE MOVEMENT DUE TO LOOSE SNA	P RING GROOVE.				1	L	7	1 	3O				A1CE 					 
1995022400001	19950224	00001	CE 	1995	2	24	95ZZZX816 	1	19950209	G	7602	98620105	CONTROL 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					MIXTURE	BROKE 	H				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			SW	15	4818D					17272367				WHILE IN-FLIGHT, PILOT EXPERIENCED SUDDEN LOSS OF POWER. PILOT ACTUATED CARBURETOR HEAT, SWITCHED FUEL TANKS WITH NO RE	SULTS. PILOT WAS FORCED TO LAND THE 172 ON THE HIGHWAY. PILOT AND PLANE RECEIVED NO INJURIES OR DAMAGE. A MECHANIC DI	SCOVERED THAT THE MIXTURE CONTROL HAD BROKE AT THE CARBURETOR MIXTURE ATTACH POINT. THE MECHANIC ALSO NOTICED THAT THE 	BOLT DID NOT PIVOT IN THE CARB MIXTURE ARM. THIS CONDITION WORK HARDENED THE MIXTURE CONTROL TILL THE CONTROL BROKE. M	ECHANIC RECOMMENDS THAT UPON INSTALLATION OF THE CARB, OR THE MIXTURE CONTROL, MAKE SURE THE BOLT PIVOTS IN THE MIXTURE 	ARM OF THE CARB. INSPECTIONS SHOULD ALSO INCLUDE A VISUAL CHECK TO MAKE SURE THE BOLT PIVOTS.	1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1995022400002	19950224	00002	SO 	1995	2	24	95ZZZX817 	2	19950125	G	7322	MA35PA	CARBURETOR 	FACET 		AMTR 	MSTG2 	MUSTANG2 		GL 	CONT 	O300 	O300B 	17022	SO 					ACCEL PUMP	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	132RK				103237	132	7758D32			DURING ANNUAL INSPECTION, CARBURETOR WAS DISCOVERED LEAKING AND MIXTURE CUT-OFF WOULD NOT WORK. DISASSEMBLY REVEALED TH	AT LEATHER ON ACCELERATOR PUMP PISTON WAS WORN CAUSING FUEL TO OVERFLOW INTO VENTURI. GASKET SET DID NOT INLCUDE A REPL	ACEMENT SO ONE HAD TO BE SPECIAL ORDERED. RECOMMEND INCLUDING REPLACEMENT IN THE GASKET KIT.				1	L	7	1 	3O	3	O		EXPA1L71	E253				 
1995022400003	19950224	00003	SO 	1995	2	24	95ZZZX818 	1	19950201	G	3230	38078002	DOWNLOCK 			PIPER 	PA32 	PA32300 	7103212	SO 										NLG	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	5910V	3100 				327780377				DURING ANNUAL INSPECTION, DOWNLOCK FOUND BINDING ON DOWNLOCK BOLT. DOWNLOCK CRACKED AND TIP WAS MISSING.						1	L	7	1 	3O				A3SO 					 
1995022400004	19950224	00004	CE 	1995	2	24	95ZZZX819 	1	19950205	G	5510	073210110	HINGE 			CESSNA	180 	180A 	2072604	CE 										RT HORIZ STAB	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	5384D	2337 				50284				UPON ANNUAL INSPECTION, FOUND SEVERE EXFOLIATION CORROSION ON RT HORIZONTAL STABILIZER HINGE. NOTE: ACFT USED ON FLOAT	S.					1	H	7	1 	3O				5A6 					 
1995022400005	19950224	00005	GL 	1995	2	24	95ZZZX820 	1	19950101	G	2842	389AM	SENSOR 			BLANCA	17 	1731ATC 	1220437	GL 										AUXILIARY FUEL	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1285R	2233 				31026				VARIABLE RESISTOR CORE BROKE CAUSING AN ARC. BELIEVE TO HAVE BEEN CAUSED BY VIBRATION DUE TO WEIGHT OF FLOAT HANGING IN	 ON EMPTY TANK. RECOMMEND REPLACING SENDING UNIT WITH LATER DESIGN, SENDING UNIT, PN 7740-57.					1	L	7	1 	3O				A18CE 					 
1995022400006	19950224	00006	CE 	1995	2	24	95ZZZX821 	1	19950109	G	5320	07120591	SUPPORT 			CESSNA	182 	182R 	2072731	CE 										BATTERY	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	9704E	1300 				68439				TWO SUPPORTS INCLUDED IN BATTERY MOUNT ASSY. BOTH PARTS CRACKED AT ENDS OF PIECES WHERE NUTPLATES LOCATED. IDENTICAL C	ONDITOIN FOUND ON ANOTHER LIKE AIRCRAFT.					1	L	7	1 	3O			NT	3A13 					 
1995022400007	19950224	00007	SO 	1995	2	24	95ZZZX822 	2	19950203	G	8530	652112	ROTOR COIL 			CESSNA	206 	U206G 	2073356	CE 	CONT 	O550 	IO550* 		SO 					EXH VALVE	WORN 	B			BFWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	5434X	717 				20605750	284519R			ROTO-COILS EXTREMELY WORN, AND ELONGATED. FOUND DURING TOP OVERHAUL OF ENGINE.						1	H	7	1 	3O	3	O		A4CE 	E3SO				 
1995022400008	19950224	00008	CE 	1995	2	24	95ZZZX823 	1	19950113	G	2410	01501240	BRACKET 		01501237 	BEECH 	35 	H35 	1151520	CE 										ALT MOUNT	FAILED 	B			OYSR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	8201D	354 			3068	D5288				ANNUAL INSPECTION FOUND ALTERNATOR MOUNT BRACKET HAD FAILED AND JAMBED AGAINST THE ALUMINUM MOUNT BLOCK CAUSING ALT. TO 	SHIFT ONLY SLIGHTLY. THIS PREVENTED FULL FAILURE AND ALLOWED THE AIRCRAFT TO REMAIN OPERATIONAL. AFTER A PERIOD OF APP	ROXIMATELY 100 HOURS OF HEAVY VIBRATION FROM A BAD PROPELLER, THE PILOT SQUAWKED ALTERNATOR BELT WOULD BE THROWN EVERY T	HIRTY OR SO HOURS. THIS FAILURE EXISTED FOR APPROXIMATELY 150 HOURS AND WAS MISSED BY AT LEAST TWO INSPECTIONS. THIS A	IRCRAFT HAD THE INTERAV MOD. KIT NR 1255A INSTALLED AND THESE BRACKETS CAN ONLY BE SEEN WITH A MIRROR INSPECTION.		1	L	7	1 	3O				3A15 					 
1995022400009	19950224	00009	EA 	1995	2	24	95ZZZX824 	2	19950112	G	7421	SR87	SPARKPLUG 			PIPER 	PA28 	PA28161 	7102803	SO 	LYC 	O320 	O320D3G 	41508	EA 					CENTER ELECTRODE	MELTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	8285B	600 				288116006	L999139A			WHEN REMOVING PLUGS FOR 100-HOUR INSPECTION, 2 PLUGS WERE FOUND WITH MELTED AND DEFORMED CENTER ELECTRODES. THERE WAS N	O EVIDENCE OF FOREIGN MATTER INSIDE OF CYLINDER. THIS CONDITION WAS NOTED ON ANOTHER PLUG IN ANOTHER PLANE AS WELL. SP	ARKPLUG MFG BY AUBURN.				1	L	7	1 	3O	3	O		2A13 	E274				 
1995022400010	19950224	00010	CE 	1995	2	24	95ZZZX825 	1	19950126	G	7160	714755	FLEX TUBE 			BBAVIA	8 	8KCAB 	2110612	CE 										AIR SCOOP BOX	MISINSTALLED 	B			GMZ2	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	111LS	17 				74095				DURING ENGINE MAINTENANCE, NOTED THAT UPON REINSTALLING THE LOWER ENGINE COWL THAT THE FLEX TUBE CAN BECOME FOLDED AND B	LOCK AIR FLOW TO THAT AIR SCOOP BOX AND FUEL INJECTOR. SUBMITTER RECOMMENDS REMOVAL OF AIR FILTER TO INSPECT FOR THIS C	ONDITION AFTER EACH COWLING INSTALLATION.				1	H	7	1 	3O				A21CE 					 
1995022400011	19950224	00011	CE 	1995	2	24	95ZZZX826 	1	19950118	G	5210	051180310	SKIN 			CESSNA	172 	172N 	2072434	CE 										DOOR RT	DELAMINATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	737YE	1493 				17269771				OUTER SKIN DELAMINATED FROM DOOR FRAME. LIGHT CORROSION FOUND IN UNBONDED AREA. LENGTH OF DELAMINATION IS 10 INCHES AN	D LOCATED ALONG BOTTOM EDGE NEAR LOWER CORNER OPPOSITE DOOR HINGE.					1	H	7	1 	3O			NT	3A12 					 
1995022400012	19950224	00012	CE 	1995	2	24	95ZZZX827 	1	19950207	G	7922	75944	VALVE 			BEECH 	76 	76 	1153005	CE 										THERMO BYPASS	LOOSE CRIMP NUT 	B			UC2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	3868N				121258	ME407				WHILE COMPLYING WITH LYCOMING SB 518, FOUND CRIMP NUT LOOSE DUE TO POOR DESIGN.						1	L	7	2 	3O				A29CE 					 
1995022400013	19950224	00013	SO 	1995	2	24	95ZZZX828 	1	19950209	G	3240		BRAKE 			GULSTM	AA5 	AA5B 	3960105	SO 										MLG	ICED UP 	B		A	MALR	O				OTHER 				O			OTHER 			LD	LANDING 	1			GL	15	81286					AA5B0484				AIRCRAFT TT 1,565.7. ON LANDING, FAILED TO KEEP ACFT ON RUNWAY AND ACFT WENT OFF RUNWAY INTO SNOW BANK DAMAGING LOWER E	NGINE COWL AND WHEEL FAIRINGS. UPON FURTHER INVESTIGATION, FOUND MAIN WHEEL FAIRINGS FULL OF COMPACTED SNOW. ACFT WAS 	THEN BROUGHT TO A HANGAR AND SNOW WAS MELTED OFF AND WHEEL PANTS REMOVED. FUNCTIONAL CHECK OF BRAKES AFTER THIS WAS PER	FORMED AND BRAKE OPERATION WAS FOUND SATISFACTORY. THE COLLECTION OF SNOW IN WHEEL FAIRINGS MELTED ON BRAKE PADS AND DI	SC AFTER TAKEOFF, THEN FROZE, CAUSING INEFFECTIVE BRAKES UPON NEXT LANDING.		1	L	7	1 	3O				A16EA 					 
1995022400014	19950224	00014		1995	2	24	95ZZZX829 	4	19950118	G	2562	ELT10	ELT 	NARCO 		BEECH 	55 	95A55 	1152704	CE 										CIRCUIT BOARD	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	363T				15130	TC416				THIS UNIT WAS REMOVED FOR INSPECTION PER 91.207(D) DURING ANNUAL INSPECTION. CORROSION (WHITE POWDER TYPE RESIDUE AROUN	D NEG. TERMINAL, BLUE RESIDUE INSIDE NEG. TERM.) WAS FOUND DURING INSPECTION OF CIRCUIT BOARD. UNIT WAS RECOND. AND CER	TIFIED BY MANUFACTURER ON 6-30-93 WITH OEM BATTERY INSTALLED. EXP. 5-29-95. NO LEAKAGE NOTED FROM BATTERY, POSSIBLE GA	SSING. BATTERY POTTING COMPOUND SEEMS LESS THAN NORMAL, NO 'SEALING' GREASE MATERIAL NOTED AT TRANSMITTER TO BATTERY PA	CK JOINT. UNIT RETURNED TO FACTORY FOR REPAIR - WARRANTY. ACFT IS ALWAYS HANGARED - FLYS REGULAR.		1	L	7	2 	3O				3A16 					 
1995040700322	19950407	00322	GL 	1995	4	7	95ZZZX830 	1	19950104	G	3222	11513001	STRUT 			AMTR 	WHEELR	WHELREXPRS 	05616ZC	GL 										NLG	BROKE 	H				O				OTHER 				O			OTHER 			LD	LANDING 	1			SW	99	93DE	95 				SUT604				NORMAL LANDING TO TOUCHDOWN WHEN STRUT BROKE AT WELD CAUSING FORK, SPINDLE AND WHEEL TO DEPART. AIRPLANE PROCEEDED TO D	ECELERATE ALONG RUNWAY RIDING ON REMAINING STRUT. REMAINING STRUT BROKE NEXT FOLLOWED BY RIDING ON GEAR STRUCTURE TIED 	TO ENGINE MOUNT AND FIREWALL (WHICH PREVENTED BODY DAMAGE). AS SPEED BLED OFF, BRAKED INTO SOD, OFF ASPHALT RUNWAY.				1	L	7	1 	3O			NT	EXPA1L71					 
1995022400015	19950224	00015	SO 	1995	2	24	95ZZZX831 	2	19950101	G	8520	631716	CRANKSHAFT 			CESSNA	188 	T188C 	2073012	CE 	CONT 	O520 	TSIO520T 	17040	SO 					FLANGE	HIGH RUNOUT 	B	L		YECR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	9560K	823 			B453M1	T18803958T	515405			ENGINE WAS DISASSEMBLED FOR REPAIR OF CRACKED CRANKCASE. INSPECTION OF CRANKSHAFT 631716 REVEALED HIGH RUN-OUT OF ALL M	EASUREMENT POINTS, BUT NO CRACKS. ENGINE HAS NO PROP STRIKE HISTORY. IT WAS ALSO NOTED THAT LARGE FLAKES OF NITRIDED M	ATERIAL HAD CHIPPED OFF THE REAR SIDE OF REAR COUNTERWEIGHT HANGER BLADES ADJACENT TO BUSHING HOLES. THERE WAS NO CORRE	SPONDING DAMAGE OF 639195 COUNTERWEIGHTS INDICATING DAMAGE HAD OCCURRED PRIOR TO ASSEMBLY AT FACTORY. THIS IS THE FOURT	H VAR CRANKSHAFT WITH HIGH RUNOUT THIS SUBMITTER HAS SEEN. NONE WERE CRACKED.		1	L	7	1 	3O	3	O		A9CE 	E8CE				 
1995022400018	19950224	00018	CE 	1995	2	24	95ZZZX834 	1	19950131	G	3297		WIRE 			CESSNA	500 	S550 	2076607	CE 										GEAR WARNING	CHAFED 	B		A	EBVR	O				OTHER 				N			FALSE WARNING 			NR	NOT REPORTED 	1			GL	09	138QS	3930 				S5500138				PILOT COMPLAINED OF INTERMITTENT GEAR UNSAFE INDICATION AND WARNING HORN. ALSO, ANTI-SKID WAS INOPERATIVE. FOUND WIRE 	BUNDLE IN THE LT WING TRAILING EDGE, JUST OUTBOARD OF THE INBOARD FLAP BELLCRANK HAD SHORTED AND BURNED. IT APPEARED TH	E SHRINK WRAP HAD CHAFED THROUGH TO THE BUNDLE AND SHORTED TO GROUND. REPAIRED WIRE BUNDLE.				1	L	7	2 	4F			RT	A22CE 					 
1995022400019	19950224	00019	WP 	1995	2	24	95ZZZX835 	1	19950207	G	6230	369A7013	UNIBALL 		369A70033 	HUGHES	369 	369D 	4470706	WP 										SWASHPLATE	WORN 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	31154	1718 				500716D				DURING BI-ANNUAL REGREASE OF M/R SWASHPLATE, DISCOVERED SWASHPLATE UNIBALL HAD EXCESSIVE AXIAL PLAY. M/R SWASHPLATE WAS 	REMOVED AND SENT FOR OVERHAUL.					1	G	7	1 	3U				H3WE 					 
1995022400020	19950224	00020	WP 	1995	2	24	95ZZZX836 	1	19950206	G	2820	369A8113	HOSE 			HUGHES	369 	369E 	4470707	WP 										START PUMP	LOOSE 	A		A		O				OTHER 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			SW	15	685F					0512E				CREWS DESCRIBED AN INTERMITTENT VIBRATION THAT COULD BE FELT THROUGHOUT THE AIRCRAFT DURING FLIGHT. ALSO, A HESITANT ST	ART AND A FLUCTUATING TOT INDICATION WAS SQUAWKED. AFTER FLYING OVER 2 HOURS AND BEING LOW IN FUEL, DUPLICATED ALL THRE	E PROBLEMS. DISCOVERED THESE PROBLEMS WOULD STOP WITH START PUMP ACTIVATED. WHILE INSPECTING THE FUEL SUPPLY SYSTEM, D	ISCOVERED THE FUEL SUPPLY HOSE ASSY FROM THE START PUMP TO THE FUEL SHUT-OFF VALVE WAS LOOSE AT THE VALVE. THIS ALLOWED	 AIR TO BE SUCKED INTO THE SYSTEM. REPLACED HOSE ASSY AND PROBLEMS HAVE NOT RECURRED.		1	G	7	1 	3U				H3WE 					 
1995022400021	19950224	00021	WP 	1995	2	24	95ZZZX837 	1	19950201	G	6320	369D25140	BEARING 		369025A00505	HUGHES	369 	369D 	4470706	WP 										M/R XMSN	MISINSTALLED 	B		A	EOOR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03	3115Y	7819 	1718 		6014	500716D				M/R TRANSMISSION INPUT ASSY WAS REMOVED TO CHANGE A LEAKY GARLOCK SEAL, NO AXIAL PLAY WAS NOTED. THE AXIAL PLAY SHOULD 	BE .009 INCH TO .015 INCH. REMOVED DUPLEX BEARING SET AND FOUND SPLIT RACES HAD BEEN SWITCHED WHEN IT HAD BEEN INSTALLE	D AT O/H. BRAZING WAS REPLACED AND THIS UNIT WAS SENT IN FOR OVERHAUL INSPECTION.				1	G	7	1 	3U				H3WE 					 
1995022400022	19950224	00022	SW 	1995	2	24	95ZZZX838 	1	19950129	G	5302	222035101101	CASTING 			BELL 	222 	222U 	1182140	SW 										TAILBOOM	WORKING 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	08	274SM					47537				DURING DAILY INSPECTION NOTED VERTICAL FIN WORKING AGAINST TAILBOOM CASTING.						1	G	7	2 	3U				H9SW 					 
1995022400321	19950224	00321	EA 	1995	2	24	95ZZZX869 	1	19950130	G	7333	912733	TRANSMITTER 			CNDAIR	CL600 	CL6001A11 	1900302	EA 										LT ENG FUEL FLOW	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	11	1045X	6572 			1119	1038				PERFORMING ENGINE FUEL TEMP TROUBLESHOOTING, NOTICED THE FUEL FLOW TRANSMITTER WAS CORRODED. IT WAS LATER REVEALED THE 	CORROSION WAS ACTUALLY BYPASSED FUEL BAKED ONTO THE ELECTRICAL JACK MOUNT. THE CANNON PLUG, GOING TO TRANSMITTER, WAS G	REATLY DETERIORATED AS WELL. REMOVED AND REPLACED THE FUEL FLOW TRANSMITTER AND ASSOCIATED ELECTRICAL CONNECTOR WITH SE	RVICEABLE PARTS. PERFORMED WIRE VERIFICATION AND ENGINE RUNS FOR LEAK CHECKS. RETURNED AIRCRAFT TO SERVICE.			2	L	7	2 	4F			RT	A21EA 					 
1995030300129	19950303	00129	WP 	1995	3	3	95ZZZX896 	1	19950207	G	6220	369D21011	BOOT 			HUGHES	369 	369D 	4470706	WP 										M/R HUB	TORN 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	3115Y					500716D				DURING ANNUAL INSPECTION, FOUND M/R HUB DUST BOOT RIPPED ALONG THE INSIDE PLEATS FOR ABOUT 120 DEGREES OF ARC ON 3 PLEAT	S. REPLACED BOOT WITH NEW.					1	G	7	1 	3U				H3WE 					 
1995030300130	19950303	00130	WP 	1995	3	3	95ZZZX897 	2	19950201	G	7321	30708008	FUEL CONTROL 			ISRAEL	1124 	1124 	4500102	EU 	GARRTT	TFE731	TFE7313 	01518	WP 					LT ENGINE	DEFECTIVE 	B			EBVR	O				OTHER 				O			OTHER 			AP	APPROACH 	1			GL	09	481NS				44553T	378				ENGINE WAS INSTALLED AFTER 4200 HOUR CORE INSPECTION. AFTER 2.6 HOURS OF OPERATION, THE PILOT EXPERIENCED SLUGGISH RESP	ONSE TO THROTTLE CHANGES. THIS WAS A PROBLEM IN TRAFFIC PATTERNS BECAUSE OF AIRCRAFT YAW WHEN POWER CHANGES RESULTED IN	 SLOW ENGINE RESPONSE. REPLACED ENGINE FUEL CONTROL AND PROBLEM WAS SOLVED.				2	M	7	2 	4F	4	F		A2SW 	E6WE				 
1995030300131	19950303	00131	SO 	1995	3	3	95ZZZX898 	1	19950131	G	2913		DRIVE SPLINE 			GULSTM	G159 	G159 	3952202	SO 										LT END HYD	WRONG PART 	B			EBVR	E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			W	J		INADEQUATE Q C 	WARNING INDICATION 		CR	CRUISE 	1			GL	09	2NA					96				AIRCRAFT WAS DEPARTING AFTER PAINT. ONE HOUR OUTBOUND, THE PILOT NOTED THE LT ENGINE GEARBOX OIL PRESSURE ANNUNCIATOR F	LICKERING. HE TURNED BACK, BUT HAD TO SHUT DOWN THE LT ENGINE BEFORE HE COULD LAND. INVESTIGATION FOUND THE LT ENG HYD	 PUMP HAD THE WRONG DRIVE SPLINE INSTALLED. DRY SPLINE SHAFT WAS INSTALLED IN A WET SPLINE. AIRCRAFT HAD COME FROM MAI	NTENANCE FOR PAINT.			2	L	7	2 	4T				1A17 					 
1995030300132	19950303	00132	EU 	1995	3	3	95ZZZX899 	1	19950206	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		287 			580					THIS STARTER/GENERATOR HAD EXCESSIVELY WORN BRUSHES. THE BRUSHES WERE WORN 70 PERCENT WITHIN 287.0 FLIGHT HOURS. SUBMI	TTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995030300133	19950303	00133	EU 	1995	3	3	95ZZZX900 	1	19950206	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		201 			210					THIS STARTER/GENERATOR HAD EXCESSIVELY WORN BRUSHES. THE BRUSHES WERE WORN 70 PERCENT WITHIN 201.0 FLIGHT HOURS. SUBMI	TTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995030300134	19950303	00134	EU 	1995	3	3	95ZZZX901 	1	19950206	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		286 			811					THIS STARTER/GENERATOR HAD EXCESSIVELY WORN BRUSHES. THE BRUSHES WERE WORN 80 PERCENT WITHIN 286.0 FLIGHT HOURS. SUBMI	TTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995030300135	19950303	00135	EU 	1995	3	3	95ZZZX902 	1	19950206	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		227 			1175					THIS STARTER/GENERATOR HAD EXCESSIVELY WORN BRUSHES. THE BRUSHES WERE WORN 80 PERCENT WITHIN 227.0 FLIGHT HOURS. SUBMI	TTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995030300136	19950303	00136	EU 	1995	3	3	95ZZZX903 	1	19950106	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B		A	XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		211 			1012					THIS STARTER/GENERATOR HAD EXCESSIVELY WORN BRUSHES. THE BRUSHES WERE WORN 70 PERCENT WITHIN 211.0 FLIGHT HOURS. SUBMI	TTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995030300138	19950303	00138	SW 	1995	3	3	95ZZZX905 	1	19950211	G	3230	755003	DRAG BRACE 			GULSTM	112 	114 	7630314	SW 										NLG	FAILED 	B			MJ7R	A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			GL	05	4998W	1808 				14318				ON TAKEOFF FROM LUK, PILOT HEARD A LOUD CRACK AT GEAR RETRACTION. NOSE GEAR WOULD NOT RETRACT. PILOT CYCLED GEAR DOWN 	AND LANDED WITHOUT INCIDENT. JACKED AIRCRAFT AND FOUND UPPER DRAG BRACE CRACKED. REPLACED WITH NEW UNIT.					1	L	7	1 	3O				A12SO 					 
1995030300139	19950303	00139	CE 	1995	3	3	95ZZZX906 	1	19950131	G	2842	034001001	PROBE 	GULL 		RKWELL	NA265 	NA26560 	7630106	CE 										AUX FUEL	CRACKED 	B	P		KI2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	8NR	6953 			341	306141				PILOTS REPORTED THAT FUEL QUANTITY INDICATION BECAME ERRATIC IN-FLIGHT. AFTER TROUBLESHOOTING AND PINPOINTING PROBLEM T	O BE AUXILIARY FUEL TANK PROBE, REMOVAL OF PROBE REVEALED THAT BARREL WAS CRACKED THE FULL CIRCUMFERENCE. CAUSE: EFFEC	T OF FUEL SLOSHING ON LONG LENGTH OF PROBE. RECOMMEND: VISUAL INSPECTION AT 5,000-HOUR INITIAL INTERVAL AND RECURRENT 	AROUND 2,500 HOURS.			2	L	7	2 	4J			RT	A2WE 					 
1995030300140	19950303	00140	CE 	1995	3	3	95ZZZX907 	1	19950208	G	3240	6517109201	BRAKE LINE 			CESSNA	500 	560CESSNA 	2076750	CE 										LT PARK	CHAFED 	B		A	JGVR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CE	09	96MT	1743 				5600032				BOLT HEAD ON BOTTOM OF PILOT'S CONTROL COLUMN CHAFED A HOLE IN THE LT PARK BRAKE LINE WHERE IT RUNS UNDER THE CONTROL CO	LUMN. LINE WAS POSITIONED WRONG AT THE FACTORY.					2	L	7	2 	4F			RT	A22CE 					 
1995030300141	19950303	00141	CE 	1995	3	3	95ZZZX908 	1	19950207	G	3240	620701182	LINE 			CESSNA	650 	650 	2076802	CE 										POWER BRAKE	CHAFED 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	673JS	1568 				6500073				POWER BRAKE METERING VALVE HYDRAULIC RETURN LINE RUNS CLOSE TO THE VALVES LOWER CONTROL ARM. THE CABLE ATTACH BOLT COTT	ER PIN MUST BE TRIMMED PROPERLY TO AVOID CONTACT WITH THE LINE.					2	L	7	2 	4F				A9NM 					 
1995030300142	19950303	00142	SW 	1995	3	3	95ZZZX909 	1	19950110	G	2434		ALTERNATOR 			MOONEY	M20 	M20K 	5870220	SW 										FIELD WIRE	INOPERATIVE 	B			AA4R	O				OTHER 				H			ELECT. POWER LOSS-50 PC 			CR	CRUISE 	1			WP	07	231RR					250072				ALTERNATOR OFF-LINE IN FLIGHT. PROBLEM TRACED TO BROKEN FIELD WIRE. FUNCTION CHECK OKAY AFTER REPAIRS.						1	L	7	1 	3O				2A3 					 
1995030300148	19950303	00148	CE 	1995	3	3	95ZZZX915 	1	19950101	G	7602	98620105	CONTROL CABLE 			CESSNA	172 	172N 	2072434	CE 										MIXTURE	DEFECTIVE 	B			DPOD	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	5426J	7449 				17273789				OUTSIDE HOUSING BROKE, NOT ALLOWING MIXTURE TO GO TO IDLE CUT OFF OR FULL RICH. SUSPECT CAUSE COLD TEMP (UNSURE).						1	H	7	1 	3O			NT	3A12 					 
1995030300149	19950303	00149	CE 	1995	3	3	95ZZZX916 	1	19950117	G	2810	35921155	FUEL CELL 			BEECH 	33 	35B33 	1151406	CE 										INTERNAL SIDES	DETERIORATED 	B			PW9R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	14586					CD463				INSIDE OF FUEL CELL COMING OFF INTO FUEL, BOTH SIDES. FOUND ON ROUTINE MAINTENANCE. FUEL STARVATION COULD OCCUR IN-FLI	GHT.					1	L	7	1 	3O				3A15 					 
1995030300150	19950303	00150	SO 	1995	3	3	95ZZZX917 	2	19950202	G	8540	643259	ADAPTER 			CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					SHAFT GEAR	SPALLED 	B			QY5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	1950G	332 				421B0649	267212R			INSPECTED THE STARTER ADAPTER SHAFT GEAR AND CRANKSHAFT GEAR ON BOTH ENGINES OF A CESSNA 421B IAW TCM SB CSB94-4. FOUND	 THE GEARS SPALLED AND PITTED BEYOND LIMITS. REPAIRED ENGINES BY INSTALLATION OF TCM KIT NR EQ6642. THE STARTER ADAPTE	R AND CRANKSHAFT GEARS THAT ARE SUPPLIED IN THIS KIT AND ON CURRENT PRODUCTION TCM GTSIO520 MODEL ENGINES UTILIZE AN IMP	ROVED TOOTH PROFILE.			1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995030300151	19950303	00151	SO 	1995	3	3	95ZZZX918 	2	19950202	G	8540	643259	ADAPTER 			CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					SHAFT GEAR	SPALLED 	B			QY5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	1950G	332 				421B0649	267213R			INSPECTED THE STARTER ADAPTER SHAFT GEAR AND CRANKSHAFT GEAR ON BOTH ENGINES OF A CESSNA 421B IAW TCM SB CSB94-4. FOUND	 THE GEARS SPALLED AND PITTED BEYOND LIMITS. REPAIRED ENGINES BY INSTALLATION OF TCM KIT NR EQ6642. THE STARTER ADAPTE	R AND CRANKSHAFT GEARS THAT ARE SUPPLIED IN THIS KIT AND ON CURRENT PRODUCTION TCM GTSIO520 MODEL ENGINES UTILIZE AN IMP	ROVED TOOTH PROFILE.			1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1995030300154	19950303	00154	EA 	1995	3	3	95ZZZX921 	2	19950207	G	8550	LW14729	DIPSTICK 			PIPER 	PA32 	PA32R301T 	7103220	SO 	LYC 	O540 	TIO540S1AD 	41532	EA 					ENGINE OIL	LOOSE 	B			IBIR	A				UNSCHED LANDING 				K			FLUID LOSS 			NR	NOT REPORTED 	1			EA	27	8463X					32R8229009	L799461A			AIRCRAFT MADE EMERGENCY LANDING DUE TO MASSIVE OIL LEAK FROM ENGINE. UPON LANDING, PILOT CHECKED THE ENGINE OIL AND STA	TED DIPSTICK SEEMED TO BE LOOSE. ACFT WAS MOVED INTO A HANGAR, THE COWLING REMOVED, AND THE ENGINE WASHED DOWN. INSPEC	TION REVEALED NO VISIBLE ENGINE DEFECTS. A BREATHER CHECK WAS PERFORMED AND FOUND SATISFACTORY.				1	L	7	1 	3O	3	O		A3SO 	E14EA				 
1995030300393	19950303	00393	GL 	1995	3	3	95ZZZX926 	3	19950206	G	6111	V8433N4	BLADE 			GULSTM	500 	500B 	0141106	SW 						HARTZL	HCA3V	HCA3VK2 	GL 	BLADE BUTT	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	6106X					94128		AA337		INSPECTION FOUND BLADE CRACKED. SUBMITTER STATED AD 68-19-04 SHOULD APPLY TO THESE BLADES ALSO.						1	H	7	2 	3O				6A1 		5	C	P6EA	 
1995030300394	19950303	00394	EA 	1995	3	3	95ZZZX927 	2	19950126	G	8530		VALVE 			DOUG 	DC3 	DC3C 	3021457	WP 	WRIGHT	R1820 	R1820* 	67020	EA 					NR 7 CYL EXH	BROKE 	E		A		E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			R	J		PARTIAL RPM/PWR LOSS 	WARNING INDICATION 		CL	CLIMB 	1			WP	13	99131	912 				18949	SW022927			APPROXIMATELY 10 MINUTES AFTER TAKEOFF A SLIGHT INTERRUPTION OF POWER WAS NOTED WHICH RETURNED IMMEDIATELY TO NORMAL. P	RESSURES AND TEMPS INDICATED AN INCREASE IN OIL TEMP AND A DECREASE IN OIL PRESSURE. ENGINE WAS FEATHERED AND RETURNED 	A/C TO HNL. EXAMINATION OF ENGINE INDICATED NR 7 CYLINDER EXHAUST VALVE HEAD BROKE. SCREENS INDICATED A SMALL AMOUNT O	F ALUMINUM.			2	L	7	2 	4R	4	R		A669 	5E10				 
1995030300395	19950303	00395	EU 	1995	3	3	95ZZZX928 	1	19950126	G	6120		CONTROL CABLE 			BNORM 	BN2 	BN2A26 	1520226	EU 										PROP CONTROL	BINDING 	D				O				OTHER 				O			OTHER 			IN	INSP/MAINT 	1			WP	13	26MR					882				WHILE PERFORMING A MAINTENANCE TEST FLIGHT FOR REPLACEMENT OF RIGHT ENGINE, PILOT PERFORMED AN IN-FLIGHT FEATHER CHECK,	 PROPELLER FEATHERED NORMALLY. ONCE CHECK COMPLETED, PILOT ATTEMPTED TO UN-FEATHER ENG; AT THAT TIME, HE DISCOVERED 'PR	OP CONTROL' TO BE BINDING. PILOT MADE SEVERAL ATTEMPTS TO MOVE 'PROP CONTROL' OUT OF FEATHER POSITION. WOULD NOT MOVE.	 ACFT LANDED WITH RT ENG FEATHERED. ONCE AIRCRAFT WAS ON THE GROUND, RIGHT 'PROP CONTROL' MOVED FREELY. MX INSPECTED 	RIGHT PROP CONTROL, FOUND WHEN IN-FLIGHT, LOWER COWLING COULD HAVE POSSIBLY CAUSED BONDING OF CONTROL. RE-ROUTED PROP C	ONTROL CABLE TO AVOID POSSIBLE IN-FLIGHT BINDING. ACFT TEST FLOWN AGAIN, NO FURTHER BINDING OF 'PROP CONTROL' CABLE.	1	H	7	2 	3O			 	A17EU 					 
1995030300396	19950303	00396		1995	3	3	95ZZZX929 	4	19950127	G	2312	KX165	TRANSCEIVER 	BENDIX 	51157 	CESSNA	402 	402C 	207590R	CE 										NAV-COM	INOPERATIVE 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	173VB	400 				402C1003				INOP OR FREQ 115.6 -- BRG POINTER AND ADI SCALLOP 20 DEGREES LEFT AND RIGHT EVEN AT 15 MILES FROM STATION. PROBLEM IS O	NLY ON FREQ 115.B. FREQS 112.3, 112.6, 116.0, 113.3 -- OKAY.					1	L	7	2 	3O				A7CE 					 
1995030300397	19950303	00397	CE 	1995	3	3	95ZZZX930 	1	19950126	G	5730		SKIN 			CESSNA	310 	T310R 	2074246	CE 										WING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	289WB	6406 				310R0817				THREE TO FOUR CRACKS FOUND IN WING SKINS ABOVE UPPER MAIN GEAR DRAG LINK ATTACH POINTS. CRACKS CAN BE SEEN BY LOOKING U	P THROUGH GEAR WELL OUTBOARD OF RIB.					1	L	7	2 	3O				3A10 					 
1995030300398	19950303	00398	SO 	1995	3	3	95ZZZX931 	1	19950211	G	2750	4009210	BELLCRANK 			PIPER 	PA18 	PA18A150 	7101837	SO 										RT WING FLAP	CRACKED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	3875P					184701				FLAP CONTROL BELLCRANK CRACKED AT POINT WHERE CONTROL ROD ATTACHES.						1	H	7	1 	3O				1A2 					 
1995030300399	19950303	00399	CE 	1995	3	3	95ZZZX932 	1	19950101	G	5712	16911000054	RIB 			BEECH 	23 	C23 	1151242	CE 										RT WING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	6014F					M2107				DURING A ROUTINE 100-HOUR INSPECTION, CRACKS WERE FOUND IN THE RIB AT THE AILERON HINGE DOUBLER.						1	L	7	1 	3O				A1CE 					 
1995030300400	19950303	00400	CE 	1995	3	3	95ZZZX933 	1	19950127	G	2720	24670011	RUDDER BAR 			CESSNA	172 	172RG 	2072438	CE 										RT RUD PEDAL	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	9520B	4725 				172RG0851				RUDDER BAR BROKEN IN HALF ADJACENT TO WELD THAT HOLDS STEERING BUNGEE BRACKET. THIS BAR HAS THE TWO RIGHT RUDDER PEDALS	 CONNECTED TO IT AND IS LOCATED IN THE REAR OF THE TWO RUDDER BARS. STRESS OF FACTORY WELD CAUSED CRACKING TO OCCUR WIT	H ULTIMATE FAILURE OF PART.				1	H	7	1 	3O				3A17 					 
1995030300401	19950303	00401	CE 	1995	3	3	95ZZZX934 	1	19950127	G	2720	031019612	SPRING 			CESSNA	172 	172 	2072402	CE 										RUDDER	BOGUS 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	01	6953A					29053				DURING ANNUAL INSPECTION WHILE RIGGING RUDDER CONTROL SYSTEM, DISCOVERED RUDDER RETURN SPRINGS SUBSTANTIALLY LIGHTER THA	N THE CORRECT SPRINGS. APPEARED TO BE AUTOMOTIVE THROTTLE RETURN SPRINGS. THE RIGGING PROCEDURE DOES NOT INCLUDE A CAB	LE TENSION SPEC MANDATING THE USE OF CORRECT SPRINGS FOR PROPER CABLE TENSION & CORRECT RUDDER & NOSEWHEEL STEERING RESP	ONSE. THE SPRINGS THAT WERE INSTALLED APPEARED OK UNTIL RIGGING WAS ATTEMPTED. UPON CLOSER INSP, DISCOVERED THE SPRING	S WERE INCORRECT. THE DIFFERENCE WAS ONLY NOTICEABLE WHEN SPRINGS WERE LOOKED AT SIDE-BY-SIDE. DECEPTIVE APPEARANCE OF	 THE BOGUS SPRINGS APPARENTLY FOOLED INSPECTORS FOR YEARS.	1	H	7	1 	3O			NT	3A12 					 
1995030300402	19950303	00402	CE 	1995	3	3	95ZZZX935 	1	19950127	G	2720	03101965	SPRING 			CESSNA	172 	172 	2072402	CE 										RUDDER	BOGUS 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	01	6953A					29053				DURING ANNUAL INSPECTION WHILE RIGGING RUDDER CONTROL SYSTEM, DISCOVERED RUDDER RETURN SPRINGS SUBSTANTIALLY LIGHTER THA	N THE CORRECT SPRINGS. APPEARED TO BE AUTOMOTIVE THROTTLE RETURN SPRINGS. THE RIGGING PROCEDURE DOES NOT INCLUDE A CAB	LE TENSION SPEC MANDATING THE USE OF CORRECT SPRINGS FOR PROPER CABLE TENSION & CORRECT RUDDER & NOSEWHEEL STEERING RESP	ONSE. THE SPRINGS THAT WERE INSTALLED APPEARED OK UNTIL RIGGING WAS ATTEMPTED. UPON CLOSER INSP, DISCOVERED THE SPRING	S WERE INCORRECT. THE DIFFERENCE WAS ONLY NOTICEABLE WHEN SPRINGS WERE LOOKED AT SIDE-BY-SIDE. DECEPTIVE APPEARANCE OF	 THE BOGUS SPRINGS APPARENTLY FOOLED INSPECTORS FOR YEARS.	1	H	7	1 	3O			NT	3A12 					 
1995030300403	19950303	00403	CE 	1995	3	3	95ZZZX936 	1	19950206	G	3231	08411066	IDLER BELLCRANK 			CESSNA	421 	421B 	2076014	CE 										INBD RT MLG DR	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	51RW	4576 				421B0900				POST-FLIGHT INSPECTION REVEALED INBOARD RIGHT MLG DOOR NOT RETRACTED. NOTED IDLER BELLCRANK BROKEN IN TWO. SUSPECT CRA	CK WAS DUE TO METAL FATIGUE FROM THE TENSION ON THE LINKAGE AND VIBRATION. INSPECTION OF GEAR REVEALED NO OTHER DEFECTS	.				1	L	7	2 	3O				A7CE 					 
1995030300405	19950303	00405	SO 	1995	3	3	95ZZZX938 	1	19950209	G	5730	62061004	SKIN 			PIPER 	PA28 	PA28180 	7102808	SO 										RT WING WALKSKIN	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	6356J	4100 				284767				UPPER SURFACE INBOARD, REAR REINFORCED WALK SKIN, RT WING. STIFFENER CRACKED AT OTBD ENDS OF FLUTES. SUSPECT FATIGUE A	ND EXCESSIVE WEIGHT ON WING WALK. SECOND AIRCRAFT WITH DEFECT IN FLEET 2ND. (TTAF 5300).					1	L	7	1 	3O				2A13 					 
1995030300406	19950303	00406	SO 	1995	3	3	95ZZZX939 	1	19950212	G	2133	2H3017	VALVE 	AIRBORNE 		PIPER 	PA31T 	PA31T 	7103124	SO 										PNEU PRESS	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	444RC	3750 			W10	31T7520030				THE A/C WAS NOT ABLE TO PRESSURIZE. ALSO, PNEUMATIC PRESS INDICATOR DID NOT INDICATE PRESSURE IN THE SYSTEM. TROUBLESH	OOTING FOUND PRESSURE REGULATING VALVE HAD SEPARATED INTO TWO SECTIONS. THIS SECTION (THE DIAPHRAGM) IS HELD TOGETHER W	ITH 6 RIVETS WHICH HAD FAILED. INSTALLED A NEW VALVE & A/C TEST FLOWN AND RETURNED TO SERVICE. NOTE: THE LOSS OF PNEU	MATIC PRESSURE CAUSED BY VALVE FAILURE - COULD HAVE BEEN A SERIOUS SYSTEM MALFUNCTION I.E., 'LOSS OF CABIN PRESSURE' AT 	ALTITUDE.		1	L	7	2 	3T				A8EA 					 
1995030300408	19950303	00408	CE 	1995	3	3	95ZZZX941 	1	19950209	G	7160	S12244	CONTROL CABLE 			CESSNA	172 	172F 	2072414	CE 										CARB HEAT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15	5249F	8333 				17253346				CARBURETOR HEAT CABLE IS A SPLIT CABLE. ONE PART CONTROLS FILTER AIR FLOW, OTHER PART CONTROLS HOT AIR, HOT AIR CABLE W	ORE THROUGH ALL THE WAY WHERE IT EXITS CABLE HOUSING. SUSPECT CAUSED BY CLAMP BEING LOOSE AND BEING IMPROPERLY ALIGNED.	 CABLE WAS IN GOOD SHAPE 35 HOURS BEFORE IT FAILED. THAT WAS THE TIME OF ENGINE INSTALLATION. SUBMITTER SUGGESTED GOO	D PREVENTION WOULD BE TO HAVE CABLE CLAMPED TIGHTLY AND ALIGNED PROPERLY. BECAUSE OF THE DUAL CABLE OPERATION, ONE PART	 CAN BE BROKEN AND STILL SHOW AN RPM DROP DURING THE RUN-UP.		1	H	7	1 	3O			NT	3A12 					 
1995030300409	19950303	00409	CE 	1995	3	3	95ZZZX942 	1	19950217	G	5753	052390114	BRACKET 			CESSNA	172 	172N 	2072434	CE 										FLAP TRACK	BOLT PULLED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	4822G					17273370				BOLT PULLED THROUGH BRACKET FOR RIGHT INBOARD FLAP ATTACHMENT. APPEARS TRACK WORN EXCESSIVELY AT BOLT HOLES. SUBMITTER	 SUGGESTED TRACK SHOULD BE CHECKED FOR WEAR.					1	H	7	1 	3O			NT	3A12 					 
1995030300410	19950303	00410	SO 	1995	3	3	95ZZZX943 	2	19950101	G	8530	652112	ROTO COIL 			CESSNA	206 	U206G 	2073356	CE 	CONT 	O550 	IO550* 		SO 					EXH INT VALVE	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	5343X	717 				U20605750	284519R			DURING TOP OVERHAUL, INSPECTION REVEALED WORN OUT EXHAUST AND INTAKE VALVE SPRING RETAINING ROTO-COILS.						1	H	7	1 	3O	3	O		A4CE 	E3SO				 
1995030300412	19950303	00412	SO 	1995	3	3	95ZZZX945 	1	19950207	G	2750	452645	ROD END 		850773 	PIPER 	PA46 	PA46350P 		SO 										LT FLAP	FAILED 	B		A	DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	89HS	1295 				4622033				PILOT REPORTED TO MAINTENANCE, THAT ON PRE-FLIGHT, WING FLAPS RETRACTED, LEFT FLAP COULD BE MOVED AFT BY HAND (UNNESTED	) ABOUT ONE INCH. INVESTIGATION REVEALED COMPLETE FAILURE OF, PN 452-645, ROD END AT OUTBOARD END OF LEFT PUSH ROD ASSY	, PN 8507703. ACTUAL LOCATIONS IN LEFT MLG WELL, AFT INBOARD CORNER WHERE ATTACHMENT TO INBOARD FLAP BELLCRANK OCCURS. 	 CAUSE OF FAILURE UNKNOWN. SUBMITTER STATED THIS CONDITION COULD DIRECTLY LEAD TO SUDDEN ASYMMETRICAL FLAPS AND LESS OF	 CONTROL OF AIRCRAFT.		1	L	7	1 	3O			RT	A25SO 					 
1995030300413	19950303	00413	GL 	1995	3	3	95ZZZX946 	3	19950214	G	6114		HUB 			BEECH 	33 	35C33 	1151408	CE 						MCAULY	3A32C	3A32C76 	GL 	SOCKET	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	5827S		519 			CD815		781492		PROPELLER IN FOR 5 YEAR TBO FOUND DURING OHC. FOUND HUB CRACKED.						1	L	7	1 	3O				3A15 		5	C	P21EA	 
1995030300414	19950303	00414	SO 	1995	3	3	95ZZZX947 	1	19950209	G	5730		SKIN 			AMRGEN	AG5B 	AG5B 	3990100	SO 										RT WING TOP	DEBONDED 	B			AWKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	1197Z					10023				DEBONDING OF WING RIB FROM WING SKIN FOUND DURING TROUBLESHOOTING FOR A FUEL LEAK IN LT WING FUEL TANK. TOP SIDE DEBOND	ING AT RT WING, STA WS 161.25, ONE PLACE 2 INCHES LONG. WS 112.5, TWO PLACES 3 AND 11 INCHES LONG. WS 97, TWO PLACES 3	 AND 14 INCHES LONG. WS 49.5, ONE PLACE 3 INCHES LONG.				1	L	7	1 	3O			NT	1L71 					 
1995030300415	19950303	00415	SO 	1995	3	3	95ZZZX948 	1	19950209	G	5730		SKIN 			AMRGEN	AG5B 	AG5B 	3990100	SO 										RT WING BOTTOM	DEBONDED 	B			AWKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	1197Z					10023				DEBONDING OF WING RIB FROM WING SKIN FOUND DURING TROUBLESHOOTING FOR A FUEL LEAK IN LEFT WING FUEL TANK. BOTTOM SIDE D	EBONDING AT RT WING WS 161.25, ONE PLACE 9 INCHES LONG. WS 145.25, ONE PLACE 4 INCHES LONG. WS 112.5, TWO PLACES 4 INC	HES LONG. WS 97, TWO PLACES 4 INCHES LONG. WS 66, ONE PLACE 3 INCHES LONG.				1	L	7	1 	3O			NT	1L71 					 
1995030300416	19950303	00416	SO 	1995	3	3	95ZZZX949 	1	19950209	G	5730		SKIN 			AMRGEN	AG5B 	AG5B 	3990100	SO 										LT WING TOP	DEBONDED 	B	S		AWKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	1197Z					10023				DEBONDING OF WING RIB FROM WING SKIN FOUND DURING TROUBLESHOOTING FROM A FUEL LEAK IN LT WING FUEL TANK. TOP SIDE DEBON	DING AT LT WING, STA WS 49.5, TWO PLACES 13 AND 10 INCHES LONG. WS 66, ONE PLACE 38 INCHES LONG. WS 97, ONE PLACE 3 INC	HES LONG. WS 112.5, ONE PLACE 2.75 INCHES LONG. WS 145.25, ONE PLACE 2 INCHES LONG. WS 161.25, ONE PLACE 3 INCHES LON	G.			1	L	7	1 	3O			NT	1L71 					 
1995030300417	19950303	00417	SO 	1995	3	3	95ZZZX950 	1	19950209	G	5730		SKIN 			AMRGEN	AG5B 	AG5B 	3990100	SO 										LT WING BOTTOM	DEBONDED 	B	S		AWKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	1197Z					10023				DEBONDING OF WING RIB FROM WING SKIN FOUND DURING TROUBLESHOOTING FROM A FUEL LEAK IN LT WING FUEL TANK. BOTTOM SIDE DE	BONDING AT LT WING STA WS 97, ONE PLACE 3 INCHES LONG. WS 112.5, ONE PLACE 3 INCHES LONG.					1	L	7	1 	3O			NT	1L71 					 
1995030300418	19950303	00418	CE 	1995	3	3	95ZZZX951 	1	19950207	G	2510	04140451	BRACKET 			CESSNA	150 	150M 	2071830	CE 										CENTER SEAT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	9166U	3420 				15078117				DURING AN ANNUAL INSPECTION, SIGNS OF CORROSION WERE NOTICED AT THE BASE OF THE CENTER SEAT BELT ATTACH BRACKET. UPON R	EMOVAL OF BRACKET, FOUND BOTH THE BOTTOM OF THE BRACKET AND THE ALUMINUM STRUCTURE HAD EXTENSIVE AMOUNTS OF CORROSION. T	HIS CORROSION IS A RESULT OF A STEEL BRACKET FASTENED DIRECTLY TO THE ALUMINUM STRUCTURE. WITH THE ADDITION OF MOISTURE	 IN THE AREA, THE CORROSION INTENSIFIES. THIS BRACKET SHOULD BE REMOVED, CORROSION TREATED, THE BRACKET PAINTED AND RE-	INSTALLED. RE-INSPECTION AT 100-HOUR INTERVALS IS SUGGESTED.		1	H	7	1 	3O				3A19 					 
1995030300419	19950303	00419	SO 	1995	3	3	95ZZZX952 	2	19950120	G	8530	24044	RETAINER 		641917 	UNIVAC	GC1 	GC1B 	9230104	NM 	CONT 	O300 	O300A 	17022	SO 					NR 2 CYL EXH VLV	MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	2420B	40 				3720	16110DR			DISASSEMBLY OF THE CYLINDER DISCLOSED A MISSING RETAINER FOR THE EXHAUST VALVE SPRING. WEAR INTO THE ALUMINUM HEAD WAS 	NOTED. 'NR 2 CYLINDER'.					1	L	7	1 	3O	3	O		A766 	E253				 
1995030300420	19950303	00420	SO 	1995	3	3	95ZZZX953 	1	19950221	G	3233	451826	ACTUATOR 			PIPER 	PA31 	PA31310 	7103103	SO 										MLG	NUT LOOSE 	D				A				UNSCHED LANDING 				J			WARNING INDICATION 			CL	CLIMB 	1			SW	99	27337					3186				AIRCRAFT RETURNED TO BASE AFTER GEAR FAILED TO RETRACT. MAINTENANCE DISCOVERED JAM NUT ON MLG ACTUATOR HAD LOOSENED ALL	OWING ROD END TO MOVE IN RELATION TO ACTUATOR, THUS, PREVENTING THE GEAR FROM ENGAGING ON THE UPLOCK AS ACTUATOR DID NOT	 HAVE SUFFICIENT TRAVEL. SAFETY WIRE WAS STILL ON NUT, BUT HAD SEPARATED FROM ROD END. NUT PN 404528.				1	L	7	1 	3O			RT	A20SO 					 
1995030300421	19950303	00421	SO 	1995	3	3	95ZZZX954 	2	19950127	G	8520	6419311075	BOLT 			BEECH 	33 	G33 	1151435	CE 	CONT 	O520 	IO520BB 	17032	SO 					NR 2 CYLINDER	BROKEN 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	09	1740W	129 				CD1302	285662R			DURING ROUTINE MAINTENANCE, AN OIL LEAK WAS NOTED BETWEEN THE NR 2 CYLINDER AND THE OIL COOLER. FURTHER INSPECTION REVE	ALED LOWER AFT THROUGH-BOLT BROKEN APPROXIMATELY ONE-THIRD ITS LENGTH. REPLACEMENT BOLT WAS A SLIGHTLY DIFFERENT DESIGN	. ENGINE TIME SINCE FACTORY REBUILD, 128.64.				1	L	7	1 	3O	3	O		3A15 	E5CE				 
1995030300422	19950303	00422	SO 	1995	3	3	95ZZZX955 	1	19950201	G	7920	1776699	LINE 			PIPER 	PA31 	PA31350 	7103110	SO 										OIL PRESS	LOOSE 	D		A		A				UNSCHED LANDING 				K			FLUID LOSS 			CR	CRUISE 	1			SW	99	146DC					317305016				AFTER 10 MINUTES OF FLIGHT, PILOT NOTICED OIL ON COPILOT'S SCUFF PLATE AND RETURNED TO BASE. MAINTENANCE DISCOVERED OIL	 HOSE HAD A HOLE IN IT. SCREW ON CLAMP ON HOSE HAD BACKED OUT OF STRUCTURE FREEING HOSE TO RUB OFF ADJACENT HOSE. THIS	 AREA IS HARD TO INSPECT, BUT A ONE-TIME CHECK TO SEE HOSES ARE CORRECTLY ROUTED AND CLAMPED SHOULD PREVENT THIS FROM HA	PPENING.			1	L	7	2 	3O				A20SO 					 
1995030300423	19950303	00423	SO 	1995	3	3	95ZZZX956 	2	19950120	G	7414	1057441	IMPULSE COUPLING	BENDIX 	S6LN21 	BEECH 	35 	F35 	1151514	CE 	CONT 	E225 	E2258 	17015	SO 					BORE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	3376C	800 			8410	D4043				DURING INSPECTION OF IMPULSE COUPLING, I.E., AD 78-09-07R3, NUT WAS LOOSE DUE TO CRACK IN BORE OF IMPULSE COUPLING. TCM	 BENDIX SB 639 REFERS TO INSTALLATION OF COUPLINGS. AD 78-09-07R3 DOES NOT REQUIRE REMOVAL OF COUPLING FOR INSPECTION. 	 MAYBE IT SHOULD TO DETECT CRACKS IN BORE OF COUPLING. BOTH MAGS AND IMPULSES REPLACED WITH REBUILT TCM UNITS.				1	L	7	1 	3O	3	O		A777 	E267				 
1995030300424	19950303	00424	CE 	1995	3	3	95ZZZX957 	1	19950206	G	7603	556580315	RETURN SPRING 			CESSNA	500 	560CESSNA 	2076750	CE 										POWER LEVER	BROKEN 	B		A	OL1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	172CV	1387 	1019 			5600172				AIRCRAFT PREPARING FOR TRIP, ENGINES RUNNING ON RAMP. WHEN POWER LEVERS WERE ADVANCED AND BROUGHT BACK TO IDLE, NR 1 EN	GINE UNEXPECTEDLY SHUT DOWN. FOUND POWER LEVER LOCKING TAB RETURN SPRING BROKEN ALLOWING POWER LEVER TO GO TO CUT OFF W	HEN IDLE POSTION WAS SELECTED. NORMALLY, THIS TAB IS LIFTED MANUALLY WHEN CUT-OFF POSITION IS DESIRED.				2	L	7	2 	4F			RT	A22CE 					 
1995030300425	19950303	00425	SO 	1995	3	3	95ZZZX958 	1	19950127	G	5741		FITTING 			PIPER 	PA28 	PA28181 	7102807	SO 										WING ATTACH	RUSTED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	2204Q	3197 				287790381				IN COMPLYING WITH PIPER SB 977, BOTH FORWARD AS WELL AS THE AFT WING ATTACH FITTINGS WERE FOUND SEVERELY RUSTED. THE BR	ACKETS FOR THE ATTACHMENT OF THE FORWARD SEAT BELTS WERE FOUND IN THE SAME CONDITION. AT THE FORWARD UPPER FUSELAGE FIT	TINGS AT STA 73, REAR CORNERS OF WINDOWS HAD TO BE REPLACED DUE TO THE EXTENT OF RUST. SUBMITTER RECOMMENDATION WOULD B	E TO EXTEND THE SCOPE OF THE SB TO ENCOMPASS ALL STEEL FITTINGS. ALSO, THE REMOVAL OF THE FIBERGLASS INSULATION AND THE	 INSTALLATION OF FOAM INSULATION (SIMILAR TO MOONEY SB).		1	L	7	1 	3O				2A13 					 
1995030300426	19950303	00426	SO 	1995	3	3	95ZZZX959 	1	19950127	G	5320		FITTING 			PIPER 	PA28 	PA28181 	7102807	SO 										FS 73	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	2204Q	3197 				287790381				IN COMPLYING WITH PIPER SB 977, BOTH FORWARD AS WELL AS THE AFT WING ATTACH FITTINGS WERE FOUND SEVERELY RUSTED. THE BR	ACKETS FOR THE ATTACHMENT OF THE FORWARD SEAT BELTS WERE FOUND IN THE SAME CONDITION. AT THE FORWARD UPPER FUSELAGE FIT	TINGS AT STA 73, REAR CORNERS OF WINDOWS HAD TO BE REPLACED DUE TO THE EXTENT OF RUST. SUBMITTER RECOMMENDATION WOULD B	E TO EXTEND THE SCOPE OF THE SB TO ENCOMPASS ALL STEEL FITTINGS. ALSO, THE REMOVAL OF THE FIBERGLASS INSULATION AND THE	 INSTALLATION OF FOAM INSULATION (SIMILAR TO MOONEY SB).		1	L	7	1 	3O				2A13 					 
1995030300427	19950303	00427	SO 	1995	3	3	95ZZZX960 	1	19950127	G	2510		BRACKET 			PIPER 	PA28 	PA28181 	7102807	SO 										FWD SEAT BELT	RUSTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	2204Q	3197 				287790381				IN COMPLYING WITH PIPER SB 977, BOTH FORWARD AS WELL AS THE AFT WING ATTACH FITTINGS WERE FOUND SEVERELY RUSTED. THE BR	ACKETS FOR THE ATTACHMENT OF THE FORWARD SEAT BELTS WERE FOUND IN THE SAME CONDITION. AT THE FORWARD UPPER FUSELAGE FIT	TINGS AT STA 73, REAR CORNERS OF WINDOWS HAD TO BE REPLACED DUE TO THE EXTENT OF RUST. SUBMITTER RECOMMENDATION WOULD B	E TO EXTEND THE SCOPE OF THE SB TO ENCOMPASS ALL STEEL FITTINGS. ALSO, THE REMOVAL OF THE FIBERGLASS INSULATION AND THE	 INSTALLATION OF FOAM INSULATION (SIMILAR TO MOONEY SB).		1	L	7	1 	3O				2A13 					 
1995030300428	19950303	00428	CE 	1995	3	3	95ZZZX961 	1	19950208	G	2750	051010593	CONTROL CABLE 			CESSNA	172 	172N 	2072434	CE 										INBD FLAP MOTOR	FAILED 	H				O				OTHER 				F			FLT CONT AFFECTED 			CR	CRUISE 	1			EA	23	5422E					17271853				CABLE SNAPPED IN FLIGHT. LOUD BANG, A/C ROLLED LEFT. CORRECTED AND LANDED. VFLE SHOULD BE ADHERED TO AT ALL TIMES. N	O SIGN OF CORROSION OR ABRASION. EIGHT OCCURRENCES BY THIS MECHANIC OF BREAKAGE AT THIS SPOT IN SYSTEM.					1	H	7	1 	3O			NT	3A12 					 
1995030300429	19950303	00429	EA 	1995	3	3	95ZZZX962 	2	19950127	G	7322	HA6IC5	CARBURETOR 			CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540J3C5 	41532	EA 					ACCELERATOR	PUMP BINDING 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	01	5482T	23 			75036815	R18201877	L2162940A			CARBURETOR ACCELERATOR PUMP STICKING OR BINDING CAUSING EXTREMELY DIFFICULT THROTTLE OPERATION. THIS WAS A FACTORY REMA	NUFACTURED ENGINE WITH A NEW CARBURETOR. TIME IN SERVICE IS 23.0 HOURS. THIS HAS OCCURRED ONCE BEFORE ON THE SAME MODE	L CARBURETOR, ON A DIFFERENT ENGINE AND AIRCRAFT. SUBMITTER RECOMMENDS INSPECTING ACCELERATOR PUMP AND THROTTLE SHAFT F	OR FREEDOM OF MOVEMENT AND PROPER TRAVEL BEFORE INSTALLATION.			1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1995030300430	19950303	00430	EA 	1995	3	3	95ZZZX963 	2	19950201	G	7414	S6LN	MAGNETO 			PIPER 	PA31 	PA31310 	7103103	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					LT MAG	SEPARATED 	D				A				UNSCHED LANDING 				K	B		FLUID LOSS 	SMOKE/FUMES/ODORS/SPARKS 		NR	NOT REPORTED 	1			SW	99	27337		14 		8220066	3186	L160061			PILOT RETURNED TO BASE AFTER NOTICING SMOKE FROM LEFT ENGINE SOON AFTER TAKEOFF. MAINTENANCE DISCOVERED LT MAGNETO HAD 	SEPARATED FROM ENGINE CAUSING OIL LEAK AND SMOKE. REASON FOR MAGNETO SEPARATION IS UNKNOWN. NEW NUTS AND LOCKWASHERS H	AD BEEN USED DURING INSTALLATION, AND STUDS ARE IN A GOOD CONDITION.				1	L	7	1 	3O	3	O	RT	A20SO 	E14EA				 
1995030300431	19950303	00431	CE 	1995	3	3	95ZZZX964 	1	19950212	G	2810		CAP 			CESSNA	182 	182M 	2072728	CE 										FUEL TANK	SEAL FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	70920	2350 				18259420				OLD STYLE CESSNA PLASTIC FUEL CAPS - SEALS ARE NOT AVAILABLE ANYMORE.						1	H	7	1 	3O			NT	3A13 					 
1995030300432	19950303	00432	SO 	1995	3	3	95ZZZX965 	2	19950207	G	7414	10357281	CAPACITOR 		101630601 	CESSNA	310 	T310R 	2074246	CE 	CONT 	O520 	TSIO520B 	17040	SO 					RT ENG, RT MAG	FAILED 	B			AHTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	5094C	466 			9324	310R1417	RT176631R			DURING ENGINE RUN-UP FOR A ROUTINE 50-HOUR INSPECTION, THE MECHANIC NOTED THE RIGHT ENGINE, RIGHT MAGNETO DID NOT RESPON	D TO THE IGNITION SWITCH. FURTHER INVESTIGATION REVEALED THE MAGNETO CAPACITOR TO BE FAULTY. AFTER REPLACING THE CAPAC	ITOR, THE MAGNETO OPERATION CHECKED NORMAL. NOTE: THIS IS THE SAME CONDITION THAT AD 94-06-09 PERTAINED TO, EXCEPT THE	 AD DOES NOT APPLY TO THIS CAPACITOR PART NUMBER OR DATE CODE. SUBMITTER STATED THIS CONDITION COULD CAUSE INJURY OR DE	ATH.		1	L	7	2 	3O	3	O		3A10 	E8CE				 
1995030300433	19950303	00433	CE 	1995	3	3	95ZZZX966 	1	19950213	G	7430		SWITCH 			BBAVIA	8 	8KCAB 	2110612	CE 										COCKPIT MAG	MISWIRED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	7JB					72794				AMERICAN CHAMPION AIRCRAFT, SUPER DECATHLON, FEB 94 MODEL. LEFT AND RIGHT MAGNETO WIRES FOUND INSTALLED ON INCORRECT SW	ITCH IN COCKPIT. LEFT WIRE FOUND LOOSE ON SWITCH. A/C TT 27.0 HRS.					1	H	7	1 	3O				A21CE 					 
1995030300435	19950303	00435	SO 	1995	3	3	95ZZZX968 	1	19950126	G	3222	45314000	CYLINDER ASSY 			PIPER 	PA31 	PA31350 	7103110	SO 										NLG STRUT	HOLES STRIPPED 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	27594	11500				317852070				DURING ANNUAL INSPECTION, FOUND THREE AN3H-7A BOLTS WHICH SECURE THE NOSE GEAR STEERING ARM ASSY TO THE OLEO CYLINDER LO	OSE. FURTHER INSPECTION SHOWED TWO OF THE HOLES IN THE CYLINDER WERE STRIPPED. SAFETY WIRE WAS INTACT. SUSPECT CAUSE 	AS INSUFFICIENT DESIGN.				1	L	7	2 	3O				A20SO 					 
1995030300436	19950303	00436	SW 	1995	3	3	95ZZZX969 	1	19950208	G	5320	3501124	STIFFENER 			MOONEY	M20 	M20C 	5870208	SW 										FUSELAGE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	6902U	2296 				2697				OWNER BROUGHT ACFT IN FOR LONGERON AND STIFFENER REPLACEMENT. FOUND EXISTING LONGERONS WITH EXTREME INTERGRANULAR CORRO	SION AND EXFOLIATION. SUBMITTER SUGGESTED THESE SHOULD BE INSPECTED CLOSELY ON TOP AND BOTTOM AT EACH ANNUAL INSPECTION	. IF CORROSION IS FOUND, REPLACE PARTS. APPROXIMATELY 10-15 HOURS LABOR FOR EACH.				1	L	7	1 	3O				2A3 					 
1995030300437	19950303	00437	SW 	1995	3	3	95ZZZX970 	1	19950208	G	5313	3501123	LONGERON 			MOONEY	M20 	M20C 	5870208	SW 										FUSELAGE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	15	6902U	2296 				2697				OWNER BROUGHT ACFT IN FOR LONGERON AND STIFFENER REPLACEMENT. FOUND EXISTING LONGERONS WITH EXTREME INTERGRANULAR CORRO	SION AND EXFOLIATION. SUBMITTER SUGGESTED THESE SHOULD BE INSPECTED CLOSELY ON TOP AND BOTTOM AT EACH ANNUAL INSPECTION	. IF CORROSION IS FOUND, REPLACE PARTS. APPROXIMATELY 10-15 HOURS LABOR FOR EACH.				1	L	7	1 	3O				2A3 					 
1995030300438	19950303	00438	CE 	1995	3	3	95ZZZX971 	1	19950119	G	3230	23421061	CENTERING CAM 			LEAR 	35 	36A 	5170603	CE 										NLG	CORRODED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	17A	3746 				046				DURING NLG STRUT RESEALING, THE LOWER CENTERING CAM WAS FOUND UNSERVICEABLE DUE TO CORROSION. FIFTY PERCENT OF THE FLAN	GE SEPARATING THE FELT WIPER AND THE SCRAPER RING WAS CORRODED AWAY. THE REPLACEMENT PART IS 2342106-2 AND HAS A LIGHT 	GREEN ANODIZING. THE ORIGINAL PART HAS A LIGHT GRAY ANODIZING.				2	L	7	2 	4F				A10CE 					 
1995030300439	19950303	00439	CE 	1995	3	3	95ZZZX972 	1	19950201	G	2730	115610010325	TORQUE TUBE 			BEECH 	100 	B100 	1152919	CE 										MT BRACKET	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	93SF					BE13				TORQUE TUBE MOUNT BRACKET WAS CRACKED FROM TAPER PIN HOSE (HEAD SIDE) TO THE END OF PART. TAPER PIN MIGHT HAVE BEEN OVE	RTORQUED.					1	L	7	2 	4T				A14CE 					 
1995030300440	19950303	00440	CE 	1995	3	3	95ZZZX973 	1	19950202	G	3240	65171082	COUPLING 			CESSNA	525 	525 	2076601	CE 										POWER BRAKE	FAILED 	B			ERY2	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	20FL	175 				5250069				PILOTS REPORTED ANTI-SKID AND POWER BRAKES FAILED. FOUND POWER BRAKE MOTOR TO PUMP COUPLING HAD FAILED. REASON UNKNOWN	. REPLACED COUPLING WITH NEW UNIT. OPS CHECK GOOD. AIRCRAFT RETURNED TO SERVICE. AIRCRAFT TOTAL TIME 175.4. AIRCRAF	T TOTAL LANDINGS 293.				1	L	7	2 	4F			RT	A1WI 					 
1995030300441	19950303	00441	NE 	1995	3	3	95ZZZX974 	2	19950123	G	7230	778487	MODULE 			DOUG 	DC9 	DC981 	3022081	WP 	PWA 	JT8 	JT8D217A 	52053	NE 					6TH-7TH STAGES	BLADE DAMAGE 	B		A	ASTY	A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			SO	23	10022	5383 				48024	P696930D			FLT 410 - DURING FLIGHT, PILOT REPORTED A BANG ON NR 2 ENGINE. PILOT REDUCED POWER AND MADE A QRF. LANDING PERFORMED W	ITHOUT INCIDENTS. AT THE BASE, ENGINE WAS BORESCOPED BEFORE ANY ATTEMPT TO RESTART. DAMAGE FOUND ON 6TH, 7TH, AND 13TH	 STAGES COMPRESSOR GROUPS BLADES. DEBRIS IMPACTED ON TURBINE STAGES AND MIXER WITHOUT MAJOR DAMAGE. ENGINE WAS REPLACE	D, GROUND TEST PERFORMED SUCCESSFULLY. ACFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F		A6WE 	E9NE				 
1995030300442	19950303	00442	CE 	1995	3	3	95ZZZX975 	1	19950203	G	7120		MOUNT PAD 			CESSNA	500 	550 	2076604	CE 										ENGINE	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	24RF	3216 				550456				FOUND CORROSION ON ENGINE MOUNT BOSS AND AREA ON ENGINE, DURING SCHEDULED INSPECTION. PRATT AND WHITNEY WAS INFORMED, G	AVE OKAY TO CLEAN, TREAT, AND REINSTALL ENGINE MOUNTS.					1	L	7	2 	4F				A22CE 					 
1995030300592	19950303	00592	NE 	1995	3	3	95ZZZX981 	2	19950206	G	7210	7757571	BEARING 	HAMSTD 	77580010 	SAAB 	SF340 	340B 	7860101	EU 	GE 	CT7TP 	CT79B 	30030	NE 					GC 49 GEARCASE	CRACKED 	B	S		SI3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	174AE	7018 			9138	340B174				THE GEARCASE WAS RETURNED FOR 'MAKING METAL'. THE UNIT WAS DISASSEMBLED. EXAMINATION OF INTERNAL HARDWARE REVEALED A C	RACKED INNER BEARING RACE ON THE PROPELLER SHAFT FORWARD ROLLER BEARING. REF. CMM 72-11-02.					2	L	7	2 	4T	4	T	RT	A52EU 	E8NE				 
1995030300593	19950303	00593	NE 	1995	3	3	95ZZZX982 	2	19950119	G	7530	6927221	COTTER PIN 	HAMSTD 	EVC32 	BOEING	747 	747* 		NM 	PWA 	JT9 	JT9* 	52054	NE 					ENG VANE CONTROL	MISSING 	B	S	A	SI3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03					75363	677				UPON DISASSEMBLY FOR OVERHAUL IT WAS OBSERVED THAT COTTER PIN, REF. CMM 75-31-01, FIGURE 2, ITEM 49, AND SHIM, FIGURE 2,	 ITEM 50, WERE NOT INSTALLED. NOTE: HEADED STRAIGHT PIN, FIGURE 2, ITEM 51, REMAINED IN INSTALLED POSITION. NOTE 2: L	AST REPAIR PERFORMED BY ANOTHER AGENCY.				2	L	7	4 	4F	4	F	RT	A20WE 	E20EA				 
1995030300594	19950303	00594	NE 	1995	3	3	95ZZZX983 	2	19950206	G	7210	7757535	IDLER GEAR 	HAMSTD 	77580010 	SAAB 	SF340 	340B 	7860101	EU 	GE 	CT7TP 	CT79B 	30030	NE 					GC 49 GEARCASE	FAILURE 	B	S		SI3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	201AE	8129 			1C6412310	340B201				THE UNIT WAS REMOVED FROM THE AIRCRAFT DUE TO A LT IDLER GEAR FAILURE. THE FAILED GEAR BROKE THROUGH THE GEAR CASE HOUS	ING. DISASSEMBLY OF THE UNIT REVEALED THE IDLER GEAR WEB HAD FAILED. ALSO, OBSERVED WAS BROKEN DAMPER RINGS, BROKEN RE	TAINING RINGS AND A BROKEN SLIDER BLOCK HOUSING. REF. CMM 72-11-02.				2	L	7	2 	4T	4	T	RT	A52EU 	E8NE				 
1995030300597	19950303	00597	SO 	1995	3	3	95ZZZX986 	1	19950227	G	7922	53E19600	BYPASS VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										OIL COOL LT ENG	NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	27910	1568 				317952044				NUT LOOSE. CHECKED PER SB NR 518A (LYCOMING).						1	L	7	2 	3O				A20SO 					 
1995030300600	19950303	00600	SO 	1995	3	3	95ZZZX989 	3	19950214	G	6111		ROD END BEARING 			BEECH 	33 	35B33 	1151406	CE 						FLTORP	F12	F12A5 	SO 	PITCH CHANGE	NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	9737Y		855 			CD604		2121		PROPELLER PITCH CHANGE THROUGH-LINKS AND ROD-END BEARINGS. INSPECTION FOUND NUT LOOSE ON STUD HOLDING ROD-END BEARING. 	 NUT HAD DEFECTIVE SELF-LOCKING FEATURE. A FIX WAS DONE BY USING STEEL LOCK NUTS WITH LOCK-TITE. ALSO, NO SAFETY WASHE	RS WERE USED ON THOSE ROD-ENDS. SUBMITTER FEELS SAFETY WASHERS SHOULD BE ADDED.				1	L	7	1 	3O				3A15 		5	C	P902	 
1995030300605	19950303	00605	CE 	1995	3	3	95ZZZX994 	1	19950220	G	3231	S217840120	HOSE 			CESSNA	210 	P210N 	2073454	CE 										NLG DR ACTUATOR	FAILED 	D				O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			GL	05	3549D	2937 				21000029				PILOT REPORTED NO DOWN AND LOCKED INDICATION. PILOT FLEW BY TOWER AND ALL THREE GEARS APPEARED DOWN AND LOCKED, BUT GEA	R DOORS WERE NOT FULLY CLOSED. THE PILOT THEN LANDED WITH NO OCCURRENCES. UPON TROUBLESHOOTING THE SUPPLY LINE FOR THE	 NOSE GEAR DOOR ACTUATOR WAS FOUND BROKEN OFF FROM ITS B-NUT. THE LINE HAD NO DATE ON IT AND APPEARS TO BE ORIGINAL EQU	IPMENT.			1	H	7	1 	3O				3A21 					 
1995030300607	19950303	00607	CE 	1995	3	3	95ZZZX996 	1	19950214	G	2410		BUSHING 			CESSNA	310 	310L 	2074230	CE 										ALTERNATOR MOUNT	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	3257X	2113 	460 			310L0107				ALTERNATOR MOUNT BUSHING BADLY WORN ALLOWING ALTERNATOR TO MOVE OUT OF ALIGNMENT CAUSING WEAR ON BELT. EVIDENCE SHOWS C	ONTINUED WEAR ON SIDE OF MOUNT CAUSED BY ALTERNATOR VIBRATIONS. THIS MOUNT WAS CHECKED AND RETORQUED AT LAST INSPECTION	 SOME 132 HOURS PREVIOUSLY.				1	L	7	2 	3O				3A10 					 
1995030300608	19950303	00608	CE 	1995	3	3	95ZZZX997 	1	19950214	G	3510		LINE 			CESSNA	310 	310C 	2074210	CE 										OXYGEN FEED	HOLE CHAFED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	1837H					35937				STOP RETRACTION CABLE RUBBED HOLE IN OXYGEN FEED LINE UNDER FLOOR AND CABIN. OXYGEN SYSTEM NOT FACTORY INSTALLED. LOGB	OOK SHOWS REPLACEMENT OF CABLE A FEW YEARS BACK. SUBMITTER SUGGESTS OXYGEN LINE COULD HAVE BEEN INSTALLED IMPROPERLY.					1	L	7	2 	3O				3A10 					 
1995030300610	19950303	00610	SO 	1995	3	3	95ZZZX999 	1	19950130	G	5320	79553000	FITTING 			PIPER 	PA28 	PA28RT201 	7102818	SO 										LT WINDSHIELD	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	8109D					28R8018014				UPON REMOVAL OF WINDSHIELDS FOR REPLACMENT, THE LEFT WINDSHIELD OUTBOARD STRUCTURE FITTING WAS FOUND TO HAVE SEVERE CORR	OSION FROM A WINDSHIELD LEAK. THE FITTING PART IS STEEL AND RIVETED TO THE ALUMINUM STRUCTURE. SUBMITTER SUGGESTS UPON	 REMOVAL OF WINDSHIELDS, IT IS RECOMMENDED TO INSPECT THIS AREA VERY CLOSELY.				1	L	7	1 	3O				2A13 					 
1995070700268	19950707	00268	EA 	1995	7	7	95ZZZY0717 	2	19950405	G	7200		ENGINE 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3 	52045	EA 					CONTROL SYS	MALFUNCTION 	H			CZ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	24HL					30815				ENGINE HAD UNCONTROLLED ACCELERATION FROM IDLE. RPM OF NF REACHED 110% BEFORE MANUAL GOVERNOR WAS ENGAGED AND ENGINE SE	CURED. INVESTIGATION REVEALED NO LOOSE LINES, NO LINES WITH ICE, AND AFCU DRIVESHAFT WAS SERVICABLE. ENGINE WAS REMOVED	 AND RETURNED TO PRATT & WHITNEY FOR EVALUATION AND REPAIR.				1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1995070700269	19950707	00269	EU 	1995	7	7	95ZZZY0718 	1	19950405	G	6730	SC5071	SERVO 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	LEAKING 	H			R7MA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			FS	01	91GT	2779 				1289				SERVO LEAKING BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700270	19950707	00270		1995	7	7	95ZZZY0719 	4	19950405	G	2330	A21815869817	SWITCH 			BOLKMS	117 	BK117B1 	5626012	EU 										TRIGGER	STICKS 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	17SJ	398 				7230				SWITCH UNIT STICKS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700271	19950707	00271	EU 	1995	7	7	95ZZZY0720 	1	19950405	G	6320	IPT20RT1100080G	TRANSMITTER 			BOLKMS	117 	BK117A3 	5626015	EU 										XMSN OIL PRESS	FAILED 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	158BK					7058				PRESSURE TRANSMITTER WORKED FOR 30 MINUTES FROM INSTALLATION. AFTER 30 MINUTES UNIT FAILED TO INDICATE. REPLACED WITH NE	W UNIT(S) CORRECTED PROBLEM.					1	G	7	2 	3U				H13EU 					 
1995070700272	19950707	00272	EU 	1995	7	7	95ZZZY0721 	1	19950405	G	6320	IPT20RT1100080G	TRANSMITTER 			BOLKMS	117 	BK117A3 	5626015	EU 										XMSN OIL PRESS	FAILED 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	158BK					7058				PRESSURE TRANSMITTER WORKED FOR FIRST 30 MIN. FROM INSTALLATION. AFTER 30 MIN. UNIT FAILED TO INDICATE. REPLACED WITH N	EW UNIT(S) CORRECTED PROBLEM.					1	G	7	2 	3U				H13EU 					 
1995070700273	19950707	00273	EU 	1995	7	7	95ZZZY0722 	1	19950405	G	7931	IPT70RT11000250G	TRANSDUCER 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENG OIL	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	202HN	183 				7115	LE45071			PRESSURE TRANSDUCER UNIT CAUSES PRESSURE FLUCTUATION. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995070700274	19950707	00274	EU 	1995	7	7	95ZZZY0723 	1	19950405	G	7931	IPT70RT11000250G	TRANSDUCER 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					ENG OIL	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	911VU	112 				7141	LE45582			PRESSURE TRANSDUCER UNIT CAUSES INDICATOR NEEDLE TO FLUCTUATE. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995070700275	19950707	00275	EU 	1995	7	7	95ZZZY0725 	1	19950405	G	7931	IPT70RT11000250G	TRANSDUCER 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					ENG OIL	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	911VU	101 				7141	LE45582			#2 OIL PRESSURE GAUGE FLUCTUATES. REPLACED WITH NEW UNIT CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995070700276	19950707	00276	EU 	1995	7	7	95ZZZY0726 	1	19950405	G	6320	IPT20RT1100080G	TRANSMITTER 			BOLKMS	117 	BK117B1 	5626012	EU 										XMSN OIL PRESS	FAILED 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	10UM	441 				7231				NO INDICATION. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700277	19950707	00277	EU 	1995	7	7	95ZZZY0751 	1	19950426	G	6220	1051420103	FLANGE BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R HEAD	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	7060G	1494 				7173				FLANGE BUSHING WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT AND CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700278	19950707	00278	EU 	1995	7	7	95ZZZY0752 	1	19950426	G	6220	1051418103	FLANGE BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R HEAD	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	7060G	1494 				7173				FLANGE BUSHING WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700279	19950707	00279	EU 	1995	7	7	95ZZZY0753 	1	19950426	G	6220	11714107122	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R HEAD	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	7060G	1494 				7173				BOLT WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNITS, 4 EA CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700280	19950707	00280	EU 	1995	7	7	95ZZZY0757 	1	19950426	G	6220	827N85X105X13FP7	SHAFT SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R HEAD	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	7060G	1494 				7173				SHAFT SEAL WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700281	19950707	00281	EU 	1995	7	7	95ZZZY0758 	1	19950426	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL QTY	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	202HN	1 				7115				NUMBER 2 SUPPLY QUANTITY WENT TO -0-. MAIN TANK WENT FROM 140 GALLONS TO 356 GALLONS. REPLACED WITH NEW UNIT(S) CORREC	TED PROBLEM.					1	G	7	2 	3U				H13EU 					 
1995070700282	19950707	00282	NE 	1995	7	7	95ZZZY0759 	2	19950426	G	7250	430136201	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					ENGINE	FAULTY 	H			R7MA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			FS	01	7059N	66 				7154	LE45518E			THIS BEARING IS AFFECTED BY SB LT101-72-10-0151. ALLIED SIGNAL PARTS FACILITY FAILED TO ISOLATE AND DISCARD THIS BEARIN	G. SUBSQUENTLY, ALLIED SIGNAL SHIPPED THE BEARING TO RMH. ALLIEDSIGNAL ADVISED RMH OF ERROR. THE AIRCRAFT WAS GROUNDE	D AND THE ENGINE REMOVED.				1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995070700283	19950707	00283	EU 	1995	7	7	95ZZZY0772 	1	19950510	G	7930	DK040	PRESSURE PICK-OF			BOLKMS	105 	BO105S 	5626006	EU 										ENG OIL	DEFECTIVE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	105LC	177 				789				INDICATOR PEGGED. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H3EU 					 
1995070700284	19950707	00284	EU 	1995	7	7	95ZZZY0773 	1	19950510	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R HEAD	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	71703	360 				7227				BEARING WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700285	19950707	00285	EU 	1995	7	7	95ZZZY0932 	1	19950510	G	6420	10531717	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	17SJ	372 				7230				BOLT WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700286	19950707	00286	EU 	1995	7	7	95ZZZY0933 	1	19950510	G	6210	1051585403	BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R BLADE	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	10UM	313 				7231				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700287	19950707	00287	EU 	1995	7	7	95ZZZY0934 	1	19950510	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	10UM	323 				7231				BEARING WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNITS, CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700288	19950707	00288	EU 	1995	7	7	95ZZZY0935 	1	19950510	G	6420	10531717	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	10UM	245 				7231				BOLT WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700289	19950707	00289	EU 	1995	7	7	95ZZZY0936 	1	19950510	G	6710	10513142	ROD END ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	71703	255 				7227				ROD END ASSY WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700290	19950707	00290	EU 	1995	7	7	95ZZZY0937 	1	19950510	G	6210	11715856	ELASTIC BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	417BK	401 				7143				ELASTOMERICS WORN BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700291	19950707	00291	EU 	1995	7	7	95ZZZY0938 	1	19950510	G	6230	1051011305	BELLOWS 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R MAST	TORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	5188B	451 				7163				BELLOWS IS TORN AROUND CLAMP AND FOLDED AREAS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700292	19950707	00292	EU 	1995	7	7	95ZZZY0939 	1	19950510	G	3310	RV2NBYSD103B	RESISTOR 			BOLKMS	117 	BK117B1 	5626012	EU 										CONSOLE LIGHTS	DEFECTIVE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	5188B	243 				7163				CENTER CONSOLE LIGHTS FLICKER. REPLACED WITH NEW VARIABLE RESISTOR UNIT CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700293	19950707	00293	EU 	1995	7	7	95ZZZY0940 	1	19950510	G	3310	RV2NBYSD103B	RESISTOR 			BOLKMS	117 	BK117B1 	5626012	EU 										CO-PILOT LIGHTS	DEFECTIVE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	5188B	290 				7163				CO-PILOTS INSTRUMENT LIGHTS FLICKER. REPLACED WITH NEW VARIABLE RESISTOR UNIT CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700294	19950707	00294	EU 	1995	7	7	95ZZZY0941 	1	19950510	G	6710	10513142	ROD END ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	417BK	329 				7143				ROD END ASSY WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700295	19950707	00295	EU 	1995	7	7	95ZZZY0955 	1	19950510	G	6420	ABWT82008	BEARING 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	911VU	542 				7141				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700296	19950707	00296	EU 	1995	7	7	95ZZZY0956 	1	19950510	G	6320	4639302037	SEALING RING 			BOLKMS	117 	BK117A4 	5626017	EU 										M/R XMSN	LEAKING 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			FS	01	9025N	19 				7137				SEALING RING LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700297	19950707	00297	EU 	1995	7	7	95ZZZY0957 	1	19950510	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	527SF	407 				7111				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700298	19950707	00298	EU 	1995	7	7	95ZZZY0958 	1	19950510	G	6410	134616P	BUSHING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	527SF	550 				7111				TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700299	19950707	00299	EU 	1995	7	7	95ZZZY0959 	1	19950510	G	6410	134617P	BUSHING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	527SF	550 				7111				TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700300	19950707	00300	EU 	1995	7	7	95ZZZY0960 	1	19950510	G	6210	1051585403	BUSHING 			BOLKMS	117 	BK117A4 	5626017	EU 										M/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	117CW	290 				7125				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. UNITS SCRAPPED ON SITE. SEE LOG BOOK ENTRY ATTACHED. REPLACED WITH NEW UN	IT(S), CORRECTED PROBLEM.					1	G	7	2 	3U				H13EU 					 
1995070700301	19950707	00301	EU 	1995	7	7	95ZZZY0961 	1	19950510	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	117CW	435 				7125				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700302	19950707	00302	EU 	1995	7	7	95ZZZY0962 	1	19950510	G	6230	1051011305	BELLOWS 			BOLKMS	117 	BK117A4 	5626017	EU 										M/R MAST	TORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	911BY	481 				7127				BELLOWS IS TORN AROUND CLAMP AND FOLD AREAS. ABOVE DATE IS OCCURRENCE DATE. REMOVAL DATE 1/10/95. REPLACED WITH NEW UN	IT(S), CORRECTED PROBLEM.					1	G	7	2 	3U				H13EU 					 
1995070700303	19950707	00303	EU 	1995	7	7	95ZZZY0963 	1	19950510	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117A4 	5626017	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	911BY	264 				7127				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700304	19950707	00304	EU 	1995	7	7	95ZZZY0964 	1	19950510	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	428MB	276 				7088				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700305	19950707	00305	EU 	1995	7	7	95ZZZY0965 	1	19950510	G	6420	1053170018	FITTED BOLT 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	117MV	400 				7089				FITTED BOLT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700306	19950707	00306	EU 	1995	7	7	95ZZZY0966 	1	19950510	G	6420	1053170018	FITTED BOLT 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	428MB	916 				7088				FITTED BOLT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700307	19950707	00307	EU 	1995	7	7	95ZZZY0967 	1	19950510	G	2430	MS24149D1	RELAY 			BOLKMS	117 	BK117A3 	5626015	EU 										DC SYS	SHORTED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	424MB					7082				SUSPECT RELAY HAS INTERNAL SHORT, UPON INSTALLATION UNIT POPS CIRCUIT BREAKER. REPLACED WITH NEW UNIT(S), CORRECTED PROB	LEM.					1	G	7	2 	3U				H13EU 					 
1995070700308	19950707	00308	EU 	1995	7	7	95ZZZY0968 	1	19950510	G	6230	1051011305	BELLOWS 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R MAST	TORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	158BK	3 				7058				BELLOWS IS TORN AROUND CLAMP AND FOLD AREAS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700309	19950707	00309	EU 	1995	7	7	95ZZZY0969 	1	19950510	G	6420	ABWT82008	BEARING 			BOLKMS	105 	BO105CBS 	5626008	EU 										T/R	WORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	722MB	523 				754				BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U			NC	H3EU 					 
1995070700310	19950707	00310	EU 	1995	7	7	95ZZZY0970 	1	19950510	G	6220	114986P	BALL END 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	58045	436 				1602				TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. UNITS SCRAPPED ON SITE.						1	G	7	1 	3U				H9EU 					 
1995070700311	19950707	00311	EU 	1995	7	7	95ZZZY0971 	1	19950510	G	6420	704A33633116	ROLLED BEARING 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	29888	310 				1065				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) FROM KIT NO. 355A09-1036-00 CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700312	19950707	00312	EU 	1995	7	7	95ZZZY0972 	1	19950510	G	6220	117775P	BALL END 			SNIAS 	350 	AS350B 	8680801	EU 										STARFLEX	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	5771C	493 				1369				TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700313	19950707	00313	EU 	1995	7	7	95ZZZY0973 	1	19950510	G	6420	704A33633116	BEARING 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	58045	534 				1602				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) FROM KIT PN 355A09-1036-00 CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700314	19950707	00314	EU 	1995	7	7	95ZZZY0975 	1	19950510	G	6720	3160S88100454	CONTROL CABLE 			AEROSP	SA316 	SA316B 	8680207	EU 										T/R DRUM	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	9362	422 				1739				EXCESSIVE DISCOLORATION AND CRACKING OF CABLE COATING AROUND T/R DRUM AREA. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM	.					1	G	7	1 	4U			 	H1IN 					 
1995070700315	19950707	00315	EU 	1995	7	7	95ZZZY0976 	1	19950510	G	6720	3160S88100454	CONTROL CABLE 			AEROSP	SA316 	SA316B 	8680207	EU 										T/R DRUM	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	67081	159 				2184				EXCESSIVE DISCOLORATION AND CRACKING OF CABLE COATING AROUND T/R DRUM AREA. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM	.					1	G	7	1 	4U			 	H1IN 					 
1995070700316	19950707	00316	EU 	1995	7	7	95ZZZY0977 	1	19950510	G	6410	704A33633171	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R BLADE	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	92LG	253 				2575A				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) FROM KIT PN 579-091, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700317	19950707	00317	EU 	1995	7	7	95ZZZY0978 	1	19950510	G	6220	117775P	BALL END 			SNIAS 	350 	AS350B2 	8680813	EU 										STARFLEX	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	93LG	500 				2654				TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. LINERS OF THE BEARINGS ARE CRACKED WHERE THEY RIDE ON THE STARFLEX. REPLA	CED WITH NEW UNIT(S), CORRECTED PROBLEM.					1	G	7	1 	3U				H9EU 					 
1995070700318	19950707	00318	EU 	1995	7	7	95ZZZY0979 	1	19950510	G	6420	704A33633116	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	93LG	256 				2654				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) FROM KIT PN 350A09-1036-00 CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700319	19950707	00319	EU 	1995	7	7	95ZZZY0980 	1	19950510	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	93LG	583 				2654				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) FROM KIT PN 350A33-2153-00, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700320	19950707	00320	EU 	1995	7	7	95ZZZY0981 	1	19950510	G	2150	350A72032501	BOX 			SNIAS 	350 	AS350B2 	8680813	EU 										AIR INTAKE	CRACKED 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	94LG	492 				2728				AIR INTAKE BOX CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700321	19950707	00321	EU 	1995	7	7	95ZZZY0982 	1	19950510	G	3340	356H28	LIGHT 			SNIAS 	350 	AS350B2 	8680813	EU 										ANTI COLL	INOPERATIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	94LG	335 				2728				UNIT INOPERATIVE. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700322	19950707	00322	EU 	1995	7	7	95ZZZY0983 	1	19950510	G	7930	642790041	TRANSMITTER 			SNIAS 	350 	AS350B2 	8680813	EU 										OIL PRESSURE	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	94LG	335 				2728				OIL PRESSURE GUAGE PEGS WHEN BATTERY PWR IS ON. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700323	19950707	00323	EU 	1995	7	7	95ZZZY0984 	1	19950510	G	7930	642790041	TRANSMITTER 			SNIAS 	350 	AS350B2 	8680813	EU 										ENG OIL	FAILED 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	94LG	160 				2728				NO OUTPUT SIGNAL. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700324	19950707	00324	EU 	1995	7	7	95ZZZY0985 	1	19950510	G	6420	704A33633116	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	94LG	221 				2728				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) FROM KIT 355A09-1036-00, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700325	19950707	00325	EU 	1995	7	7	95ZZZY0986 	1	19950510	G	6420	704A33633116	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	94LG	158 				2728				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) FROM KIT NO. 355A09-1036-00, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700326	19950707	00326	EU 	1995	7	7	95ZZZY0987 	1	19950510	G	6410	704A33633171	HINGE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	94LG	187 				2728				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) FROM KIT NO. 579-091, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700327	19950707	00327	EU 	1995	7	7	95ZZZY0988 	1	19950510	G	6730	AC67246	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	LEAKING 	H			R7MA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			FS	01	94LG	696 				2728				SERVO LEAKING FROM PILOT VALVE BEYOND SERVICEABLE LIMITS. . REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700328	19950707	00328	EU 	1995	7	7	95ZZZY0989 	1	19950510	G	6510	355A34107820	FLANGE SPLINE 			AEROSP	AS355 	AS355F1 	8680810	EU 										T/R DRIVE	WEAR 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	5787M	428 				5067				EXCESSIVE SPLINE WEAR. ABOVE DATE IS OCCURRENCE DATE, REMOVAL DATE 11/25/94. REPLACED WITH NEW UNIT(S), CORRECTED PROBL	EM.					1	G	7	2 	3U				H11EU 					 
1995070700329	19950707	00329	EU 	1995	7	7	95ZZZY0990 	1	19950510	G	7931	IPT70RT11000250G	TRANSDUCER 			BOLKMS	117 	BK117A3 	5626015	EU 										OIL PRESSURE	MALFUNCTION 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	424MB	274 				7082				OIL PRESSURE FLUCTUATION. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700330	19950707	00330	EU 	1995	7	7	95ZZZY0991 	1	19950510	G	2550	AFG0432143	AUTOMATIC STRAP 			BOLKMS	117 	BK117A4 	5626017	EU 										RELEASE CABLE	WRONG PART 	H			R7MA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			FS	01	586BH					7129				AFTER INSTALLATION IT WAS NOTED THAT THE RELEASE CABLE WAS TOO LONG. THE PART NUMBER SHIPPED BY AEC WAS NOT THE PART NU	MBER ORDERED. ON RMH PO 19859 THE ACTUAL PART NUMBER ORDERED WAS AFG0176217. REPLACED WITH NEW UNIT(S), CORRECTED PROBL	EM.				1	G	7	2 	3U				H13EU 					 
1995070700331	19950707	00331	EU 	1995	7	7	95ZZZY0992 	1	19950510	G	3340	6034743	SUPPLY UNIT 			BOLKMS	117 	BK117A3 	5626015	EU 										FLASHER	INOPERATIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	428MB	209 				7088				SUPPLY UNIT INOPERATIVE. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700332	19950707	00332	EU 	1995	7	7	95ZZZY0993 	1	19950510	G	6710	10513142	ROD END ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	911VU	821 				7141				ROD END ASSY WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700333	19950707	00333	EU 	1995	7	7	95ZZZY0994 	1	19950510	G	3340	3146581	LIGHT 			BOLKMS	117 	BK117B1 	5626012	EU 										SUB ASSY	INOPERATIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	911VU	286 				7141				LIGHT UNIT INOPERATIVE. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700334	19950707	00334	EU 	1995	7	7	95ZZZY0995 	1	19950510	G	6220	1051410110	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	PLATING WEAR 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	5194C	203 				7169				MAIN BOLT EXCESSIVE PLATING WEAR. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700335	19950707	00335	EU 	1995	7	7	95ZZZY0996 	1	19950510	G	8000	SP461300	TOGGLE SWITCH 			BOLKMS	117 	BK117B1 	5626012	EU 										START SYS	STICKS 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	10UM	237 				7231				TOGGLE SWITCH STICKS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700336	19950707	00336	EU 	1995	7	7	95ZZZY0997 	1	19950510	G	7931	DK040	TRANSMITTER 			BOLKMS	105 	BO105CBS 	5626008	EU 										OIL PRESS	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	722MB	295 				754				HIGH READINGS. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U			NC	H3EU 					 
1995070700337	19950707	00337	EU 	1995	7	7	95ZZZY0998 	1	19950510	G	6730	AC67244	SERVO 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	58045	204 				1602				M/R SERVO FEEDBACK. REPLACED WITH OVERHAULED UNIT(S), CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1995070700338	19950707	00338	EU 	1995	7	7	95ZZZY0999 	1	19950510	G	3340	024716	BULB 			BOLKMS	117 	BK117A3 	5626015	EU 										ANTI COLL	PIN BROKE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	420MB					7077				ANODE PIN BROKE OFF DURING LAMP REPLACEMENT. XENON TUBE DID NOT BURST. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995070700339	19950707	00339	CE 	1995	7	7	95ZZZY1000 	1	19950510	G	7810	31031281	SHROUD 			BEECH 	18 	C45 	1150904	CE 										EXH	FLAKING 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	8970N	1595 				0092				SHROUD HAS PREMATURE FLAKING. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	L	7	2 	3R				A757 					 
1995070700340	19950707	00340	NE 	1995	7	7	95ZZZY1001 	2	19950510	G	7250	414129001	PT ROTOR 			BOLKMS	117 	BK117A4 	5626017	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENGINE	BLADE SHIFT 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	127HH	1231 				7060	LE45244E			FAILED SERVICE BULLETIN LT 101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT. #12 +0.012". REPLACED WITH NEW UNIT(S), CORRECT	ED PROBLEM.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995070700341	19950707	00341	NE 	1995	7	7	95ZZZY1002 	2	19950510	G	7250	414129001	PT ROTOR 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENGINE	BLADE SHIFT 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	117MA	1076 				7107	LE45155E			FAILED SERVICE BULLETIN LT 101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT. #4-0.0145". REPLACED WITH NEW UNIT(S), CORRECTE	D PROBLEM.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995070700342	19950707	00342	NE 	1995	7	7	95ZZZY1003 	2	19950510	G	7250	411105056	ROTOR ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					GAS PRODUCER	DEFECTIVE 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	7059N	1817 				7154	LE45752			DUE SERVICE BULLETIN LT 101-72-10-0150. REQUIRES DISASSEMBLY AND INSPECTION OF ROTOR BROACH SLOTS FOR POSSIBLE CRACKS I	N THE DISC/TENON AREA. LAB SEAL ENCLOSED WITH ROTOR. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.					1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995070700343	19950707	00343	NE 	1995	7	7	95ZZZY1004 	2	19950510	G	7250	414129001	PT ROTOR 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					ENGINE	BLADE SHIFT 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	5188B	1776 				7163	LE45518E			FAILED SERVICE BULLETIN LT 101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995070700344	19950707	00344	NE 	1995	7	7	95ZZZY1005 	2	19950510	G	7250	414129001	PT ROTOR 			BOLKMS	117 	BK117A4 	5626017	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENGINE	BLADE SHIFT 	H			R7MA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	128HH	663 				7036	LE45332			FAILED SERVICE BULLETIN LT 101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995070700345	19950707	00345	GL 	1995	7	7	95ZZZY1458 	2	19950612	G	7323	23007505	GOVENOR 								ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	DEFECTIVE 	H			XH3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01										NG SPLIT. FOUND GOV FAULTY											3	U			E4CE				 
1995070700346	19950707	00346		1995	7	7	95ZZZY1459 	4	19950612	G	3444	066305401	ALTIMETER 	KING 	KI250 															COCKPIT	DEFECTIVE 	H			XH3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01										RADAR ALTIMETER HAS JUMPY NEEDLE.																			 
1995070700347	19950707	00347	SW 	1995	7	7	95ZZZY1462 	1	19950612	G	2435	206062218001	DUCT 			BELL 	206 	206B3 	1181506	SW 										START/GEN	CRACKED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	303PD					4319				PART FOUND CRACKED DURING INSPECTION.						1	G	7	1 	3U				H2SW 					 
1995070700348	19950707	00348	SW 	1995	7	7	95ZZZY1463 	1	19950612	G	6420	206011736001	BOOT 			BELL 	206 	206B3 	1181506	SW 										T/R	TORN 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	303PD					4319				TAIL ROTOR BOOT TORN.						1	G	7	1 	3U				H2SW 					 
1995070700349	19950707	00349	SW 	1995	7	7	95ZZZY1464 	1	19950612	G	6320	206040156101	SEAL ASSY 			BELL 	206 	206B3 	1181506	SW 										M/R GR BOX	FAILED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	303PD					4319				SEAL FAILED.						1	G	7	1 	3U				H2SW 					 
1995070700350	19950707	00350		1995	7	7	95ZZZY1468 	4	19950612	G	3120	1120WE	CLOCK 			AEROSP	AS355 	AS355F1 	8680810	EU 	ALLSN 	250C 	250C20F 	03013	GL 					COCKPIT	DEFECTIVE 	H			INDA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	321HC	3407 				5015	CAE840527			TIMER RESET BUTTON BROKEN OFF. REPLACED CLOCK						1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1996010500258	19960105	00258	EA 	1996	1	5	96ZZZX1 	2	19951013	G	7210	3100767	SUN GEAR 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					PT HOUSING	FRACTURED 	B			MASR	E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	01	118YV	4384 			55C037	UC118	32532			AN IN-FLIGHT SHUT DOWN OF THE LT ENGINE DUE TO THE FAILURE OF THE POWER SECTION. AT THE TEAR DOWN, THE INVESTIGATION RE	VEALED THE NR 1 SUN GEAR AS BEING THE MODE OF FAILURE.					2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1996010500571	19960105	00571	WP 	1996	1	5	96ZZZX100 	1	19951216	G	6230	369D27609501	SWASHPLATE 			HUGHES	369 	369D 	4470706	WP 										M/R	DEFECTIVE 	B			EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R	3945 	2277 		0716	1151D				PILOT COMPLAINED THAT FORE/AFT CYCLIC WAS A 'LITTLE NOTCHEY'. SUBSEQUENT INSPECTION FOUND THE UNIBAL LINER IN THE OUTER	 RACE WAS CONTAMINATED WITH GREASE OR OIL AND WAS ROUGH. REPLACED SWASHPLATE AND SENT THE OTHER IN FOR OVERHAUL.					1	G	7	1 	3U				H3WE 					 
1996031500052	19960315	00052	SW 	1996	3	15	96ZZZX1000 	1	19950519	G	6220	204010937009	DAMPER 			BELL 	212 	212 	1181420	SW 										M/R	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	708H		21 		H1021	30641				DAMPER TIMING IS SLOW 2 SECONDS.						1	G	7	1 	4U				H4SW 					 
1996031500053	19960315	00053	SW 	1996	3	15	96ZZZX1001 	1	19950422	G	6410	206016201127	BLADE 			BELL 	206 	206L3 	1182108	SW 										T/R	PAINT PEEL 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	731H		47 		CS3836	51562				BAD PAINT 'VERY ROUGH PAINT'.						1	G	7	1 	3U				H2SW 					 
1996031500054	19960315	00054	SW 	1996	3	15	96ZZZX1002 	1	19950511	G	6230	206040014103	MAST ASSY 			BELL 	206 	206L3 	1182108	SW 										M/R	MAKING METAL 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	731H		99 		51550	51562				MAKING METAL.						1	G	7	1 	3U				H2SW 					 
1996031500055	19960315	00055	SW 	1996	3	15	96ZZZX1003 	1	19950404	G	2435	200SGL111Q	GENERATOR 			BELL 	206 	206L3 	1182108	SW 										STAT/GEN	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	731H		444 		1934	51562				STARTER/GENERATOR FAILED DURING GROUND RUN. NO OUTPUT. FOUND SEVERAL BAD BRUSHES (WORN/PITTED EXCESSIVELY).						1	G	7	1 	3U				H2SW 					 
1996031500056	19960315	00056	SW 	1996	3	15	96ZZZX1004 	1	19950511	G	6320	206040004107	TRANSMISSION 			BELL 	206 	206L3 	1182108	SW 										M/R	MAKING METAL 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	731H		99 		A101	51562				TRANSMISSION MAKING METAL.						1	G	7	1 	3U				H2SW 					 
1996031500057	19960315	00057	SW 	1996	3	15	96ZZZX1005 	1	19950707	G	7722	212075067109	INDICATOR 			BELL 	212 	212 	1181420	SW 										COCKPIT ITT	INOPERATIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	736H		27 		101	35048				ITT INDICATOR INOPERATIVE.						1	G	7	1 	4U				H4SW 					 
1996031500058	19960315	00058	SW 	1996	3	15	96ZZZX1006 	1	19950814	G	7722	212075067109	INDICATOR 			BELL 	212 	212 	1181420	SW 										ITT	INOPERATIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	736H		116 		384	35048				NO ITT INDICATION WHEN ENGINE IS RUNNING.						1	G	7	1 	4U				H4SW 					 
1996031500059	19960315	00059	SW 	1996	3	15	96ZZZX1007 	1	19950813	G	2435	214175150105	GENERATOR 			BELL 	214 	214ST 	1182106	SW 										START/GEN	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H		333 		296	28197				GENERATOR WILL NOT RESET.						2	G	7	2 	4U				H10SW 					 
1996031500060	19960315	00060		1996	3	15	96ZZZX1008 	4	19950725	G	2210	214001540117	ACTUATOR 			BELL 	214 	214ST 	1182106	SW 										YAW SCAS	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H		47 		0329	28197				YAW CHANNEL OF SCAS WILL NOT ENGAGE.						2	G	7	2 	4U				H10SW 					 
1996031500061	19960315	00061	SW 	1996	3	15	96ZZZX1009 	1	19950627	G	6322	ES731701	BLOWER 			BELL 	214 	214ST 	1182106	SW 										MOTOR	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H				22	28197				FAILED, INOPERATIVE.						2	G	7	2 	4U				H10SW 					 
1996010500572	19960105	00572	SW 	1996	1	5	96ZZZX101 	1	19951201	G	6320	476209617	SPIDER SET 			BELL 	47 	47G5A 	1181034	SW 										TRANSMISSION	DEFECTIVE 	B			OUGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	4348P					25059				RECEIVED SPIDER SET FROM BELL AS A NEW REPLACEMENT PART. PLANETARY PIN HOLES ARE ROUGH AND HAVE TOO MUCH UNEVEN CHAMFER	.					1	G	7	1 	3O				2H3 					 
1996031500062	19960315	00062	SW 	1996	3	15	96ZZZX1010 	1	19950612	G	6420	214011801109	HUB ASSY 			BELL 	214 	214ST 	1182106	SW 										T/R	ROUGH 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H		42 		A24	28197				TRUNNION VERY ROUGH WHEN ROTATED.						2	G	7	2 	4U				H10SW 					 
1996031500064	19960315	00064	SW 	1996	3	15	96ZZZX1012 	1	19950814	G	2436	214175153105	REGULATOR 			BELL 	214 	214ST 	1182106	SW 										DC SYSTEM	FAULTY 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H				236A	28197				GENERATOR WILL NOT COME ON LINE DUE TO FAULTY REGULATOR.						2	G	7	2 	4U				H10SW 					 
1996031500065	19960315	00065	SW 	1996	3	15	96ZZZX1013 	1	19950815	G	2436	214175153105	REGULATOR 			BELL 	214 	214ST 	1182106	SW 										DC SYSTEM	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H				145A	28197				GENERATOR WILL NOT COME ON LINE, FAULTY REGULATOR.						2	G	7	2 	4U				H10SW 					 
1996031500066	19960315	00066	SW 	1996	3	15	96ZZZX1014 	1	19950815	G	7810	212061202009	DUCT 			BELL 	212 	212 	1181420	SW 										EXHAUST	RACKED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	749H		52 		01682	35061				EXHAUST DUCT FORWARD FACE CRACKED.						1	G	7	1 	4U				H4SW 					 
1996031500067	19960315	00067	NE 	1996	3	15	96ZZZX1015 	2	19950718	G	7532	3033063CL	BLEED VALVE 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					ENGINE	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	749H		28 		B1878	35061				BLEED VALVE WILL NOT CLOSE COMPLETELY, NOT WORKING POWER.						1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1996031500070	19960315	00070	EU 	1996	3	15	96ZZZX1018 	1	19951228	G	7714	645383051	INDICATOR 			AEROSP	SA365 	SA365N1 	8680668	EU 										NR 2 ENG NG	FLUCTUATE 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	03	365UC	1718 			641	6329				NR 2 ENGINE N.G. FLUCTUATING. REPLACED NG INDICATOR, SYSTEM CHECKED OK.						1	G	7	2 	3U				H10EU 					 
1996010500573	19960105	00573	NE 	1996	1	5	96ZZZX102 	2	19951208	G	7323	430121203	GOVERNOR 	BENDIX 		BOLKMS	117 	BK117A1 	5626010	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENGINE PT	MALFUNCTION 	B			BAQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	03	117CJ		309 		84020060	S7051	LE45130			TROUBLESHOT SYSTEM, FOUND POWER TURBINE GOVERNOR NOT FUNCTIONING PROPERLY. REPLACED GOVERNOR. PERFORMED GROUND RUN AND	 OPS CHECKED, NO DEFECTS NOTED. N2 FLUCTUATIONS HAVE BEEN REPAIRED.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996031500165	19960315	00165	GL 	1996	3	15	96ZZZX1027 	1	19951212	G	2436	VSF7203	REGULATOR 	PRESTOLITE 		ENSTRM	F28 	280C 	3300505	GL 										DC SYSTEM	SHORTED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	51742					1148				VOLTAGE REGULATOR SHORTED OUT CAUSING RUN AWAY ALTERNATOR. REPLACED REGULATOR. SUBMITTER SUGGESTS NEW PART NUMBER REGU	LATOR, ELD-069-11.					1	G	7	1 	3O				H1CE 					 
1996010500574	19960105	00574	SW 	1996	1	5	96ZZZX103 	1	19951201	G	6710	A21810064603	SWITCH 			HUGHES	500N 	500N 	3027374	SW 										PILOT CYCLIC	INOPERATIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	521FB	165 				LN001				PILOT'S TRIM SWITCH INTERMITTENT IN ALL DIRECTIONS. (EFFECTS PILOT CONTROL.)						1	G	7	1 	3U			NC	H3WE 					 
1996031500168	19960315	00168	SW 	1996	3	15	96ZZZX1030 	1	19951221	G	6320	206040002115	TRANSMISSION 			BELL 	206 	206B3 	1181506	SW 										CORK	LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	09	34698	500 				4324				TRANSMISSION OIL LEAKING THROUGH CORK. CORK SEEMS SATURATED WITH OIL. APPEARS CORK NEEDS TO BE SEALED WITH SOMETHING B	ETTER THAN SHELLAC.					1	G	7	1 	3U				H2SW 					 
1996031500170	19960315	00170	NE 	1996	3	15	96ZZZX1032 	2	19950401	G	7260	430126801	BEARING 		408100032 	SNIAS 	350 	AS350D 	8680803	EU 	LYC 	LTS101	LTS101600A2 	41560	NE 					ACCY GEARBOX	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	900PH	4008 			W816007	1428	LE43485			AFTER ENGINE TEAR-DOWN, THE NR 19 BEARING WAS FOUND BROKEN IN 3 PLACES AROUND THE OUTER RACE. THE BEARING IS A SLIP/FIT	 IN THE GEARBOX AND THE BORE WAS WORN FROM THE BEARING SPINNING. SUBMITTER SUGGESTS A METHOD OF PINNING OR SECURING THE	 BEARING OUTER RACE TO THE GEARBOX BORE.				1	G	7	1 	3U	3	U		H9EU 	E5NE				 
1996010500575	19960105	00575	WP 	1996	1	5	96ZZZX104 	1	19951216	G	6210	369A10045	PIN 			HUGHES	369 	369D 	4470706	WP 										M/R BLADE	EXCESS WEAR 	B	S		EOOR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	5074R	361 			1082R541	1151D				WHILE REMOVING BLADES FOR M/R SWASHPLATE REPLACEMENT, ONE OF THE BLADE PINS WAS FOUND WITH ABNORMAL WEAR IN THE CAM HAND	LE PIVOT BOSS. PIN RETURNED TO MDHC ON SOR NR 300165.					1	G	7	1 	3U				H3WE 					 
1996031500180	19960315	00180		1996	3	15	96ZZZX1043 	4	19950415	G	3421	1113034	INDICATOR 																	COCKPIT	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01					0234					THE LEFT RIGHT KNOB WORKS IN THE OPPOSITE DIRECTION MORE THAN TWICE AS FAR LEFT AS RIGHT. UP/DOWN IMPROPER LIMITS.																			 
1996010500611	19960105	00611	SW 	1996	1	5	96ZZZX105 	1	19951108	G	5321	205031332011	PANEL 		205031320047	BELL 	212 	212 	1181420	SW 										RT FWD FLOOR	CORRODED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	62AL					30826				WHILE PERFORMING A SHEET METAL INSPECTION, FOUND SKIN CORRODED AND SEPARATED AROUND PERIMETER OF RT FORWARD FLOOR PANEL.	 INADEQUATE (PRO-SEAL) AROUND PERIMETER OF PANEL.					1	G	7	1 	4U				H4SW 					 
1996010500612	19960105	00612	GL 	1996	1	5	96ZZZX106 	2	19951114	G	7230	23005667	PC TUBE ASSY 			BELL 	206 	206L4 	1182110	SW 	ALLSN 	250C 	250C30P 	03013	GL 					COMP SCROLL	B-NUT BURRED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	176AL	16 				52146	CAE895824			DURING REMOVAL OF LINE TO C/W ENGINE POWER RECOVERY WASH. NOTICED THE B-NUT WAS HARD TO TURN WHEN REMOVING THE LINE. B	-NUT THREADS BURRED.					1	G	7	1 	3U	3	U	NC	H2SW 	E1GL				 
1996010500613	19960105	00613	SW 	1996	1	5	96ZZZX107 	1	19951114	G	5312	205032827013	BULKHEAD 			BELL 	412 	412 	1182202	SW 										T/B STA 163	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2071C					33042				AFTER LOCATING AND DRILLING BULKHEAD, A CRACK AT THE WELD POINT WAS FOUND. (THERE IS NOT SUPPOSED TO BE A SHRINKAGE LIN	E ON PART.) CRACKED AT FORMING (SHRINKAGE) LINE. THESE PARTS HAVE PILOT HOLES, THEN FORMED AFTER, AS CAN BE SEEN ON PI	LOT HOLES ON LOWER FLANGE.				1	G	7	2 	4U				H4SW 					 
1996010500614	19960105	00614	SW 	1996	1	5	96ZZZX108 	1	19951201	G	7810	23032325	EXH COLLECTOR 		23035128 	BELL 	206 	206L3 	1182108	SW 										PT SECTION	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	187AL	2650 	1159 		42330	51135				PRE-FLIGHT OF AIRCRAFT, FOUND EXHAUST COLLECTOR CRACKED SHEET METAL; 2 PLACES, 3 O'CLOCK AND 9 O'CLOCK POSITIONS.						1	G	7	1 	3U				H2SW 					 
1996031500640	19960315	00640	CE 	1996	3	15	96ZZZX1091 	1	19951226	G	2821	07560097	FILTER 			CESSNA	172 	R172E 	2072413	CE 										FUEL SYSTEM	CRUSHED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	03	7752L					R1720428				DURING ACCEPTANCE INSPECTION, AIRCRAFT FUEL FILTER REMOVED FOR INSPECTION AND FOUND CRUSHED. THE FILTER HAD BEEN INSTAL	LED IN THE STRAINER IMPROPERLY. REPLACED FILTER AND REINSTALLED CORRECTLY.					1	H	7	1 	3O				3A17 					 
1996031500641	19960315	00641	CE 	1996	3	15	96ZZZX1092 	1	19951226	G	5730	052305568	SKIN 			CESSNA	172 	R172E 	2072413	CE 										LT WING LE	MISREPAIRED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	03	7752L					R1720428				LEFT WING LEADING EDGE SKIN REPAIRED FROM WING ROOT TO WS 56.37. THE REPAIR WAS NOT DONE IAW APPROVED DATA. ATTAINED A	PPROVED ENGINEERING ORDER FROM CESSNA AIRCRAFT COMPANY AND REACCOMPLISHED REPAIR.					1	H	7	1 	3O				3A17 					 
1996031500644	19960315	00644		1996	3	15	96ZZZX1095 	4	19951018	G	6113		SPINNER 			AMTR 	T18 	THORPT18 		GL 										PROPELLER	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	01	872RM					872				EXPERIMENTAL AIRCRAFT, ON RUN-UP, AT FULL RPM - PROPELLER SPINNER SPLIT INTO 3 PIECES, 2 LARGE PIECES LEFT AIRCRAFT. CO	ULD NOT BE FOUND. AIRCRAFT ENGINE SHUT DOWN. THIS SPINNER HAD BEEN CHROME-PLATED SOME TIME IN THE PAST.					1	L	7	1 	3O				EXPA1L71					 
1996010500616	19960105	00616	SW 	1996	1	5	96ZZZX110 	1	19951108	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	59541		978 			1412				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6604D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 978.4.				1	G	7	1 	3U				H2SW 					 
1996010500617	19960105	00617	SW 	1996	1	5	96ZZZX111 	1	19951108	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206B 	1181511	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	59541		978 			1412				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S	PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6604D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 978.4.				1	G	7	1 	3U				H2SW 					 
1996031500669	19960315	00669	CE 	1996	3	15	96ZZZX1120 	1	19951210	G	3230	12416186	SUPPORT 			CESSNA	210 	210L 	2073448	CE 										MLG DOWNLOCK	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	711TM	4155 				21061301				DURING ANNUAL INSPECTION, FOUND MAIN GEAR DOWNLOCK SUPPORT ASSEMBLY LOOSE AND ALLOWING SHIM TO MIGRATE. ALL 4 BOLTS WHI	CH SECURE SUPPORT WERE LOOSE. MM CALLS FOR THESE BOLTS TO BE LOCTITED AND SECURED WITH A SHAKEPROOF WASHER. ASSUMING T	HAT VIBRATION OVER TIME CAUSED LOOSENESS AS NO PARTS WERE DEFECTIVE. TIGHTENED SUPPORT AND RIGGED PER CESSNA 210 MANUAL	. OPS CHECK OK. SUBMITTER STATED IF LEFT LOOSE, IT IS POSSIBLE TO HAVE NO INTERMITTENT GEAR DOWN INDICATIONS.			1	H	7	1 	3O				3A21 					 
1996031500670	19960315	00670	CE 	1996	3	15	96ZZZX1121 	1	19951210	G	3222	12436171	COLLAR 			CESSNA	210 	210L 	2073448	CE 										NLG	LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	711TM	4155 				21061301				DURING ANNUAL INSPECTION, FOUND LOWER COLLAR ON NLG LOOSE. DISASSEMBLED STRUT AND INSPECTED PARTS. REASSEMBLED STRUT A	ND RE-SHIMMED COLLAR. FUNCTIONAL CHECK OK.					1	H	7	1 	3O				3A21 					 
1996032200022	19960322	00022	NE 	1996	3	22	96ZZZX1149 	2	19951215	G	7260	H08105307	GEAR TOOTH 		408100033 						LYC 	LTS101	LTS101650B1 	41560	NE 					ACCY GRBOX	BROKEN 	B			YKER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17		1688 			89G068		LE45231			ENGINE WAS REPORTEDLY MAKING METAL. UPON DISASSEMBLY AND INSPECTION OF THE GEARBOX, FOUND THE POWER PINION GEAR HAD ONE	 OF THE TEETH BROKEN OFF. FRACTURE APPEARS TO HAVE STARTED BELOW THE BASE OF THE GEAR TOOTH. SUBMITTER STATED CAUSE UN	KNOWN.									3	U			E5NE				 
1996032200023	19960322	00023	NE 	1996	3	22	96ZZZX1150 	2	19951215	G	7250	414108303	PLUG 								LYC 	LTS101	LTS101650B1 	41560	NE 					PT ROTOR	GALLED 	B			YKER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17							LE45231			PILOT REPORTED FLUCTUATION OF N2 RPM INDICATION. UPON INVESTIGATION, FOUND THE PT RETENTION SYSTEM NUT LOOSE WHICH CAUS	ED GALLING OF THE SPEED INDICATOR PLUG ON THE PT ROTOR, THE FLANGE, SPACER, AND NUT.										3	U			E5NE				 
1996032200024	19960322	00024	NE 	1996	3	22	96ZZZX1151 	2	19951215	G	7250	408108309	NUT 								LYC 	LTS101	LTS101650B1 	41560	NE 					PT ROTOR	LOOSE 	B			YKER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17							LE45231			PILOT REPORTED FLUCTUATION OF N2 RPM INDICATION. UPON INVESTIGATION, FOUND THE PT RETENTION SYSTEM NUT LOOSE WHICH CAUS	ED GALLING OF THE SPEED INDICATOR PLUG ON THE PT ROTOR, THE FLANGE, SPACER, AND NUT.										3	U			E5NE				 
1996032200026	19960322	00026	CE 	1996	3	22	96ZZZX1153 	1	19951201	G	3240	16958000187	BRAKE LINE 			BEECH 	23 	C23 	1151242	CE 										RT BRAKE	CORRODED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	09	2215L					M1868				RT BRAKE WAS SOFT. FOUND BELLY PANELS WET OF HYDRAULIC FLUID. FOUND RT BRAKE LINE CORRODED THROUGH. BRAKE LINE IS HAR	D TO SEE UNDER FLOOR PANELS AND HAD CORRODED THROUGH ON SIDE NOT VISIBLE.					1	L	7	1 	3O				A1CE 					 
1996032200032	19960322	00032	SO 	1996	3	22	96ZZZX1159 	2	19951222	G	8500		ENGINE 			CESSNA	340 	340CESSNA 	2076404	CE 	CONT 	O520 	TSIO520N 	17040	SO 					RT ENGINE	EXCES WEAR 	B	L		QD5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	07	383DQ	768 				3400089	2176695			FOLLOWING LT AND RT PROP REMOVAL FOR SLUGGISH OPERATION, FOUND EXTREME ENGINE OIL SLUDGE. THIS CONDITION OCCURRED AT 76	8 HRS TCM ZERO TIME ENGINES. FURTHER EXAMINATION FOUND EXCESS WEAR AND SLUDGE THROUGHOUT ENGINE. ACFT HAD BEEN OPERATE	D USING AV-1 OIL.				1	L	7	2 	3O	3	O		3A25 	E8CE				 
1996032200033	19960322	00033	WP 	1996	3	22	96ZZZX1160 	2	19950718	G	7320		FCU MOUNT 			GULSTM	680TP 	681 	0141718	SW 	GARRTT	TPE331	TPE33143B 	01514	WP 					RT ENGINE	BOLT MISSING 	D	L			O				OTHER 				X			ENGINE FLAMEOUT 			CR	CRUISE 	1			SO	03	676DM					6048				RT ENGINE IN-FLIGHT SHUT DOWN. INVESTIGATION FOUND RT P3 AIR LINE FITTING FOR FUEL CONT DISCONNECTED. FURTHER INVESTIG	ATION FOUND FUEL CONT LOWER MOUNT BOLT MISSING CONTRIBUTING TO VIBRATION TO WORK P3 AIR LINE FITTING LOOSE.					1	H	7	2 	3T	4	T		2A4 	E2WE				 
1996032200438	19960322	00438	CE 	1996	3	22	96ZZZX1248 	1	19950508	G	2460	CM358950	SWITCH 			CESSNA	402 	402C 	207590R	CE 										AVION MASTER	BURNED 	C		A		H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			NE	01	120PC					402C0079				DURING CRUISE FLIGHT, CABIN STARTED FILLING WITH SMOKE. SMOKE WAS ORIGINATING FROM AVIONICS MASTER SWITCH - UNABLE TO T	URN SWITCH OFF, SO CIRCUIT BREAKERS WERE PULLED. SMOKE EVACUATION PROCEDURES WERE INITIATED AND SMOKE SUBSIDED. A NORM	AL LANDING WAS MADE. PROBLEM CONFIRMED TO BE THE AVIONICS MASTER SWITCH. SWITCH REPLACED WITH NEW. AIRCRAFT RETURNED 	TO SERVICE.			1	L	7	2 	3O				A7CE 					 
1996032200441	19960322	00441	CE 	1996	3	22	96ZZZX1251 	1	19951229	G	3213	07100	BEARING CONE 			BEECH 	90 	C90A 	1152911	CE 										RT MLG WHEEL	FAILED 	B	L		NN3R	O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			WP	25	494JY	1059 				LJ1352				OUTER BEARING CONE (BEARING CLOSEST TO AXLE NUT) BROKE CAUSING THE ROLLER BEARINGS AND BEARING CAGE TO SEPARATE FROM THE	 BEARING CONE ASSY. THIS ALLOWED RT MAIN WHEEL TO WORK ITS WAY OFF AXLE AND SEPARATE FROM THE ACFT ON TAKEOFF. THE AXL	E NUT, COTTER PIN, SPACER, INNER BEARING, AND SEAL WERE IN PLACE WHEN THE ACFT WAS RECOVERED FOLLOWING A GEAR UP LANDING	. THE ACFT COMPLETED 8 TOUCH AND GOES PRIOR TO FAILURE. THE WHEEL BEARINGS HAD BEEN CLEANED, INSPECTED, AND GREASED 27	 HOURS AND 47 LANDINGS PRIOR TO THE FAILURE. THE BEARING CONE WAS ORIGINAL EQUIPMENT AND HAD ACCUMULATED 2,303 LANDINGS	.	1	L	7	2 	3T			RT	3A20 					 
1996032200443	19960322	00443	EA 	1996	3	22	96ZZZX1253 	2	19951228	G	7414	1038255514	MAGNETO 	BENDIX 		CESSNA	172 	172 	2072402	CE 	LYC 	O320 	O320H2AD 	41508	EA 					ROTOR GEAR	TEETH SHEARED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	734PF		702 		3040587	17269001	L141476			AT 702 HOURS SINCE MAGNETO OVERHAUL, A TOOTH ON THE GEAR ASSY SHEARED, AND, SUBSEQUENTLY, SHEARED THE MAJORTIY OF THE RE	MAINING TEETH ON THAT GEAR AS WELL AS THE OTHER GEAR ASSY. REGARDING THE OVERHAUL PROCEDURES, THE GEAR ASSYS ARE NOT A 	MANDATORY REPLACEMENT ITEM DURING OVERHAUL. NOTING DISCOLORATION AND GENERAL BRITTLE CONDITION OF THE NYLON GEAR MATERI	AL, SUBMITTER SUSPECTS HEATING/COOLING CYCLES AND GENERAL AGING OF NYLON MAY HAVE CONTRIBUTED TO THIS FAILURE. RECOMMEN	D A MANDATORY REPLACEMENT OF THIS PART DURING ALL OVERHAULS.		1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1996032200465	19960322	00465	SO 	1996	3	22	96ZZZX1275 	2	19950801	G	7414	K3984	CONDENSOR 	SLICK 	6320 	CESSNA	206 	TU206F 	2073353	CE 	CONT 	O520 	TSIO520C 	17040	SO 					MAG	LEAD BROKEN 	B			RH6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	1031V	57 			94040049	U20602409	178171R			CONNECTION BETWEEN CONDENSER AND CONDENSER LEAD WAS BROKEN DUE TO CORROSION FROM AMBIENT AIR CAUSING MAG FAILURE.						1	H	7	1 	3O	3	O		A4CE 	E8CE				 
1996011200038	19960112	00038	EU 	1996	1	12	96ZZZX131 	1	19951130	G	6520	4619211901	HOUSING 		4619003003 	BOLKMS	105 	BO105CBS 	5626008	EU 										RT MOUNT STUD	CRACKED 	B	S	A	ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5416F	2907 			1044	794				DAILY INSPECTION FOUND TAIL ROTOR GEAR BOX CASE CRACKED AT RIGHT MOUNTING STUD.						1	G	7	2 	3U			NC	H3EU 					 
1996011200039	19960112	00039	CE 	1996	1	12	96ZZZX132 	1	19951214	G	3230	6607A837B	PRESSURE SWITCH 			BEECH 	99 	C99 	1154006	CE 										RT MLG	MALFUNCTIONED 	A			GUUA	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			SO	19	7209W				H417	U224				MIA/MIA - FLT 209 (TRAINING) - PILOT REPORT: RIGHT MAIN GEAR REQUIRES SEVERAL CYCLES TO RETRACT. MAINTENANCE: REMOVED	 AND REPLACED POWERPACK HYDRAULIC PRESSURE SWITCH. GEAR SWINGS GOOD. TEST FLIGHT SATISFACTORY.					1	L	7	2 	3T				A14CE 					 
1996032200929	19960322	00929		1996	3	22	96ZZZX1327 	4	19950731	G	3442	40008310105	TRANSCEIVER 			BELL 	212 	212 	1181420	SW 										RADAR	INOPERATIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	705H	24 			4236	35088				RADAR TRANSCEIVER SEARCH 3 INOPERATIVE.						1	G	7	1 	4U				H4SW 					 
1996032900333	19960329	00333	SW 	1996	3	29	96ZZZX1362 	1	19951106	G	5743	1750301	FITTING 			GULSTM	112 	112TC 	7630306	SW 										MLG TRUNNION	BOLT LOOSE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	4613W	2647 				13103				PILOT WAS PULLING AIRCRAFT OUT OF HANGAR WHEN HE NOTICED THE RT MAIN GEAR WOBBLE FORE AND AFT. UPON CLOSER INVESTIGATIO	N, FOUND 3 OF THE 4 'AN' 4-7A BOLTS HAD BACKED ALL THE WAY OUT. SUBMITTER RECOMMENDS BOLT REPLACEMENT WITH 'AN' 4-7 AND	 SAFETY WIRE IN PLACE AS THIS COULD CAUSE THE GEAR TO FAIL.				1	L	7	1 	3O				A12SO 					 
1996032900338	19960329	00338	CE 	1996	3	29	96ZZZX1367 	1	19951121	G	3310	63183552	CIRCUIT BOARD 			CESSNA	525 	525 	2076601	CE 										COCKPIT FLOODS	BURNED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	26CB	40 				5250117				CUSTOMER REPORTED NO COCKPIT FLOOD LIGHTS. INVESTIGATION REVEALED THE THRUST ATTENTUATOR CIRCUIT BOARD WAS BURNED. THE	 FLOOD LIGHT RESISTOR HAD BURNED THROUGH. INSTALLED NEW BOARD AND RETURNED TO SERVICE.					1	L	7	2 	4F			RT	A1WI 					 
1996032900357	19960329	00357	GL 	1996	3	29	96ZZZX1386 	2	19951201	G	7250		TURBINE 								ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	OVER TEMP 	D				K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			WP	07	911FT	5426 	431 		CAT37550		CAE836410			DURING NORMAL SHUT DOWN, PILOT ROLLED THROTTLE TO FLIGHT IDLE, NOTICED ENGINE OUT WARNING LIGHT, N1 DECAY, BUT TOT RISIN	G. PILOT MOTORED ENGINE, BUT TEMPERATURE EXCEEDED 1,000 DEGREES CELSIUS. AIRCRAFT RIGGING CHECKED OK. REPLACED TURBIN	E AND G.P. FUEL CONTROL. ALLISON REPORTS A134713 AND A134714 FILED RESPECTIVELY.									3	U			E4CE				 
1996040500003	19960405	00003	SW 	1996	4	5	96ZZZX1392 	1	19950903	G	6410	206016201127	BLADE 			BELL 	206 	206L3 	1182108	SW 										TIP BLOCK	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	726H		87 		CS3793	51548				TAIL ROTOR BLADE VOIDED AT TIP BLOCK.						1	G	7	1 	3U				H2SW 					 
1996010500263	19960105	00263	WP 	1996	1	5	96ZZZX14 	1	19951026	G	7603		THROTTLE 			DOUG 	DC9 	DC932 	3022066	WP 										PEDESTAL	MISRIGGED 	B	S		SH6Y	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	03	8270A					47037				MAINTENANCE INSPECTION FOUND FUEL SHUT-OFF AND THROTTLE CONTROLS MISRIGGED.						2	L	7	2 	4F				A6WE 					 
1996011200212	19960112	00212	CE 	1996	1	12	96ZZZX141 	1	19951106	G	3250	550140802	CAPACITOR 	JET 	CA400 	LEAR 	35 	35A 	5170602	CE 										C13,C18,C22	MISINSTALLED 	B		A	JGVR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	09	32HM				1564	187				IN REFERENCE TO J.E.T. NOSE STEERING COMPUTERS CA-400A, FOUND ELECTROLYTIC CAPACITORS INSTALLED BACKWARDS. RECURRING PR	OBLEM WITH CAPACITORS C13, C18, C22 BEING INSTALLED REVERSE POLARITY. COMMON SQUAWKS ARE INTERMITTENT OPERATION, UNABLE	 TO GET FULL NOSE STEERING TRAVEL, UNABLE TO CENTER NOSE GEAR, AND WANDERING WHEN TAXIING AIRCRAFT. SUBMITTER STATED MA	NY TIMES THE SQUAWK IS NOT DUPLICATED ON THE TEST BENCH, BUT CHANGING THE CAPACITORS SOLVES THE PROBLEM ON THE AIRCRAFT.	 THE PARTS LIST AND SCHEMATIC IN J.E.T. MANUAL TP-266 DO NOT INDICATE THE CAPACITORS ARE POLARITY SENSITIVE, BUT THEIR 	PHYSICAL APPEARANCE INDICATES THEY ARE.	2	L	7	2 	4F				A10CE 					 
1996040500027	19960405	00027	SW 	1996	4	5	96ZZZX1416 	1	19951208	G	6410	20601620131	BLADE 			BELL 	206 	206L1 	1182107	SW 										T/R	BEARING DEFECT 	B			ZV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2611	543 			CS452	45417				DURING ROUTINE MAINTENANCE, FOUND TAIL ROTOR BLADE INBOARD BEARING CRACKED ON BLADE, SN 452, AND SMALL INDICATION ON INB	OARD BEARING, SN 446.					1	G	7	1 	3U				H2SW 					 
1996040500028	19960405	00028	SW 	1996	4	5	96ZZZX1417 	1	19951208	G	6410	20601620131	BLADE 			BELL 	206 	206L1 	1182107	SW 										T/R	BEARING DEFECT 	B			ZV1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2611	543 			CS446	45417				DURING ROUTINE MAINTENANCE, FOUND TAIL ROTOR BLADE INBOARD BEARING CRACKED ON BLADE, SN 452, AND SMALL INDICATION ON INB	OARD BEARING, SN 446.					1	G	7	1 	3U				H2SW 					 
1996011200213	19960112	00213	EU 	1996	1	12	96ZZZX142 	1	19951031	G	5551	4453513	FITTING 			ISRAEL	1124 	1124 	4500102	EU 										STAB SCISSOR MT	CRACKED 	B		A	EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	651E					406				THE HORIZONTAL STABILIZER UPPER SCISSOR MOUNT HAS TWO CRACKS, ONE AT EACH MOUNTING LUG. SUBMITTER SUSPECTS CAUSE A RESU	LTANT OF HEAVY TAIL-PLANE VIBRATIONS. RECOMMEND C/W SB 1124-55-124.					2	M	7	2 	4F				A2SW 					 
1996011200214	19960112	00214	EU 	1996	1	12	96ZZZX143 	1	19951031	G	5610	3430213	WINDOW 			ISRAEL	1124 	1124 	4500102	EU 										PILOT EYEBROW	CRACKED 	B		A	EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	651E					406				FOUND 2 INCH CRACK IN THE PILOT'S EYEBROW WINDOW AT THE LOWER FORWARD CORNER. SUSPECTS MISS-DRILLED HOLES CAUSING BOLTS	 TO LOAD UP ON WINDOW WHEN A/C PRESSURIZES.					2	M	7	2 	4F				A2SW 					 
1996011200215	19960112	00215	EU 	1996	1	12	96ZZZX144 	1	19951031	G	5610	34302618	SPACER 			ISRAEL	1124 	1124 	4500102	EU 										RT WINDSHIELD	CRACKED 	B		A	EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	651E					406				CO-PILOT'S WINDSHIELD, THE SPACER BETWEEN THE INNER AND OUTER PANELS, WAS FOUND CRACKED IN HALF. UNAIRWORTHY PER MANUFA	CTURE. SUSPECT WINDSHIELD NOT BEING ALLOWED TO FLEX IN PLACES FROM BOLTS BINDING IN HOLES WHEN THE AIRCRAFT IS PRESSURI	ZED.				2	M	7	2 	4F				A2SW 					 
1996011200217	19960112	00217	EU 	1996	1	12	96ZZZX146 	1	19951204	G	2741	6052A2	TRANSMITTER 			BAC 	111 	111419EP 	1480280	EU 										ELEV POSITION	MISOVERHAULED 	B			AMCR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	09	524AC					BAC120				AFTER TROUBLESHOOTING AN AUTOPILOT PROBLEM, ORDERED AN ELEVATOR FOLLOW-UP TRANSMITTER ON AN EXCHANGE BASIS REQUESTING AN	 OVERHAULED UNIT. AFTER RECEIVING THE PART, THE UNIT WAS NOT OVERHAULED, BUT MERELY 'FUNCTIONALLY TESTED' BACK IN 1989.	 THE NULL INDEX WAS 90 DEGREES OFF, SAFETY WIRE WAS BROKEN, THE SERIAL NUMBER SCRIBED IN THE CASE DID NOT MATCH THE PLA	CARD STICKER. THERE WAS NO OTHER PAPERWORK WITH THE UNIT.			2	L	7	2 	4F				A5EU 					 
1996011200218	19960112	00218	EU 	1996	1	12	96ZZZX147 	1	19951214	G	2460	LDA150A8C	CONTACTOR 	LUCAS 		BRAERO	DH125 	BAE125800A 	1500285	EU 										BUS TIE CONTACT	STUD BROKE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	747UP		890 		F4220	258072				STUD FOR PS1 BUS BAR BROKE IN TWO. SUBMITTER STATED LOOKS LIKE A MANUFACTURER'S FLAW IN THE METAL AS IT LOOKS CRYSTALIZ	ED.					2	L	7	2 	4F			RT	A3EU 					 
1996011200219	19960112	00219	CE 	1996	1	12	96ZZZX148 	1	19951121	G	2435	23076001	STARTER 	LUCAS 		CESSNA	501 	501 	2076603	CE 										ARMATURE	SHORTED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	1HA		250 		362	5010072				CUSTOMER COMPLAINED OF SLOW STARTS. DISASSEMBLED STARTER/GENERATOR AND FOUND THE FOLLOWING: FOUND SPUR GEAR INSTALLED 	BACKWARDS, ARMATURE SHORTED, STATOR SHORTED, AND BRUSHES WORN. COMPLETED OVERHAUL ON THE STARTER/GENERATOR AND RETURNED	 TO CUSTOMER.				1	L	7	2 	4F				A27CE 					 
1996040500421	19960405	00421	NE 	1996	4	5	96ZZZX1486 	2	19950627	G	7250	430144801	BEARING 			BOLKMS	117 	BK117A4 	5626017	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 3	LEAKING 	B			R7MR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	118LF	328 			0492451	7137	LE45134			BEARING LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996040500422	19960405	00422	NE 	1996	4	5	96ZZZX1487 	2	19950627	G	7230	430135702	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	11	118LF	328 			321	7137	LE45134			BEARING LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996040500423	19960405	00423	EU 	1996	4	5	96ZZZX1488 	1	19951114	G	8011	P711982	SHAFT 	AUXILEC 		SNIAS 	350 	AS350B 	8680801	EU 										STARTER	CORRODED 	B			R7MR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	11	21UM					1674				STARTER SHAFT RECEIVED IN UNACCEPTABLE CONDITION. EXCESSIVE CORROSION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1996040500424	19960405	00424	NM 	1996	4	5	96ZZZX1489 	1	19950929	G	2120	900P3250179101	DUCT 			DOUG 	MD900 	MD900 	3027375	NM 										AIR DIST	CRUSHED 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF	100 				90000012				DUCT CRUSHED AND FAILS TO HOLD PROPER SHAPE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)						1	G	7	2 	3U			NC	H19NM 					 
1996011200220	19960112	00220	CE 	1996	1	12	96ZZZX149 	1	19951222	G	2731	55657561	WHEEL 			CESSNA	500 	550 	2076604	CE 										ELEV TRIM IND	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	35HC	4200 				5500151				ELEVATOR TRIM WHEEL 'GROOVES' FOR TRIM INDICATOR ARE BROKEN. SUBMITTER STATED THIS IS DANGEROUS AS IT GIVES A 'FALSE' T	RIM READING. PART SHOULD BE MADE FROM ALUMINUM.					1	L	7	2 	4F				A22CE 					 
1996040500425	19960405	00425	NE 	1996	4	5	96ZZZX1490 	2	19951111	G	7230	A311670001	COMPRESSION RING			DOUG 	MD900 	MD900 	3027375	NM 	PWA 	PW206 	PW206A 		NE 					ENGINE	LOOSE 	B			R7MR	K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			NM	11	901CF	175 				90000012	PCE206042			COMPRESSION RING LOOSENED UP WHICH CAUSED ENGINE LOW POWER. PWC HAS DEVELOPED AND WILL INSTALL ON THE ENGINE A RETROFIT	 KIT THAT INCORPORATES A DOWEL WHICH IS SUPPOSED TO RESTRICT MOVEMENT OF THE COMPRESSION RING.					1	G	7	2 	3U	3	U	NC	H19NM 	E42NE				 
1996040500426	19960405	00426	NE 	1996	4	5	96ZZZX1491 	2	19951020	G	7313	3039260	NOZZLE SET 			DOUG 	MD900 	MD900 	3027375	NM 	PWA 	PW206 	PW206A 		NE 					RT ENGINE	DEFECTIVE 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF	118 			1TK06508	90000012	PCE206042			HYBRID FUEL NOZZLE SET DEFECTIVE. SIL PW200-002. REMOVED DUE TO CARBON ACCUMULATION THAT COULD CAUSE ENGINE START DIFF	ICULTY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.					1	G	7	2 	3U	3	U	NC	H19NM 	E42NE				 
1996040500427	19960405	00427	NE 	1996	4	5	96ZZZX1492 	2	19951020	G	7313	3039260	NOZZLE SET 			DOUG 	MD900 	MD900 	3027375	NM 	PWA 	PW206 	PW206A 		NE 					RT ENGNE	DEFECTIVE 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF	118 			1TK06497	90000012	PCE206042			NOZZLE SET DEFECTIVE. SIL PW200-002. REMOVED DUE TO CARBON ACCUMULATION THAT COULD CAUSE ENGINE START DIFFICULTY. REP	LACED WITH NEW UNIT, CORRECTED PROBLEM.					1	G	7	2 	3U	3	U	NC	H19NM 	E42NE				 
1996040500428	19960405	00428	NE 	1996	4	5	96ZZZX1493 	2	19951020	G	7313	3039260	NOZZLE SET 			DOUG 	MD900 	MD900 	3027375	NM 	PWA 	PW206 	PW206A 		NE 					LT ENGINE	DEFECTIVE 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF	141 			1TK06505	90000012	PCE206018			NOZZLE SET DEFECTIVE. SIL PW200-002. REMOVED DUE TO CARBON ACCUMULATION THAT COULD CAUSE ENGINE START DIFFICULTY. REP	LACED WITH NEW UNIT, CORRECTED PROBLEM.					1	G	7	2 	3U	3	U	NC	H19NM 	E42NE				 
1996040500429	19960405	00429	NE 	1996	4	5	96ZZZX1494 	2	19951020	G	7313	3039260	NOZZLE SET 			DOUG 	MD900 	MD900 	3027375	NM 	PWA 	PW206 	PW206A 		NE 					LT ENGNE	DEFECTIVE 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF	141 			1TK06498	90000012	PCE206018			NOZZLE SET DEFECTIVE. SIL PW200-002. REMOVED DUE TO CARBON ACCUMULATION THAT COULD CAUSE ENGINE START DIFFICULTY. REP	LACED WITH NEW UNIT, CORRECTED PROBLEM.					1	G	7	2 	3U	3	U	NC	H19NM 	E42NE				 
1996040500430	19960405	00430	NE 	1996	4	5	96ZZZX1495 	2	19951120	G	7421	3039852	IGNITER 	CHAMPION 		DOUG 	MD900 	MD900 	3027375	NM 	PWA 	PW206 	PW206A 		NE 					LT ENGINE	WORN 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF	198 				90000012	PCE206018			IGNITER WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	NC	H19NM 	E42NE				 
1996040500431	19960405	00431	NE 	1996	4	5	96ZZZX1496 	2	19950926	G	7250	311450201	SHIELD 			DOUG 	MD900 	MD900 	3027375	NM 	PWA 	PW206 	PW206A 		NE 					ENGINE	CRACKED 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF	100 				90000012	PCE206018			SHIELD CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WTIH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	NC	H19NM 	E42NE				 
1996040500432	19960405	00432	NM 	1996	4	5	96ZZZX1497 	1	19951030	G	2140	900P3250219101	CONTROL CABLE 			DOUG 	MD900 	MD900 	3027375	NM 										HEATER	FAILED 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF					90000012				PILOT REPORTS THAT WHILE ACTIVATING THE HEATER CABLE, THE LOCKING MECHANISM CAME FREE FROM THE CONTROL KNOB. HEATER CON	FIGURATION WAS CHANGED.					1	G	7	2 	3U			NC	H19NM 					 
1996040500433	19960405	00433	NM 	1996	4	5	96ZZZX1498 	1	19951120	G	6230	900C2010183105	LINK ASSY 			DOUG 	MD900 	MD900 	3027375	NM 										DRV SCISSORS	WORN 	B			R7MR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	901CF	198 				90000012				LINK ASSY TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U			NC	H19NM 					 
1996040500434	19960405	00434	EU 	1996	4	5	96ZZZX1499 	1	19950908	G	7712	408104915	TORQUEMETER 			BOLKMS	117 	BK117B1 	5626012	EU 										RT NR 2	SHAFT 	B			R7MR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	11	911VU					7141				TORQUEMETER SHAFT RECEIVED IN DEFECTIVE CONDITION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1996010500264	19960105	00264	GL 	1996	1	5	96ZZZX15 	3	19951214	G	6114	C9822	SPIDER 													HARTZL	HCA2X	HCA2XK2 	GL 	HUB ARM	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17					H349			H349		SPIDER SUPPLIED TO SHOP FOR OVERHAUL. INSPECTION OF SPIDER FOUND IT CRACKED AT HUB ARM.																5	C	P908	 
1996011200221	19960112	00221	NM 	1996	1	12	96ZZZX150 	1	19951129	G	2782	QAR44806	GEAR ASSY 	SUNDSTRANDEM	755299A 	BOEING	757 	757* 		NM 										LE SLAT ACTUATOR	BEARING SEIZED 	B			VOVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	2FOR				A2642					NEEDLE BEARING FROZE TO PLANET GEAR. REMOVED BEFORE DAMAGE TO CARRIER OCCURRED, SUNSTRAND SB 27-15. REPLACES NEEDLE BE	ARINGS AND PINS WITH CORROSIVE RESISTANT MATERIAL. PRODUCT IMPROVEMENT. SUSPECT CAUSE, WATER IN ACTUATOR DUE TO BEING 	VENTED. CAUSED LOCK-OUT OF SLATS.				2	L	7	2 	4F			RT	A2NM 					 
1996011200222	19960112	00222	NM 	1996	1	12	96ZZZX151 	1	19951129	G	2782	5007404	GEAR ASSY 	SUNDSTRANDEM	755299B 	BOEING	757 	757* 		NM 										LE SLAT ACTUATOR	WATER CONTAM 	B			VOVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	2FOR				3524					GEAR SET CONTAMINATED WITH WATER DUE TO VENTED DESIGN OF ACTUATOR. ACTUATOR PREVIOUSLY HAD SB 27-15 ACCOMPLISHED. PLAN	ET CARRIER ASSY IN GOOD CONDITION. REPLACED PART DUE TO WATER.					2	L	7	2 	4F			RT	A2NM 					 
1996040500637	19960405	00637	SO 	1996	4	5	96ZZZX1514 	1	19951226	G	3710	B351	FILTER 			PIPER 	PA32 	PA32RT300T 	7103216	SO 										VAC REG VLV	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	39602	2170 				32R7887117				DURING ANNUAL INSPECTION FOUND THAT VACUUM SYSTEM REGULATOR FILLER WAS BLACK IN COLOR. DURING REMOVAL, FILTER DISINTEGR	ATED. THERE WAS NO LOG ENTRY TO INDICATE THIS FILTER WAS EVER CHANGED. IT IS IN A DIFFICULT AREA TO ACCESS AND WAS PR	OBABLY THE REASON IT WAS NEVER CHANGED.				1	L	7	1 	3O				A3SO 					 
1996011200223	19960112	00223	NM 	1996	1	12	96ZZZX152 	1	19951129	G	2782	QAR44806	GEAR ASSY 	SUNDSTRANDEM	755299A 	BOEING	757 	757* 		NM 										LE SLAT ACTUATOR	BEARING FROZE 	B			VOVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	2FOR				A2722					NEEDLE BEARING FROZE IN PLANET GEAR ASSY CAUSING CARRIER TO BECOME INOPERATIVE. PIN ELONGATED MATING HOLES IN CARRIER. 	 SUNSTRAND SB 27-15 REPLACES NEEDLE BEARING AND PIN WITH CORROSIVE RESISTANT MATERIAL. PRODUCT IMPROVEMENT. SUSPECT CA	USE, WATER IN ACTUATOR DUE TO ACTUATOR BEING VENTED DESIGN. DEFECT CAUSED SLAT LOCK-OUT.				2	L	7	2 	4F			RT	A2NM 					 
1996040500646	19960405	00646	SO 	1996	4	5	96ZZZX1523 	2	19951120	G	8520	634505	CRANKCASE NUT 			CESSNA	421 	421B 	2076014	CE 	CONT 	O520 	GTSIO520H 	17032	SO 					ENGINE	CRACKED 	D				O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			SW	99	400BJ					421B0819	235163R			PILOT REPORTED OIL PRESSURE FLUCTUATION DURING FLIGHT, BUT NEVER OUT OF GREEN ARC. UPON LANDING, NOTED ENGINE HAD HAD A	 MAJOR OIL LEAK. UPON INVESTIGATION, FOUND ONE OF THE THROUGH-BOLT NUTS HAD CRACKED, THIS WAS LOCATED ON THE FWD LOWER 	PART OF THE CASE. THE ENGINE HAD LOST ALMOST 6 QUARTS OF 0.1 ON A ONE-HOUR FLIGHT. LOOKING AT NUT WITH A 10-POWER MAGN	IFYING GLASS, NOTED A LOT OF MACHINING MARKS LEFT ON IT.			1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1996040500650	19960405	00650	SO 	1996	4	5	96ZZZX1527 	1	19951211	G	7160	BA104	AIR FILTER 	BRACKETT 		PIPER 	PA28 	PA28180 	7102808	SO 										ENG INTAKE	COLLAPSED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	4819T					287205201				FOUND UNIT WAS INSTALLED WITHOUT THE METAL/WIRE FRAME AND HAD COLLAPSED ALLOWING UNFILTERED AIR TO THE ENGINE. THERE WA	S THE POSSIBILITY OF THE FILTER BEING SUCKED INTO THE AIRBOX/HEATER VALVE AREA.					1	L	7	1 	3O				2A13 					 
1996011200224	19960112	00224	NM 	1996	1	12	96ZZZX153 	1	19951129	G	2782	QAR44806	GEAR ASSY 	SUNDSTRANDEM	755299 	BOEING	757 	757* 		NM 										LE SLAT ACTUATOR	BEARING FROZE 	B			VOVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11	2FOR				0161					NEEDLE BEARINGS FROZE CAUSING PINS IN 3 PLACES IN PLANET GEAR TO ELONGATE CARRIER HOLES BEYOND TOLERANCE. SCRAP COMPLET	E ASSY. CURRENTLY, NEEDLE BEARINGS AND PIN BEING REPLACED WITH PRODUCT IMPROVEMENT CORROSIVE RESISTANT MATERIAL PER SUN	DSTRAND SB 27-15. ALSO, CAUSED WEAR IN OUTPUT SHAFT CAUSING REPLACEMENT OF SAME. SUSPECT CAUSE IS WATER IN ACTUATOR WH	ICH IS VENTED CAUSING RUST TO FORM WHICH CAUSES LOCK-OUT OF SLATS.			2	L	7	2 	4F			RT	A2NM 					 
1996040500653	19960405	00653	EU 	1996	4	5	96ZZZX1530 	2	19950820	G	8500		ENGINE 			AMTR 	KITFOX	KITFOX 	05613LZ	GL 	ROTAX 	582 	ROTAX582 	55555	EU 					IGNITION	FAILED 	G				O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			GL	03	548CM	162 				1548				IT WAS REPORTED AN ENGINE BEARING FAILED CAUSING THE INTERNAL TIMING TO CHANGE LEADING TO ENGINE STOPPAGE DUE TO INCORRE	CT IGNITION TIMING.					1	H	7	1 	3I	3	I	NC	EXPA1H71	EXPE3I				 
1996040500656	19960405	00656	CE 	1996	4	5	96ZZZX1533 	1	19950510	G	3297		WIRE 			CESSNA	404 	404CESSNA 	2075901	CE 										LT MLG	BROKEN 	D				O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			SW	99	50424					4040133				WHEN GEAR WAS EXTENDED, LEFT GREEN LIGHT DID NOT COME ON. AFTER INSPECTION, FOUND GROUND WIRE BROKEN (ATTACHES TO FRAME	).					1	L	7	2 	3O			 	A25CE 					 
1996040500666	19960405	00666	SO 	1996	4	5	96ZZZX1543 	2	19951213	G	8550	12509211	ADAPTER 			CESSNA	210 	210L 	2073448	CE 	CONT 	O520 	IO520L 	17032	SO 					OIL FILTER	OIL LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	09	711TM	4155 				21061301	242851R			UPON INSPECTION OF OIL FILTER ADAPTER IAW CESSNA SEB 93-1-R1, FOUND FILTER ADAPTER THREADS HAD PIECES MISSING. INSPECTI	ON WAS PROMPTED BY LOOSE RETAINING NUT AND OIL LEAK. THREADS ON THE ENGINE WERE INTACT. REPLACED FILTER ASSY WITH NEW 	CESSNA ASSY.				1	H	7	1 	3O	3	O		3A21 	E5CE				 
1996011200226	19960112	00226	EU 	1996	1	12	96ZZZX155 	1	19951123	G	3310	1179203103	DIMMER 			BOLKMS	117 	BK117A3 	5626015	EU 										LIGHTS CONTROL	FAILED 	D				K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			EA	03	117CJ					7051				COCKPIT CENTER CONSOLE INSTRUMENT LIGHTS' CONTROL UNIT (DIMMER BOX) FAILED CAUSING SMOKE. COMMON PROBLEM AREA. RECOMME	ND MFG RE-DESIGN CONTROL UNIT.					1	G	7	2 	3U				H13EU 					 
1996040500678	19960405	00678	NE 	1996	4	5	96ZZZX1555 	3	19951129	G	6114	D5170	PISTON ROD 													MCAULY	4HFR34	4HFR34C652 	NE 	PROP	HEAD LOOSE 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								880392		UPON PROPELLER INSPECTION, HEAD WAS FOUND LOOSE ON PISTON ROD ASSY.																6	C	3PNE	 
1996010500265	19960105	00265		1996	1	5	96ZZZX16 	4	19951211	G	6122	A135A	FLYWEIGHT ASSY 	HARTZL 		PIPER 	PA32 	PA32R300 	7103213	SO 										DRIVE HOLE	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	5390F	4074 			5650U	32R7680522				INSPECTION FOUND FLYWEIGHTS ARE CRACKED AT DRIVE HOLE IN BASE.						1	L	7	1 	3O				A3SO 					 
1996011200231	19960112	00231	SW 	1996	1	12	96ZZZX160 	1	19951226	G	3212	21470612001	FLOAT 			BELL 	214 	214ST 	1182106	SW 										EMERGENCY EQUIP	INFLATED 	G	L	A		A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			SW	03	8045T					28101				WHILE IN CRUISE FLIGHT OVER THE GULF OF MEXICO, ACFT EXPERIENCED UNCOMMANDED INFLATION OF EMERGENCY FLOATS. FLIGHT CREW	 DIVERTED ACFT TO THE NEAREST OFFSHORE HELIPORT AND MADE A SUCCESSFUL LANDING. MAXIMUM ALLOWABLE AIRSPEED FOR FLOAT INF	LATION IS 35 KNOTS. AT THE TIME OF INFLATION, ACFT WAS INDICATING APPROX 120 KNOTS. PILOT STATED THEY EXPERIENCED A SL	IGHT BUFFETING BEFORE ACFT WAS SLOWED DOWN. PILOT ALSO STATED THE FLOAT SYSTEM WAS NOT ARMED AT THE TIME OF INFLATION. 	 THE CAUSE OF THE UNCOMMANDED IN-FLIGHT INFLATION IS STILL UNDER INVESTIGATION. INFLATION VALVES WERE SENT TO VALVE MFG	 FOR FURTHER EVALUATION.	2	G	7	2 	4U				H10SW 					 
1996011200232	19960112	00232	SW 	1996	1	12	96ZZZX161 	1	19951210	G	3212	21470612001	FLOAT 			BELL 	214 	214ST 	1182106	SW 										EMERGENCY EQUIP	INFLATED 	G	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				AIRCRAFT EXPERINCED AN UNCOMMANDED EMERGENCY FLOAT INFLATION WHILE AIRCRAFT WAS ON THE GROUND AND UNATTENDED. THE INFLA	TION WAS INVESTIGATED BY THE OPERATOR AND A REPRESENTATIVE FROM BELL HELICOPTER. THE MANUFACTURER ATTRIBUTED THE STATIC	 INFLATION TO DEBRIS FOUND IN THE FLOAT INFLATION VALVES. THE VALVES (BELL PN 214-073-929-105) WERE THE IMPROVED VALVES	 INSTALLED IAW BELL TB 214ST-95-149.			2	G	7	2 	4U				H10SW 					 
1996011200233	19960112	00233	SO 	1996	1	12	96ZZZX162 	1	19950905	G	2740	452363	BEARING 			PIPER 	PA24 	PA24250 	7102404	SO 										STAB TORQUE TUBE	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	7969P	1394 				243206				NOTED LOOSENESS OF STABILATOR DURING ANNUAL. AD 94-13-10 ADDRESSES THIS PROBLEM. WHILE DIAGNOSING LOOSENESS, FOUND THE	 STABILATOR TORQUE TUBE BEARINGS WORN. THE TORQUE TUBE BEARING SUPPORT FITTINGS WERE FOUND OK PER THE AD. FOUND CORROS	ION BETWEEN BEARING AND OUTER RACE, WHICH CAUSED ADVERSE WEAR. REPLACED BEARINGS WHICH ELIMINATED LOOSENESS.				1	L	7	1 	3O				1A15 					 
1996011200234	19960112	00234	SW 	1996	1	12	96ZZZX163 	1	19951214	G	7120	590000517	MOUNT 			MOONEY	M20 	M20J 	5870219	SW 										ENG FIREWALL	CRACKED 	B	S	A	DYTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	189ER	5928 				24169814				DURING A ROUTINE ENGINE CHANGE, THE ENGINE MOUNT WAS FOUND CRACKED AT THE RT LOWER ATTACHMENT TO FIREWALL, AS WOULD BE V	IEWED FROM BEHIND AIRCRAFT.					1	L	7	1 	3O				2A3 					 
1996011200235	19960112	00235	CE 	1996	1	12	96ZZZX164 	1	19951018	G	2701	076001915	CONTROL WHEEL 			CESSNA	210 	210M 	2073450	CE 										LT SIDE	CORRODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	761GK	4869 				21062244				DURING ANNUAL INSPECTION, FOUND CORROSION ON PILOT CONTROL WHEEL. REMOVED WHEEL AND INSPECTED CORROSION. CORROSION HAD	 REMOVED METAL FROM THE FOLLOWING AREAS: AROUND BOTH LOWER BOLT HOLES AT BASE OF LT GRIP, AND AROUND MAP LIGHT OPENING.	 SUBMITTER STATED IF ALLOWED TO PROGRESS, CORROSION COULD ALLOW WHEEL TO BREAK RESULTING IN LOSS OF CONTROL OF AIRCRAFT	.			1	H	7	1 	3O				3A21 					 
1996011200236	19960112	00236	SO 	1996	1	12	96ZZZX165 	1	19951201	G	7160		AIR DOOR 			PIPER 	PA30 	PA30 	7103002	SO 										ALTERNATE AIR	DETACHED 	D		A		E				ENGINE SHUTDOWN 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			GL	27	7849Y	5180 				30929				ENGINE LOST POWER ON TAKEOFF. POST-SHUT DOWN AND LANDING, INVESTIGATION REVEALED ALTERNATE AIR DOOR CAME OFF ITS HINGES	 AND WAS SUCKED UP AGAINST METERING ORFICES IN THE VENTURI, PHYSICALLY STARVING THE ENGINE FOR AIR AND UPSETTING THE MET	ERING CAPABILITIES OF THE METERING UNIT. AIRCRAFT HAD 5,000 PLUS HOURS TOTAL TIME.				1	L	7	2 	3O				A1EA 					 
1996011200237	19960112	00237	CE 	1996	1	12	96ZZZX166 	1	19951125	G	3230	S20496FG	BEARING 		20410081 	CESSNA	177 	177RG 	2073709	CE 										MLG ACT ROD END	BROKEN 	D		A		O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			SO	15	34700	1008 				1013				MLG WOULD NOT FULLY EXTEND. WITH SECOND PILOT FLYING AIRCRAFT, PILOT USED A MODIFIED GOLF CLUB TO PULL GEAR INTO LOCK P	OSITION THROUGH OPENED PILOT'S DOOR. INVESTIGATION FOUND ROD END BEARING BROKEN. SUBMITTER RECOMMENDED AD BE ISSUED RE	MOVING THIS PART AND INSTALLING NEW MODIFIED PART THAT IS NOW AVAILABLE. THIS WOULD PREVENT A GEAR-UP LANDING.				1	H	7	1 	3O				A20CE 					 
1996011200238	19960112	00238	SO 	1996	1	12	96ZZZX167 	1	19951208	G	5551	8346402	BRACKET 			PIPER 	PA46 	PA46310P 	7104605	SO 										FWD HORIZ STAB	CORRODED 	B		A	LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9100Z	2312 				4608014				DURING INSPECTION, FOUND FORWARD HORIZONTAL STABILIZER BRACKETS EXFOLIATED. PIPER SB 962, WHICH PERTAINS TO THIS AREA, 	HAD BEEN PREVIOUSLY C/W. THESE BRACKETS ARE HARD TO SEE WITHOUT A MIRROR AND, LIKEWISE, ARE HARD TO CLEAN. SUBMITTER S	TATED THIS PROBLEM (CORROSION) IS CAUSED BY 2 THINGS: INCREASES OF MOISTURE INTO EMPENNAGE, AND DISSIMILAR METALS. BRA	CKETS ARE STEEL, STRUCTURE IS ALUMINUM. IT IS HIGHLY RECOMMENDED THIS BE A MANDATORY REPLACEMENT ITEM AFTER 2 YEARS OR 	EXPOSURE TO CORROSIVE ENVIRONMENT.		1	L	7	1 	3O				A25SO 					 
1996011200239	19960112	00239	SO 	1996	1	12	96ZZZX168 	1	19951208	G	5551	8346403	BRACKET 			PIPER 	PA46 	PA46310P 	7104605	SO 										FWD HORIZ STAB	CORRODED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9100Z	2312 				4608014				DURING INSPECTION, FOUND FORWARD HORIZONTAL STABILIZER BRACKETS EXFOLIATED. PIPER SB 962, WHICH PERTAINS TO THIS AREA, 	HAD BEEN PREVIOUSLY C/W. THESE BRACKETS ARE HARD TO SEE WITHOUT A MIRROR AND, LIKEWISE, ARE HARD TO CLEAN. SUBMITTER S	TATED THIS PROBLEM (CORROSION) IS CAUSED BY 2 THINGS: INCREASES OF MOISTURE INTO EMPENNAGE, AND DISSIMILAR METALS. BRA	CKETS ARE STEEL, STRUCTURE IS ALUMINUM. IT IS HIGHLY RECOMMENDED THIS BE A MANDATORY REPLACEMENT ITEM AFTER 2 YEARS OR 	EXPOSURE TO CORROSIVE ENVIRONMENT.		1	L	7	1 	3O				A25SO 					 
1996011200240	19960112	00240	CE 	1996	1	12	96ZZZX169 	1	19951116	G	2720	040010749	CONTROL CABLE 			CESSNA	150 	152 	2071835	CE 										RUDDER FS 184	FRAYED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	67824	6728 				15282039				DURING REPLACEMENT OF RUDDER PULLEYS IN EMPENNAGE, FOUND BOTH RUDDER CABLES FRAYED. THE RT CABLE WAS FRAYED AT STA 173 	WHERE IT PASSES OVER A PULLEY. THE FRAYING WAS NOT EVIDENT UNTIL PULLEY WAS REMOVED. THE LT CABLE HAD THE SAME CONDITI	ON AT STA 184. SUBMITTER RECOMMENDS CLOSE INSPECTION OF CABLES AT PULLEYS. SUSPECT CAUSE WAS ABRASION ON PULLEY AND HI	GH TOTAL TIME.			1	H	7	1 	3O			NT	3A19 					 
1996010500266	19960105	00266	GL 	1996	1	5	96ZZZX17 	3	19951211	G	6111	C35A	CLAMP 			GULSTM	500 	500RKWELL 	0141102	SW 						HARTZL	HC82V	HC82V* 	GL 	BOLT HOLE	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	89M	13185	970 		L7429	659		246MN		CLAMP HAS SUB-SURFACE CRACK INDICATION IN A321 BOLT HOLE.						1	H	7	2 	3O				6A1 		5	C	P23EA	 
1996011200241	19960112	00241	CE 	1996	1	12	96ZZZX170 	1	19951116	G	2720	040010750	CONTROL CABLE 			CESSNA	150 	152 	2071835	CE 										RUDDER FS 173	FRAYED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	67824	6728 				15282039				DURING REPLACEMENT OF RUDDER PULLEYS IN EMPENNAGE, FOUND BOTH RUDDER CABLES FRAYED. THE RT CABLE WAS FRAYED AT STA 173 	WHERE IT PASSES OVER A PULLEY. THE FRAYING WAS NOT EVIDENT UNTIL PULLEY WAS REMOVED. THE LT CABLE HAD THE SAME CONDITI	ON AT STA 184. SUBMITTER RECOMMENDS CLOSE INSPECTION OF CABLES AT PULLEYS. SUSPECT CAUSE WAS ABRASION ON PULLEY AND HI	GH TOTAL TIME.			1	H	7	1 	3O			NT	3A19 					 
1996011200242	19960112	00242	SO 	1996	1	12	96ZZZX171 	1	19950720	G	7922	75944	VALVE 			PIPER 	PA28 	PA28180 	7102808	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	53132	2725 				284615				DURING OIL CHANGE AND C/W TEXTRON LYCOMING MANDATORY SB 518C, FOUND THE VERNATHERM CRIMP NUT WAS EXTREMELY LOOSE. THE E	NGINE WAS OVERHAULED AT 1,642 HOURS AND THIS VALVE WAS NOT REPLACED AS RECOMMENDED BY THE MANUFACTURER. SUBMITTER SUGGE	STS SB 518C BE ACCOMPLISHED AT NEXT OIL CHANGE AND ALL LYCOMING VERNATHERM VALVES REPLACED AT OVERHAUL.				1	L	7	1 	3O				2A13 					 
1996041200710	19960412	00710	WP 	1996	4	12	96ZZZX1717 	2	19950821	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		35 			1233151943		P70105C			DURING INSPECTION/REPAIR FOR LOW POWER, FOUND SEAL PLATE CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO IN	CREASE SEAL PLATE TENSION AGAINST FIRST STAGE ROTOR ASSY. INCREASED TENSION ON THE SEAL FLANGE RESULTS IN CRACKING AT T	HE EDGE PROPAGATING RADIALLY INWARD. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING REVIEW CAUSE/EFFECT. NOTE: THIS IS 	A CRITICAL LIFE-LIMITED COMPONENT. LIMIT IS 20,000 CYCLES. THIS IS THE 9TH SEAL PLATE FOUND CRACKED. TOTAL CYCLES, 7,	427.							4	T			E4WE				 
1996041200711	19960412	00711	WP 	1996	4	12	96ZZZX1718 	2	19950706	G	7250	31038391	SEAL 		31038391 						GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		9235 			9233151501		P70013			FOUND SEAL CRACKED AT FLANGE APPROXIMATELY 14 PLACES. THIS IS A CRICITAL LIFE-LIMITED COMPONENT. LIMIT - 20,000 CYCLES	. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE/CORRECT CAUSE. THIS IS THE 12TH SEAL PLATE FOUND CRACKED AT T	HIS FACILITY. PART TOTAL CYCLES, 9,656.									4	T			E4WE				 
1996041200712	19960412	00712	WP 	1996	4	12	96ZZZX1719 	2	19950907	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		3556 			1233151957		P70129			DURING SCHEDULED INSPECTION, FOUND SEAL CRACKED AT FLANGE. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE I	NCREASED TENSION AGAINST THE FIRST STAGE ROTOR. THIS INCREASED TENSION RESULTS IN CRACKING AT THE SEAL FLANGE. SUBMITT	ER STATED THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE LIMIT - 20,000 CYCLES. THIS IS THE 13TH SEAL FOUND CRACKED. 	 TOTAL CYCLES, 3,550.								4	T			E4WE				 
1996011200243	19960112	00243	SO 	1996	1	12	96ZZZX172 	1	19951026	G	2720	4012302	CABLE ASSY 			PIPER 	J3 	J3C65 	7100510	SO 										RUDDER PEDAL	WRONG LENGTH 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	09	87873					15491				WITH RUDDER PEDAL IN NEUTRAL POSITION, RUDDER WAS AT ALMOST FULL LEFT DEFLECTION. UPON INVESTIGATION, FOUND THAT RUDDER	 CABLES HAD BEEN REPLACED AND WERE OF DIFFERENT LENGTHS. SUBMITTER STATED FAILURE TO FOLLOW AIRWORTHY PRACTICES WAS THE	 OBVIOUS CAUSE. REPLACED CABLES WITH CURRENT PART NUMBERS AND RIGGED SYSTEM.				1	H	7	1 	3O				A691 					 
1996041200713	19960412	00713	WP 	1996	4	12	96ZZZX1720 	2	19950928	G	7250	31038391	SEAL 		31033152 						GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		10385			9233151437		P70010C			DURING SCHEDULED HOT SECTION INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE APPROXIMATELY 19 PLACES. SUGGEST ALLIED SIGNA	L ENGINEERING REVIEW PROBLEM. SUBMITTER STATED THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE LIMIT - 20,000 CYCLES. 	 THIS IS THE 16TH ROTATING AIR SEAL FOUND CRACKED, 16TH M OR D REPORT FILED ON THIS PART. PART TOTAL CYCLES 10,734.									4	T			E4WE				 
1996041200714	19960412	00714	WP 	1996	4	12	96ZZZX1721 	2	19951004	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		6487 			1233152025		P70087C			DURING REPAIR, FOUND AIR SEAL CRACKED AT SEAL FLANGE. CRACK RESULTED IN .025 INCH DEFLECTION OF SEALING FLANGE AND CORR	ESPONDING LOSS OF TURBINE SECTION COOLING AIR AROUND ENTIRE DIAMETER OF SEAL CAUSING SECONDARY DAMAGE TO TURBINE SECTION	 COMPONENTS. THIS IS A CRITICAL SERVICE, LIFE-LIMITED COMPONENT. LIMIT - 20,000 CYCLES. TOTAL CYCLES, 7,920.									4	T			E4WE				 
1996041200715	19960412	00715	WP 	1996	4	12	96ZZZX1722 	2	19950823	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		5482 			1233151991		P70113C			FOUND SEAL FLANGE CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO INCREASE TENSION AGAINST 1ST STAGE ROTOR.	 INCREASED TENSION RESULTS IN CRACKING AT THE SEAL FLANGE. SUBMITTER STATES THIS IS A CRITICAL SERVICE, LIFE-LIMITED C	OMPONENT. LIMIT - 20,000 CYCLES. PART TOTAL CYCLES, 5,574.									4	T			E4WE				 
1996041200716	19960412	00716	WP 	1996	4	12	96ZZZX1723 	2	19951127	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		7517 			1233151982		P70086C			DURING SCHEUDLED CAM INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE. THIS IS A MAIN ROTATING GROUP. CRITICAL LIFE-LIMIT 	IS 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE AND CORRECT THE CAUSE OF THIS PROBLEM. THIS I	S THE 21ST MALFUNCTION/DEFECT REPORT FILED BY THIS REPAIR STATION ON THIS TOPIC. PART TOTAL CYCLES, 9,199.									4	T			E4WE				 
1996041200717	19960412	00717	WP 	1996	4	12	96ZZZX1724 	2	19951207	G	7250	31038391	SEAL 								GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		10508			9233151457		P70018			DURING SCHEDULED HOT SECTION INSPECTION, FOUND AIR SEAL CRACKED AT SEALING FLANGE. THIS IS A CRITICAL LIFE-LIMITED COM	PONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE/CORRECT CAUSE OF CRACKING.	 THIS IS THE 22ND MALFUNCTION/DEFECT REPORT SUBMITTED ON THIS TOPIC BY THIS REPAIR STATION ALONE. PART TOTAL CYCLES, 1	0,865.								4	T			E4WE				 
1996041200718	19960412	00718	WP 	1996	4	12	96ZZZX1725 	2	19951207	G	7250	31038391	SEAL 								GARRTT	TPE331	TPE33112UHR 		WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		9710 			9233151419		P70029			DURING SCHEDULED HOT SECTION INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. L	IFE-LIMIT - 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE AND CORRECT CAUSE OF CRACKING. THIS 	IS THE 23RD MALFUNCTION/DEFECT REPORT SUBMITTED BY THIS REPAIR STATION ON THIS TOPIC. PART TOTAL CYCLES, 10,026.									4	T			E4WE				 
1996011200244	19960112	00244	CE 	1996	1	12	96ZZZX173 	1	19951018	G	3230	12416345	DOWNLOCK HOOK 			CESSNA	210 	210M 	2073450	CE 										MLG	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	761GK	4869 				21062244				DURING ANNUAL INSPECTION, EXCESS PLAY WAS NOTICED IN MLG WHEN ON JACKS. MLG DOWNLOCK HOOKS WERE FOUND WORN AT PIVOT POI	NT. REPLACED WITH SERVICEABLE HOOKS AND REPLACED ATTACHING PINS (MS 20392 CLEVIS PINS).					1	H	7	1 	3O				3A21 					 
1996011200245	19960112	00245	EA 	1996	1	12	96ZZZX174 	2	19950905	G	7310	LW120980210	TUBE 			PIPER 	PA24 	PA24250 	7102404	SO 	LYC 	O540 	IO540C1B5 	41532	EA 					FUEL INJECTOR	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	09	7969P	1394 				243206	L35948			DURING C/W LYCOMING AD 93-02-05, FOUND ALL 6 FUEL INJECTOR LINES CRACKED AT SOLDER JOINT AND LEAKING FUEL. SUBMITTER NO	TED THAT ON PREVIOUS ANNUAL INSPECTION FORMS, A NOTATION WAS MADE THAT LINES WERE LEAKING, BUT DEFERRED. THE LEAKING LI	NES POSED A SERIOUS FIRE HAZARD AND SHOULD NOT HAVE BEEN DEFERRED. INSTALLED NEW LINES AND CLAMPED PER LYC SB 342A.				1	L	7	1 	3O	3	O		1A15 	1E4				 
1996011200246	19960112	00246	SO 	1996	1	12	96ZZZX175 	1	19950720	G	3233	18935	CYLINDER 	PARKERHANFIN	1117 	PIPER 	PA28 	PA28R201T 	7102813	SO 										NLG RETRACT	MISMANUFACTURED 	D				O				OTHER 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			GL	09	47664	39 			905	28R7703419				LANDING GEAR WOULD NOT RETRACT. FOUND NOSE GEAR RETRACT CYLINDER TO BE ALLOWING FLUID TO BYPASS, PREVENTING PRESSURE FR	OM BUILDING IN SYSTEM. UPON DISASSEMBLY OF CYLINDER, NO ABNORMALITIES WERE FOUND WITH O-RINGS' CYLINDER BORE FOUND TO B	E LARGER DIAMETER IN CENTER ALLOWING FLUID TO BYPASS O-RINGS. CYLINDER WAS MANUFACTURED 4-93.				1	L	7	1 	3O				2A13 					 
1996011200247	19960112	00247	EA 	1996	1	12	96ZZZX176 	2	19951031	G	7414	M3525	COIL 	SLICK 	4270 	CESSNA	172 	172M 	2072418	CE 	LYC 	O320 	O320E2D 	41508	EA 					ENG RT MAG	DEFECTIVE 	D				K				NONE 				Y			ENGINE STOPPAGE 			IN	INSP/MAINT 	1			GL	09	19992	582 			89050304	17260917	L4057227A			DURING RUN-UP, RT MAG DROP WAS EXCESSIVE OR ENGINE WOULD STOP. MAGNETO WAS DISASSEMBLED AND POINTS AND CONDENSOR REPLAC	ED DUE TO WORN CONDITION. COIL WAS TESTED AND THE SECONDARY WAS FOUND TO HAVE APPROXIMATELY 5 MILLION OHMS RESISTANCE. 	 THE SPEC IS 13,000-20,500 OHMS. UPON REMOVAL OF COIL, ALSO NOTED LAMINATIONS HAD STARTED TO SEPARATE. SUBMITTER RECOM	MENDS ADHERENCE TO SLICK MANUAL WHICH REQUIRED 500-HOUR INSPECTIONS. THERE WAS NO PREVIOUS WORK ON MAGS NOTED IN LOG BO	OK.		1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1996041800129	19960418	00129		1996	4	18	96ZZZX1761 	4	19951226	G	3421	5040017901	GYRO 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ATTITUDE	FAILED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LF	57 			1324	S663				GYRO IS TUMBLED AND SPINS OUT OF CONTROL WHEN POWER IS APPLIED. TIME SINCE OVERHAUL 57.3 HRS.						1	G	7	2 	3U				H3EU 					 
1996041800130	19960418	00130	SW 	1996	4	18	96ZZZX1762 	1	19951210	G	7810	212061202009	EXHAUST 			BELL 	212 	212 	1181420	SW 										AFT	CRACKED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	748H		1029 		920124	35060				EXHAUST STACK CRACK AT AFT LOWER PORTION.						1	G	7	1 	4U				H4SW 					 
1996041800131	19960418	00131	SW 	1996	4	18	96ZZZX1763 	1	19950730	G	6220	212010407109	SCISSORS ASSY 			BELL 	212 	212 	1181420	SW 										M/R	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	748H		22 		PR69	35060				SCISSOR ASSY BEARING CAP UNBEDED.						1	G	7	1 	4U				H4SW 					 
1996041800133	19960418	00133	NE 	1996	4	18	96ZZZX1765 	1	19951120	G	7810	23032325	COLLECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										ENGINE EXHAUST	DEFECTIVE 	B			YKER	K				NONE 				K	B		FLUID LOSS 	SMOKE/FUMES/ODORS/SPARKS 		IN	INSP/MAINT 	1			EA	17	911GH				35381	760108				ENGINE WAS REPORTEDLY LEAKING OIL AND SMOKING. UPON INVESTIGATION, FOUND THE NR 5 BEARING LABYRINTH SEAL AIR SUPPLY TUB	E ON THE EXHAUST COLLECTOR BROKEN. REPLACEMENT OF THE EXHAUST COLLECTOR CORRECTED THE PROBLEM.					1	G	7	2 	3U				H1NE 					 
1996041800134	19960418	00134	SW 	1996	4	18	96ZZZX1766 	1	19950610	G	6330	222331617101	ISOLATION MOUNT 			BELL 	222 	222U 	1182140	SW 										XMSN MOUNT	BROKEN 	B			W6HR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	415MA				BR355	47568				ISOLATION MOUNT IS BROKEN. THREADED BUSHING THAT ROD END ASSY THREADS INTO IS SEPARATED FROM ELASTOMERIC MATERIAL. DAT	E OF MANUFACTURE OF THIS PART WAS 5-29-93.					1	G	7	2 	3U				H9SW 					 
1996041800135	19960418	00135	SW 	1996	4	18	96ZZZX1767 	1	19951114	G	6330	LB6107881	BEARING 			BELL 	222 	222U 	1182140	SW 										NODAL BEAM	BROKEN 	B			W6HR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	429MA	743 			LK0345	45523				BEARING BROKEN. ELASTOMERIC BEARINGS ARE SEPARATED FROM THE INNER RACE OF THE BEARING. REPLACED WITH NEW BEARINGS IAW 	BHT T.B. 222U-91-57.					1	G	7	2 	3U				H9SW 					 
1996041800136	19960418	00136	SW 	1996	4	18	96ZZZX1768 	1	19951114	G	6330	LB6107881	BEARING 			BELL 	222 	222U 	1182140	SW 										NODAL BEAM	BROKEN 	B			W6HR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	429MA	743 			LK0423	45523				BEARING BROKEN. ELASTOMERIC BEARINGS ARE SEPARATED FROM THE INNER RACE OF THE BEARING. REPLACED WITH NEW BEARINGS IAW 	BHT T.B. 222U-91-57.					1	G	7	2 	3U				H9SW 					 
1996041800137	19960418	00137	NE 	1996	4	18	96ZZZX1769 	2	19951120	G	7321	2525013	DIAPHRAGM 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					AIR KEY	TORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3895U	2578 				31153	CPPS62345			DURING INSPECTION OF AIR REGULATOR, FOUND HOLE (TEAR) IN DIAPHRAGM OF AUTO FUEL CONTROL.						1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1996011200248	19960112	00248	SO 	1996	1	12	96ZZZX177 	2	19951026	G	7414	1076304	COIL 	BENDIX 	105136027 	PIPER 	J3 	J3C65 	7100510	SO 	CONT 	A65 	A658 	17003	SO 					RT MAGNETO	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	87873				782939	15491	4626268			WHILE DETERMINING C/W TELEDYNE AD 94-01-03R2, FOUND RIGHT MAGNETO TO HAVE AN UNAIRWORTHY COIL. UPON REMOVAL, COIL WAS F	OUND CRACKED IN TWO PLACES ORIGINATING FROM THE CORE ON THE GROUND LEAD END. LOG ENTRY OF 2-20-88 INDICATES THIS MAGNET	O COIL WAS CHANGED TO THE 'NEW STYLE', BUT DID NOT GIVE A PART NUMBER.				1	H	7	1 	3O	3	O		A691 	E205				 
1996011200249	19960112	00249	SO 	1996	1	12	96ZZZX178 	2	19951130	G	8540	643257	SHAFT TOOTH 		635050 	CESSNA	421 	421A 	2076012	CE 	CONT 	O520 	GTSIO520D 	17032	SO 					STARTER ADAPTER	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	2219Q	3658 	932 			421A0019	1884908D			PILOT REPORTED LOWER OIL PRESSURE, RT ENGINE. TROUBLESHOT TO BROKEN TOOTH ON STARTER ADAPTER SHAFT AND FAILED BEARING I	N CRANKCASE. BEARING SUPPORT WAS OVERSIZED, FILLING ENGINE OIL SYSTEM WITH METAL. NO PREVIOUS INDICATION OF C/W TCM CS	B NR 94-4 COULD BE FOUND.				1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1996011200250	19960112	00250	SO 	1996	1	12	96ZZZX179 	2	19951130	G	8540	537721	BEARING 		635050 	CESSNA	421 	421A 	2076012	CE 	CONT 	O520 	GTSIO520D 	17032	SO 					STARTER ADAPTER	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	2219Q	3658 	932 			421A0019	1884908D			PILOT REPORTED LOWER OIL PRESSURE, RT ENGINE. TROUBLESHOT TO BROKEN TOOTH ON STARTER ADAPTER SHAFT AND FAILED BEARING I	N CRANKCASE. BEARING SUPPORT WAS OVERSIZED, FILLING ENGINE OIL SYSTEM WITH METAL. NO PREVIOUS INDICATION OF C/W TCM CS	B NR 94-4 COULD BE FOUND.				1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1996010500267	19960105	00267	NE 	1996	1	5	96ZZZX18 	3	19951214	G	6114	SS210	SPIDER 													HAMSTD	2B	2B20 	NE 	HUB ARM	CRACKED 	B			LU4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17					A14454			A14454		PROPELLER SPIDER SUPPLIED WITH ASSEMBLY FOR OVERHAUL. FOUND SPIDER CRACKED.																5	C	P255	 
1996011200251	19960112	00251	SO 	1996	1	12	96ZZZX180 	2	19951208	G	8530	649177	VALVE GUIDE 			CESSNA	182 	182A 	2072704	CE 	CONT 	O470 	O470R 	17026	SO 					EXHAUST VALVE	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	3774D	766 				34474	321243R			FOUND CYLINDER COMPRESSION AT 40/80. REMOVED CYLINDER AND FOUND EXHAUST VALVE GUIDE WORN OVER LIMITS. EXHAUST VALVE IN	 GUIDE CLEARANCE AS MEASURED IS 0.016 INCH. SERVICEABLE LIMITS ARE 0.006 INCH.					1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1996011200252	19960112	00252	CE 	1996	1	12	96ZZZX181 	1	19951204	G	3310	S20917	POST LIGHT 			CESSNA	206 	TU206G 	2073357	CE 										COCKPIT	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	4759U	7000 				U20605086				INSTRUMENT POST LIGHT TRANSISTOR AND RHEOSTAT FAILED BY BURNING UP. SUBMITTER FOUND IF A CAPACITOR/RESISTOR IS INSTALLE	D IN LINE TO SUPPRESS INITIAL POWER SPIKE, LIFE OF TRANSISTOR AND RHEOSTAT IS LENGTHENED AND CONTROL IS BETTER. FIELD A	PPROVAL IS PENDING.				1	H	7	1 	3O				A4CE 					 
1996011200253	19960112	00253	GL 	1996	1	12	96ZZZX182 	3	19951213	G	6111	S90AT8	BLADE 			CESSNA	182 	182 	2072702	CE 						MCAULY	2A34C	2A34C66 	GL 	PROPELLER	CORRODED 	B			FG6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11					K109601YS			795412		FIRST OVERHAUL, ROUTINE, FOUND HUB AND 1 BLADE REJECTED DUE TO CORROSION. PROPELLER WAS 16 YEARS OLD AND NEVER BEEN APA	RT. SUBMITTER RECOMMENDS PROPELLER INSPECTION IAW MCAULEY TBO SPECS.					1	H	7	1 	3O			NT	3A13 		5	C	P3EA	 
1996011200254	19960112	00254	GL 	1996	1	12	96ZZZX183 	3	19951213	G	6114		HUB 			CESSNA	182 	182 	2072702	CE 						MCAULY	2A34C	2A34C66 	GL 	PROPELLER	CORRODED 	B			FG6R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11								795412		FIRST OVERHAUL, ROUTINE, FOUND HUB AND 1 BLADE REJECTED DUE TO CORROSION. PROPELLER WAS 16 YEARS OLD AND NEVER BEEN APA	RT. SUBMITTER RECOMMENDS PROPELLER INSPECTION IAW MCAULEY TBO SPECS.					1	H	7	1 	3O			NT	3A13 		5	C	P3EA	 
1996011200255	19960112	00255	SO 	1996	1	12	96ZZZX184 	1	19951128	G	3243	06102100	HOUSING 			PIPER 	PA28 	PA28180 	7102808	SO 										LOCATOR PIN	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	15956	3894 				287305196				UPON FURTHER INSPECTION OF PISTON HOUSING AFTER BLEEDER SHEARED OFF, CORROSION AND CRACKS WERE FOUND AT LOCATOR PIN HOLE	S. SUBMITTER SUGGESTS CORROSION COULD BE STOPPED BY MORE FREQUENT CLEANING AND PAINTING. CRACKS MAY HAVE STARTED FROM 	OVERTORQUE OF NUTS ON PINS.				1	L	7	1 	3O				2A13 					 
1996011200257	19960112	00257	NM 	1996	1	12	96ZZZX186 	1	19951201	G	3020	6568858	DUCT ASSY 			BOEING	727 	727 	1384001	NM 										NR 1-3 ENG COWL	BROKEN 	B			EG4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	25										DURING OVERHAUL OF NR 1 AND NR 3 NOSE COWLS, THERMAL ANTI-ICING DUCT ASSEMBLIES, PN 65-68858-(ALL DASH NUMBERS) WERE FOU	ND BROKEN OR COMPLETELY WORN THROUGH BY THE ATTACHING CLAMPS IN THE 6 O'CLOCK AREA.					2	L	7	3 	4F				A3WE 					 
1996011200258	19960112	00258	NM 	1996	1	12	96ZZZX187 	1	19950822	G	5313	69144924	STRINGER 			BOEING	727 	72723 	1384004	NM 										BS 480 STR 28R	CORRODED 	B			LVTR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	1972	72212				18428				DURING AN INTERNAL VISUAL INSPECTION PER AD 90-26-09*, THE STRINGER SPLICE ON STR 28R AT BS 480 WAS FOUND SEVERELY CORRO	DED (EXFOLIATED). REMOVAL OF STRINGER SPLICE REVEALED CORROSION ON STRINGER END AFT OF SPLICE. AIRCRAFT HAS BEEN IN ST	ORAGE SINCE 9/92 IN NORTH CAROLINA. *CORROSION IS UNRELATED TO INSPECTION REQUIREMENTS OF AD 90-26-09.				2	L	7	3 	4F				A3WE 					 
1996011200259	19960112	00259	EA 	1996	1	12	96ZZZX188 	1	19951215	G	2730	C6CF14711	CONTROL ROD 			DHAV 	DHC6 	DHC6* 	2802606	EA 										ELEVATOR	CRACKED 	B		A	ROSR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	35062	720 				429				THIS AIRCRAFT WAS MODIFIED TO INCORPORATE THE LATEST TYPE OF FLIGHT CONTROL RODS (6061 MATERIAL) AND INCREASE THE INSPEC	TION INTERVALS FOR THE FLIGHT CONTROL RODS (SB 61502). UPON THE FIRST INSPECTION, THIS CONTROL ROD WAS FOUND CRACKED IN	 THE MAGNAFORMED SLEEVES, BOTH ENDS.				1	H	7	2 	3T				A9EA 					 
1996011200550	19960112	00550	SO 	1996	1	12	96ZZZX189 	1	19951120	G	5347	6255704	SEAT TRACK 			PIPER 	PA28 	PA28140 	7102802	SO 										PILOT OUTBOARD	CORRODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	3454K	2172 				2823562				DURING ANNUAL INSPECTION, FOUND PILOT'S OUTBOARD SEAT RAIL HAD SEVERE EXFOLIATION CORROSION SEVEN INCHES FORWARD OF SPAR	 CARRY-THROUGH STRUCTURE. UPON PROBING CORROSION WITH A PICK, THE RAIL DISINTEGRATED. SUBMITTER STATED THERE WAS EVIDE	NCE OF WATER PREVIOUSLY STANDING IN CABIN AREA.				1	L	7	1 	3O				2A13 					 
1996010500268	19960105	00268	EU 	1996	1	5	96ZZZX19 	1	19951213	G	3520	C3512000REVT	MASK 			BRAERO	1000 	BAE1251000 	1500287	EU 										CABIN	TORN 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	544QS	621 				259044				MASK RUBBER FACE CUP IS TORN. ON THIS ACFT, 6 MASKS WERE FOUND UNSERVICABLE. ALL MASKS HAD THE SAME DISCREPANCY. ONE 	NEW MASK WAS FOUND TORN PRIOR TO INSTALLATION, ITS MFG DATE WAS 6-95. P/N WAS SAME, BUT AT REV. U.					2	L	7	2 	4F			RT	A3EU 					 
1996011200551	19960112	00551	SO 	1996	1	12	96ZZZX190 	1	19951208	G	3250	400003	ROD ASSY 			PIPER 	PA44 	PA44180 	7104402	SO 										NLG STEERING	BOLT MISSING 	G	L	A		O				OTHER 				E			VIBRATION/BUFFET 			LD	LANDING 	1			WP	27	2185A					447995089				DURING A TOUCH AND GO LANDING ATTEMPT, WHEN THROTTLE ADVANCED, ACFT BEGAN TO VEER LEFT AND VIBRATE. TAKEOFF ABANDONED A	S ACFT DEPARTED RUNWAY WITH FULL RT RUDDER. INVESTIGATION REVEALED NLG DAMAGE, RT MLG DAMAGE ALONG WITH PROP, NOSE AND W	ING DAMAGE. FURTHER FINDING WAS THE STEERING ROD TO STEERING CAM BOLT AND NUT MISSING. SUBMITTER BELIEVES MISSING NUT 	AND BOLT CAUSED LOSS OF STEERING AND VIBRATION.			1	L	7	2 	3O				A19S0 					 
1996011200552	19960112	00552	SO 	1996	1	12	96ZZZX191 	1	19950214	G	2820		LINE 			PIPER 	PA28 	PA28150 	7102804	SO 										FUEL SYSTEM	BROKE 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	5071W		3627 			2880				DURING ANNUAL INSPECTION, FUEL LINES FROM TANK TO AIRFRAME WERE SHOWING AGE. WHILE PULLING TANKS, BOTH FUEL LINES SNAPP	ED. NO CORROSION WAS FOUND ON SPAR OR TANKS. SUBMITTER STATED THESE FUEL LINES HAVE TO BE CHECKED BY MIRROR.					1	L	7	1 	3O				2A13 					 
1996011200553	19960112	00553	SO 	1996	1	12	96ZZZX192 	1	19951006	G	5513	6358501	TRIM TAB 			PIPER 	PA28 	PA28R180 	7102809	SO 										STABILATOR RT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	999HS	4197 	4197 			28R30716				SKIN CORRODED AT NUTPLATE TO SKIN ATTACH POINTS. BOTH TABS BEYOND REPAIR. AIRCRAFT STRIPPED AND PAINTED 1 YEAR PRIOR. 	 DRY, TRAPPED STRIPPER FOUND AROUND NUTPLATES. THIS MAY HAVE CONTRIBUTED OR WAS RESPONSIBLE FOR CORROSION.					1	L	7	1 	3O				2A13 					 
1996011200554	19960112	00554	SO 	1996	1	12	96ZZZX193 	1	19951006	G	5513	6358500	TRIM TAB 			PIPER 	PA28 	PA28R180 	7102809	SO 										STABILATOR LT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	999HS	4197 	4197 			28R30716				SKIN CORRODED AT NUTPLATE TO SKIN ATTACH POINTS. BOTH TABS BEYOND REPAIR. AIRCRAFT STRIPPED AND PAINTED 1 YEAR PRIOR. 	 DRY, TRAPPED STRIPPER FOUND AROUND NUTPLATES. THIS MAY HAVE CONTRIBUTED OR WAS RESPONSIBLE FOR CORROSION.					1	L	7	1 	3O				2A13 					 
1996011200555	19960112	00555	CE 	1996	1	12	96ZZZX194 	1	19951201	G	5753	0523914	RIB 			CESSNA	207 	207A 	2073604	CE 										FLAP NUTPLATE	CRACKED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	9829M	6303 	6303 			20700741				FOUND FLAP RIB AND SKIN CRACKS AT THE FORWARD NUTPLATE FOR THE INBOARD FLAP CONTROL BRACKET, STA 63.81. SUBMITTER RECOM	MENDS CUTTING A 4.5 INCH DIAMETER ACCESS HOLE ON INBOARD SIDE OF RIB, REPAIRING RIB WITH A WELDED .032 INCH 4130 DOUBLER	. THIS IS A COMMON PROBLEM ON THE 207 WITH ACTT 6,000 TO 10,000 HOURS.				1	H	7	1 	3O				A16CE 					 
1996011200556	19960112	00556	EA 	1996	1	12	96ZZZX195 	2	19951221	G	7322	R5A5AD1	SERVO INJECTOR 			BBAVIA	8 	8KCAB 	2110612	CE 	LYC 	O320 	AEIO320E1B 	41508	EA 					DIAPHRAGM	SEAL FAILED 	G				A				UNSCHED LANDING 				E	R	Y	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	ENGINE STOPPAGE 	CR	CRUISE 	1			SO	11	53870	1600 			11665131	22576	L538355A			WHILE IN LEVEL FLIGHT AT AN ALTITUDE OF 4,500 FEET MSL, ENGINE DEVELOPED A ROUGH RUNNING CONDITION AND THEN QUIT. UPON 	INSPECTION OF SERVO INJECTOR, FOUND A SEAL IN THE DIAPHRAGM HOUSING HAD BECOME DEFECTIVE.					1	H	7	1 	3O	3	O		A21CE 	1E12				 
1996011200557	19960112	00557	SW 	1996	1	12	96ZZZX196 	1	19951212	G	7112	600282503	SUPPORT BRACKET 			MOONEY	M20 	M20R 	5870225	SW 										ENGINE BAFFLE	BROKEN 	B			DY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	13	6792G	160 				290012				DURING ANNUAL INSPECTION, NOTED THE BAFFLE SUPPORT BRACKET UNDER THE FRONT CENTER SECTION OF ENGINE WAS BROKEN. OBTAINE	D NEW BRACKET AND INSTALLED. SUBMITTER STATED FURTHER WORK ON THIS AND ANOTHER MOONEY M20R SHOW THIS BRACKET IS BREAKIN	G WITH REGULARITY, LASTING AROUND 50 HOURS. BRACKET NEEDS TO BE MADE OUT OF HEAVIER METAL OR REDESIGNED. FAILURE OF BR	ACKET CAUSES NO SERIOUS PROBLEMS.			1	L	7	1 	3O			RT	2A3 					 
1996011200558	19960112	00558	SO 	1996	1	12	96ZZZX197 	1	19951211	G	2730		TRIM PULLEY 			PIPER 	PA32 	PA32300 	7103212	SO 										TAIL CONE	SPLIT 	B			UFAR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	25	2835W	1800 				327940148				DURING 100-HOUR INSPECTION, FOUND TRIM CABLE TENSION AT ZERO. RECORDS REVEALED TRIM CABLES HAD BEEN ADJUSTED TO PROPER 	TENSION AT THE PREVIOUS 100-HOUR INSPECTION. FOUND THE 1.25 INCH DIAMETER PULLEY ON THE RIGHT SIDE IN THE TOP OF THE TA	IL CONE JUST BELOW THE DORSEL FIN, WAS SPLIT IN TWO. SUBMITTER SUGGESTS THERE APPEARS TO BE SIGNS OF DELAMINATIONS SOAK	ED WITH LUBRICANTS.			1	L	7	1 	3O				A3SO 					 
1996011200559	19960112	00559	SO 	1996	1	12	96ZZZX198 	2	19951122	G	7322	6397172	FUEL CONTROL 			CESSNA	185 	A185F 	2072821	CE 	CONT 	O520 	IO520D 	17032	SO 					THROTTLE ARM	BUSHING WORN 	B			CL4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	03	9987N	779 				18504379	175762R			STEEL BUSHING HAS WORN AWAY ABOUT 90 PERCENT OF THE THROTTLE ARM. THE BOLT WAS CORRECTLY INSTALLED AND PROPERLY TORQUED	. THIS AREA HAS BEEN SUBJECT TO CLOSE INSPECTION AT EACH 100-HOUR INSPECTION SINCE EARLIER REPORTS OF SIMILAR PROBLEMS 	(CESSNA SEB 95-15), A.C. 43-16. SUBMITTER SUGGESTS THIS DAMAGE APPARENTLY PROGRESSED RAPIDLY SINCE THE LAST 100-HOUR IN	SPECTION.			1	H	7	1 	3O	3	O		3A24 	E5CE				 
1996042500366	19960425	00366	SO 	1996	4	25	96ZZZX1987 	1	19950528	G	7430	103572101	SWITCH 			PIPER 	PA28 	PA28180 	7102808	SO 										IGNITION	FAILED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	55044					287305299				WHEN MASTER SWITCH WAS TURNED ON, PROPELLER BEGAN TO ROTATE. IGNITION SWITCH WAS OFF WITH NO KEY IN IT. INSTALLED NEW 	SWITCH, OPS CHECK OK.					1	L	7	1 	3O				2A13 					 
1996011200560	19960112	00560	EA 	1996	1	12	96ZZZX199 	2	19951215	G	7322	229587	TUBE 	FACET 	MA4SPA 	PIPER 	PA28 	PA28151 	7102805	SO 	LYC 	O320 	O320E3D 	41508	EA 					CARB IDLE ASSY	SEPARATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	1195X		1243 			287515324	L4600927A			ENGINE WAS ROUGH AT IDLE, AND WOULD SMOKE. IDLE ADJUSTMENT WOULD NOT HELP. CARBURETOR WAS DISASSEMBLED. THE IDLE TUBE	 WAS FOUND SEPARATED FROM THE THREADED PORTION.					1	L	7	1 	3O	3	O		2A13 	E274				 
1996010500269	19960105	00269	EA 	1996	1	5	96ZZZX2 	2	19950624	G	7230	311211702	BEARING 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					COMP NR 1	FRACTURED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	119YV	2527 			FC30316	UC119	32573			NEITHER THE COMPRESSOR OR THE CT DISK ROTATED FREELY AND HEAVY RUB WAS NOTED ON THE FIRST STAGE COMPRESSOR ROTOR. THE N	R 1 BEARING INNER BALL CAGE WAS FRACTURED AND THE BALLS SHOWED SIGNS OF SKIDDING.					2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1996011200561	19960112	00561	SO 	1996	1	12	96ZZZX200 	1	19951018	G	5741	62448XX	FITTING 			PIPER 	PA28 	PA28140 	7102802	SO 										WING ATTACH AFT	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	3454K	2172 				2823562				CORROSION FOUND ON BOTH WING REAR ATTACH FITTINGS. THIS PROBLEM IS ADDRESSED BY PIPER SB 977. IT APPEARS THERE IS SURF	ACE CORROSION ON THE STEEL FITTING AND DISSIMILAR METAL CORROSION ON THE SPAR CARRY-THROUGH STRUCTURE. SUBMITTER RECOMM	ENDED THIS SB BE MADE INTO AN AD TO ELIMINATE THIS UNSAFE CONDITION.				1	L	7	1 	3O				2A13 					 
1996042500395	19960425	00395	CE 	1996	4	25	96ZZZX2017 	1	19950824	G	3233	98820152	ACTUATOR 			CESSNA	172 	172RG 	2072438	CE 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	9639B	7476 				172RG0937				THE RADIUS OF THE ACTUATOR APPEARED TO BE CRACKED, THE PART WAS REMOVED AND DYE PENETRANT INSPECTION PERFORMED. FOUND N	UMEROUS CRACKS AROUND THE RADIUS WHERE THE MAIN GEAR ACTUATING GEAR IS BOLTED TO THE ACTUATOR. THE BOSS FOR THE SHAFT A	ND BEARING WHICH ALIGN THE JACK WAS CRACKED ALMOST ALL THE WAY AROUND. FURTHER INVESTIGATION SHOWED SIMILAR CRACKS ON T	HE OTHER MAIN GEAR ACTUATOR. SUBMITTER SUGGESTS THESE PARTS BE INSPECTED WITH DYE PENETRANT AT 5,000 HRS AND THEN EACH 	1,000 HRS THEREAFTER OR ANYTIME GEAR CONTACTS THE GROUND IN OTHER THAN FULLY EXTENDED OR FULLY RETRACTED POSITION.		1	H	7	1 	3O				3A17 					 
1996011200563	19960112	00563	CE 	1996	1	12	96ZZZX202 	1	19951129	G	3222	5542300491	FORK 			CESSNA	500 	550 	2076604	CE 										NLG	CRACKED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	228CC	5655 				5500133				PERFORMED UNSCHEDULED LIQUID DYE PENETRANT EXAMINATION IAW CESSNA NDT MANUAL, PART 7, CHAPTER 32-20-01, NOTED TWO CRACKS	 IN THE LT AND RT CORNER RADII OF THE NLG FORK. BOTH CRACKS EXCEED LIMITS IAW CESSNA CMM MANUAL, CHAPTER 32-20-00. INI	TIAL INSPECTION OF THIS COMPONENT IS REQUIRED AT 5,000 LANDINGS AND EVERY 1,000 LANDINGS THEREAFTER. TOTAL LANDINGS AT 	TIME OF FAILURE IS 5,434. PREVIOUS EXAM WAS C/W AT 4,776 LANDINGS WITH NO DEFECTS NOTED.			1	L	7	2 	4F				A22CE 					 
1996011200564	19960112	00564		1996	1	12	96ZZZX203 	4	19950823	G	2562	0025004	BATTERY 	ARTEX 	EB2BCD 	GULSTM	G1159 	G1159 	3953505	SO 										ELT	LEAK 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	2FOR				7326	216				AIRTEX BATTERY INSIDE ELT CASE FOUND LEAKING AND CORROSION FORMING. SUSPECT HIGH FUSELAGE TEMPERATURE AS THE CAUSE OF FA	ILURE. ASSEMBLY IS MOUNTED IN AFT EQUIPMENT BAY WITH VERY LITTLE AIR FLOW WHEN AIRCRAFT IS STATIC.					2	L	7	2 	4F			RT	A12EA 					 
1996011200565	19960112	00565	GL 	1996	1	12	96ZZZX204 	2	19951217	G	7323	252466714	GOVERNOR 			BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20B 	03013	GL 					TURBINE	DEFECTIVE 	D				K				NONE 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			SW	09	1082N		508 		25884	2945	CAE830561			GOVERNOR DROOPED TO 98 PERCENT N2 AND DID NOT RECOVER. N2 CONTINUED TO DROP WITHOUT RECOVERY. GOVERNOR ARM FELT STIFF.	 SENT IN FOR WARRANTY REPAIR. THE FOLLOWING ITEMS WERE REPLACED INSIDE GOVERNOR. PN 2520501, BEARING. PN 2523240, BE	ARING. PN 2525170, BUSHING. PN 2539034, WEIGHT. THIS GOVERNOR HAS A 2,000-HOUR OVERHAUL.				1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1996011200566	19960112	00566		1996	1	12	96ZZZX205 	4	19951211	G	3416	D120P2T	ENCODER 			AEROSP	SA365 	SA365N1 	8680668	EU 										COCKPIT	DEFECTIVE 	B			KY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	95MD	1500 			74097	6320				LOOSE ITEM WITHIN, ENCODING DIGITIZER.						1	G	7	2 	3U				H10EU 					 
1996011200567	19960112	00567	EU 	1996	1	12	96ZZZX206 	1	19951213	G	6310	365A32653000	COUPLING 			AEROSP	SA365 	SA365N1 	8680668	EU 										ENG/XMSN	CRACKED 	B			KY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	94MD				NC1159	6317				FLEX COUPLING HAS CRACKED LAYER.						1	G	7	2 	3U				H10EU 					 
1996011200568	19960112	00568	EU 	1996	1	12	96ZZZX207 	1	19951215	G	7931	53408	TRANSMITTER 			AEROSP	SA365 	SA365N1 	8680668	EU 										OIL PRESSURE	DEFECTIVE 	B			KY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	38MD				1091	6335				OIL PRESSURE TRANSMITTER FLUCTUATING AND PEGGING AT 5 BARS.						1	G	7	2 	3U				H10EU 					 
1996011200569	19960112	00569	EU 	1996	1	12	96ZZZX208 	1	19951215	G	7931	53408	TRANSMITTER 			AEROSP	SA365 	SA365N1 	8680668	EU 										OIL PRESSURE	FLUCTUATING 	B			KY1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	95MD	478 			1188	6320				TRANSMITTER HAS FLUCTUATING PRESSURE.						1	G	7	2 	3U				H10EU 					 
1996010500271	19960105	00271	NE 	1996	1	5	96ZZZX21 	2	19951114	G	7230	766933	CASE 			BOEING	727 	727172C 	1384058	NM 	PWA 	JT8 	JT8D7B 	52053	NE 					LP COMPRESSOR	FRACTURED 	B	L		RRXR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11	527PC	45420			UAL3388	19665				ON DISASSEMBLY OF ENGINE, FOUND THE LP COMPRESOR HAD SUFFERED A 360 DEGREE FRACTURE OF FORWARD FLANGE OF INTERMEDIATE CA	SE (WHERE IT IS BOLTED TO THE REAR OF THE 3-4 STATOR). ON EXAMINATION OF CASE. IT WAS EVIDENT IT HAD BEEN PARTIALLY CRA	CKED FOR SOME TIME BEFORE FINALLY FAILING AND FRACTURING COMPLETELY THROUGH 360 DEGREES. THIS TOTAL FAILURE OF THE FRON	T FLANGE CAUSED THE LP COMPRESSOR ASSY LOSS OF LOCATION, THE LP COMPRESSOR MOVING FORWARD CAUSNG HEAVY RUBS TO ALL STAGE	S OF LP COMPRESSOR BLADE TIPS, STAGE 3 THROUGH STAGE 6. CYCLES, 35,247.		2	L	7	3 	4F	4	F		A3WE 	E2EA				 
1996011900084	19960119	00084	NM 	1996	1	19	96ZZZX214 	1	19951005	G	5315	BAC1518399	FLOOR BEAM 			BOEING	737 	737247 	138448D	NM 										BS 947.5	CORRODED 	B			IX3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	303VA					20125				MAINTENANCE REPORT OF CORROSION AT FLOOR BEAM STA 947.5 LT UPPER T-CHORD. CORROSION RUNS APPROXIMATELY 23 INCHES INBOAR	D OF THE FRAME. CORROSION FOUND DURING INSPECTION OF AREA FOR 24-MONTH CPCP CARD C53-107-02 (BOEING). REPAIR OF AREA T	O BE ACCOMPLISHED IAW B737 SRM 53-10-09, AND E.O. 353E021, DATED 10-14-95. AIRCRAFT TOTAL TIME, 54,469.8 HOURS. AIRCRA	FT TOTAL CYCLES, 61,901.			2	L	7	2 	4F				A16WE 					 
1996050200269	19960502	00269	CE 	1996	5	2	96ZZZX2147 	1	19950502	G	7120	121343317	SUPPORT 			CESSNA	206 	P206B 	2073309	CE 										ENG RT MOUNT	RIVETS SHEARED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	4778F	3000 				P2060378				DURING ROUTINE PROPELLER REMOVAL FOR OVERHAUL, DETERMINED 6 AN470 4-4 RIVETS COMPLETELY SHEARED OFF AND MISSING FROM RIG	HT FRONT ENGINE SUPPORT AND CHANNEL ASSY, PN 1213433-14, AND SUPPORT, PN 1213433-17. FURTHER INSPECTION REVEALED NO OTH	ER DAMAGE OR SHEARED RIVETS IN ANY OTHER OF THE 3 REMAINING MOUNTS. THE ENGINE HAD BEEN OVERHAULED AT AN EARLIER DATE. 	 SUSPECT CAUSE: TORQUE MAXIMUM PERFORMANCE TAKEOFF AND PROP VIBRATION. SUBMITTER SUGGESTS CLOSER INSPECTION IN AREA.			1	H	7	1 	3O				A4CE 					 
1996050200270	19960502	00270	CE 	1996	5	2	96ZZZX2148 	1	19950502	G	7120	121343314	CHANNEL 			CESSNA	206 	P206B 	2073309	CE 										ENG RT MOUNT	RIVETS SHEARED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	4778F	3000 				P2060378				DURING ROUTINE PROPELLER REMOVAL FOR OVERHAUL, DETERMINED 6 AN470 4-4 RIVETS COMPLETELY SHEARED OFF AND MISSING FROM RIG	HT FRONT ENGINE SUPPORT AND CHANNEL ASSY, PN 1213433-14, AND SUPPORT, PN 1213433-17. FURTHER INSPECTION REVEALED NO OTH	ER DAMAGE OR SHEARED RIVETS IN ANY OTHER OF THE 3 REMAINING MOUNTS. THE ENGINE HAD BEEN OVERHAULED AT AN EARLIER DATE. 	 SUSPECT CAUSE: TORQUE MAXIMUM PERFORMANCE TAKEOFF AND PROP VIBRATION. SUBMITTER SUGGESTS CLOSER INSPECTION IN AREA.			1	H	7	1 	3O				A4CE 					 
1996050200282	19960502	00282	SO 	1996	5	2	96ZZZX2160 	2	19950819	G	8530		CYLINDER 			CESSNA	188 	A188B 	2073005	CE 	CONT 	O520 	IO520D 	17032	SO 					NR 1 CYLINDER	SEPARATED 	D				O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			EA	21	731VX	2916 				18803200T	175074R			CYLINDER HEAD SEPARATED FROM BARREL ON TAKEOFF CAUSING CONSIDERABLE DAMAGE TO AIRCRAFT, NO INJURIES. DURING REPAIR OF A	CFT AND ANNUAL INSP, FOUND ENGINE BAFFLE SEAL MATERIAL EXTREMELY DETERIORATED AND IN A DEFECTIVE CONDITION AND CHT PROBE	 IN WRONG CYLINDER POSITION PER TCDS. INSTALLED PROBE IN CORRECT POSITION. REPLACED BAFFLE SEALS. PAST REPLACEMENT OF	 BAFFLE SEAL MATERIAL ON SAME MODEL ACFT GAVE A 100 DEGREE FAHRENHEIT LOWER CHT. HIGH CHT MAY HAVE CAUSED HEAD SEPARATI	ON.		1	L	7	1 	3O	3	O		A9CE 	E5CE				 
1996050200299	19960502	00299	NM 	1996	5	2	96ZZZX2177 	1	19951221	G	2782	5007404	PLANETARY GEAR 	SUNDSTRANDEM	755299B 	BOEING	757 	757* 		NM 										LE FLAP ACTUATOR	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11					A4559					ACTUATOR TORN DOWN, FOUND NEEDLE BEARING AND PLANET GEAR ASSEMBLIES CORRODED. ONE GEAR CAUSING LOCKOUT AT PRE-TEST. WA	TER INJESTED CAUSING NEEDLES TO FREEZE TO ONE EACH PLANET GEAR. THIS GEAR ASSY COMES IN A SET CAUSING REPLACEMENT OF CO	MPLETE ASSY. CARRIER THAT CONTAINS GEAR SET WORN DUE TO HIGH TORQUE REQUIRED TO ROTATE ACTUATOR.				2	L	7	2 	4F			RT	A2NM 					 
1996010500272	19960105	00272	NM 	1996	1	5	96ZZZX22 	1	19951127	G	2750	65B15637	CRANK ASSY 			BOEING	747 	747132 	1384882	NM 										RT T/E FLAP	DAMAGED 	B			QLMY	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	481EV					19886				RIGHT T/E FLAP AFT SEGMENT BENT DOWN 6 FEET FROM OUTBOARD END. NR 6 GENEVA CRANK FOUND UNLACTHED WITH ASSOCIATED MECHAN	ISM DAMAGED. FOUND BOTH FIXED T/E PANELS ABOVE INBOARD FLAPS CRACKED/DELAMINATED.					2	L	7	4 	4F				A20WE 					 
1996010500273	19960105	00273	NM 	1996	1	5	96ZZZX23 	1	19951127	G	5753	65B15648	SUPPORT 			BOEING	747 	747132 	1384882	NM 										RT T/E FLAP	BENT 	B			QLMY	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	481EV					19886				RIGHT T/E FLAP AFT SEGMENT BENT DOWN 6 FEET FROM OUTBOARD END. NR 6 GENEVA CRANK FOUND UNLATCHED WITH ASSOCIATED MECHAN	ISM DAMAGED. FOUND BOTH FIXED T/E PANELS ABOVE INBOARD FLAPS CRACKED/DELAMINATED.					2	L	7	4 	4F				A20WE 					 
1996010500274	19960105	00274	CE 	1996	1	5	96ZZZX24 	1	19951206	G	7830	225012509	THRUST REVERSER 			BEECH 	MU300 	400BEECH 		CE 										LT T/R	DEPLOYED 	B		A	MGOR	O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			CE	09	8053V	426 				RK47				LEFT THRUST REVERSER DEPLOYED ON TAKEOFF. DEACTIVATED BOTH T/R SYSTEMS AND FERRIED TO OMA. COMPLETED COMPLETE RIGGING 	AND OPERATIONAL TEST OF T/R SYSTEM. NO SYSTEM MALFUNCTIONS WERE NOTED. REPLACED BOTH T/R STOW SWITCHES AT THE RECOMMEN	DATION OF RAYTHEON AIRCRAFT. STOW SWITCH, P/N 21681.				2	H	7	2 	4F			RT	A16SW 					 
1996051600270	19960516	00270	CE 	1996	5	16	96ZZZX2402 	1	19951113	G	3230	504501019	TORUE TUBE 			CESSNA	402 	402B 	207590P	CE 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	75GB	4715 				402B0912				INSPECTION FOUND MLG TORQUE TUBE CRACKED AT BOLT HOLE DOUBLER.						1	L	7	2 	3O				A7CE 					 
1996051600272	19960516	00272	SO 	1996	5	16	96ZZZX2404 	2	19950707	G	7414		IMPULSE COUPLING	SLICK 	6310 	CESSNA	207 	207A 	2073604	CE 	CONT 	O520 	IO520F 	17032	SO 					ENG MAG	BROKEN 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	99	7320U	920 				20700397				IMPULSE COUPLING BROKE ALLOWING A PART TO RUB THE INSIDE OF THE MOUNTING FLANGE. THE MOUNTING FLANGE BROKE OFF ALLOWING	 THE MAG TO FALL OFF. THE MAG WAS LAYING ON TOP OF THE CASE WHEN THE AIRCRAFT WAS RETURNED TO BASE.					1	H	7	1 	3O	3	O		A16CE 	E5CE				 
1996011900144	19960119	00144	SO 	1996	1	19	96ZZZX245 	1	19951127	G	5751	902010501	BRACKET 			GULSTM	AA5 	AA5 	0631410	SO 										RT AIL BEARING	BROKEN 	H	S	A		O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			NE	05	5402L	3163 				AA50302				REPORTED ON FINAL APPROACH FOR LANDING, RT AILERON WAS IN 'UP' POSITION & AILERON CONTROL WAS JAMMED. LANDING WAS PERFO	RMED WITHOUT INCIDENT. INSP SHOWED RT OUTER AILERON SUPPORT HAD SEPARATED & WING TIP KEPT THE AILERON FROM COMING OFF T	HE ACFT. AFTER RT WING TIP WAS REMOVED, FND OUTER AILERON SUPPORT HAD BROKEN OFF AT THE 90 DEGREE RADIUS AT ATTACH POIN	T AND STOP PLATE, PN 5603074-1, WAS BENT. NO OTHER DAMAGE FND. UPON REMOVING LT WING TIP, FND AILERON STOP PLATE, PN 5	603074-1, BENT AT AN ANGLE SO AS THE STOP PIN WAS INEFFECTIVE. LT OUTER AILERON SUPPORT, PN 902010-501, HAD CRACKS AT T	HE 90 DEGREE RADIUS. NO OTHER DAMAGE FND. BOTH OUTER AILERON SUPPORTS WERE REPLACED & ACFT RETURNED TO SERVICE.	1	L	7	1 	3O				A16EA 					 
1996011900145	19960119	00145	CE 	1996	1	19	96ZZZX246 	1	19951220	G	7120	454103858	SUPPORT 			BEECH 	35 	C35BEECH 	1151508	CE 										ENG MOUNT LT	SEVERED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	7MK	8515 				D3033				SUPPORT REMOVED FOR SMALL CRACK IN UPPER FLANGE. UPON REMOVAL OF CABIN AIR INLET DUCT FROM FORWARD BULKHEAD, FOUND SUPP	ORT COMPLETELY SEVERED AT POINT SUPPORT PASSES THROUGH TUNNEL ASSY AND ATTACHES TO KEEL. SAME CONDITIONS FOUND ON RT SI	DE ALTHOUGH NOT AS OBVIOUS. ENGINE MOVEMENT CAUSED NUMEROUS CRACKS IN FORWARD BULKHEAD, AND CHAFING OF ROCKER COVERS TO	 LT SIDE COWL. NO EVIDENCE OF CONTRIBUTING FACTORS FOUND IN LOGS. DESIGN OF LATER MODEL SUPPORT ASSYS INCREASED THE WE	B AREA ATTACHING TO THE KEEL.		1	L	7	1 	3O				A777 					 
1996011900146	19960119	00146	CE 	1996	1	19	96ZZZX247 	1	19951220	G	7120	454103859	SUPPORT 			BEECH 	35 	C35BEECH 	1151508	CE 										ENG MOUNT RT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	7MK	8515 				D3033				SUPPORT REMOVED FOR SMALL CRACK IN UPPER FLANGE. UPON REMOVAL OF CABIN AIR INLET DUCT FROM FORWARD BULKHEAD, FOUND SUPP	ORT COMPLETELY SEVERED AT POINT SUPPORT PASSES THROUGH TUNNEL ASSY AND ATTACHES TO KEEL. SAME CONDITIONS FOUND ON RT SI	DE ALTHOUGH NOT AS OBVIOUS. ENGINE MOVEMENT CAUSED NUMEROUS CRACKS IN FORWARD BULKHEAD, AND CHAFING OF ROCKER COVERS TO	 LT SIDE COWL. NO EVIDENCE OF CONTRIBUTING FACTORS FOUND IN LOGS. DESIGN OF LATER MODEL SUPPORT ASSYS INCREASED THE WE	B AREA ATTACHING TO THE KEEL.		1	L	7	1 	3O				A777 					 
1996011900147	19960119	00147	SO 	1996	1	19	96ZZZX248 	1	19951215	G	5530	A5250	DORSAL FIN 			GULSTM	AA5 	AA5 	0631410	SO 										EMPENNAGE LT	DAMAGED 	D	S	A		O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			SO	25	7186L	2493 				AA50486				PILOT NOTICED TAIL FLUTTER, DIFFICULT TO CONTROL IN CROSSWIND. PILOT LANDED WITHOUT INCIDENT. UPON EXITING AIRPLANE, P	ILOT NOTICED HOLE IN DORSAL FIN. ABUSIVE HANDLING AND LOW TEMPERATURE SUSPECTED CAUSE OF PART MALFUNCTION.					1	L	7	1 	3O				A16EA 					 
1996011900148	19960119	00148	SO 	1996	1	19	96ZZZX249 	1	19951115	G	2710	8652608	BELLCRANK 			PIPER 	PA44 	PA44180 	7104402	SO 										AILERON	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	2148F	698 				447995157				AILERON HAD EXCESSIVE PLAY. WHEN CLEVIS ROD END WAS REMOVED, BEARING FELL OUT OF BELLCRANK. BEARING WAS ALSO VERY WORN	 INSIDE RACE WITH BOTH AXIAL AND RADIAL PLAY. BELLCRANK WAS REPLACED 4-6-94 DUE TO SAME PROBLEM. INSTALLED NEW BEARING	, PN 452603, INTO BELLCRANK. NEW BEARING CAME WITH PLAY BETWEEN BOLT AND BEARING. SUSPECT INSIDE DIAMETER OF HOLE TOO 	LARGE. CLEVIS ROD END, PN 554687, HAS BUSHING, PN 63900-119, IN IT. THIS BUSHING INSIDE DIAMETER IS TOO SMALL FOR BOLT	 AND OUTSIDE DIAMETER TOO SMALL FOR HOLE IN CLEVIS WHICH RESULTS IN ONE-HALF THE ALLOWABLE PLAY WITH ALL NEW PARTS.		1	L	7	2 	3O				A19S0 					 
1996010500275	19960105	00275	SW 	1996	1	5	96ZZZX25 	1	19951214	G	3610	38E852B	REGULATOR 	BENDIX 		GULSTM	690TP 	695A 	7630519	SW 										BLEED AIR	DIAPHRAGM BLOWN 	B		A	FB2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	325MM					96015				DURING THE COURSE OF A 100-HOUR INSPECTION, FOUND THE BLEED AIR REGULATOR TO HAVE A BLOWN DIAPHRAGM. THIS IS THE REGULA	TOR LOCATED IN AFT BAGGAGE AREA THAT REDUCES THE BLEED AIR FROM THE ENGINE DOWN TO 18 PSI TO INFLATE THE DOOR SEAL AND D	EICE BOOTS. HAVE FOUND MANY REGULATORS IN THIS CONDITION. INSTALLED AND OPS CHECKED AND OVERHAULED REGULATOR. SUBMITT	ER SUGGESTS THE MFG PROVIDE AN IMPROVED DIAPHRAGM TO BETTER HANDLE THE HEAT, AS THIS MAY BE THE CAUSE OF THE NUMEROUS FA	ILURES.		1	H	7	2 	4T				2A4 					 
1996011900149	19960119	00149	SO 	1996	1	19	96ZZZX250 	1	19951115	G	2710	452603	BEARING 			PIPER 	PA44 	PA44180 	7104402	SO 										AIL BELLCRANK	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	2148F	698 				447995157				AILERON HAD EXCESSIVE PLAY. WHEN CLEVIS ROD END WAS REMOVED, BEARING FELL OUT OF BELLCRANK. BEARING WAS ALSO VERY WORN	 INSIDE RACE WITH BOTH AXIAL AND RADIAL PLAY. BELLCRANK WAS REPLACED 4-6-94 DUE TO SAME PROBLEM. INSTALLED NEW BEARING	, PN 452603, INTO BELLCRANK. NEW BEARING CAME WITH PLAY BETWEEN BOLT AND BEARING. SUSPECT INSIDE DIAMETER OF HOLE TOO 	LARGE. CLEVIS ROD END, PN 554687, HAS BUSHING, PN 63900-119, IN IT. THIS BUSHING INSIDE DIAMETER IS TOO SMALL FOR BOLT	 AND OUTSIDE DIAMETER TOO SMALL FOR HOLE IN CLEVIS WHICH RESULTS IN ONE-HALF THE ALLOWABLE PLAY WITH ALL NEW PARTS.		1	L	7	2 	3O				A19S0 					 
1996011900150	19960119	00150	CE 	1996	1	19	96ZZZX251 	1	19951221	G	3230		BRACKET 			BEECH 	33 	F33A 	1151425	CE 										LT MLG UPLOCK	ELONGATED HOLE 	H	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	03	33BV					CE840				WHEN THE GEAR WAS SWUNG ON JACKS DURING ANNUAL INSPECTION, THE LT MAIN WOULD NOT EXTEND. WHEN THE GEAR WOULD NOT EXTEND	, THE LT LANDING GEAR ACTUATING ROD BUCKLED IN COMPRESSION IN THE TUBULAR SECTION, BENDING AT 2 PLACES ABOUT EQUIDISTANT	 FROM THE CENTER. THE RT MAIN AND NOSE GEAR EXTENDED NORMALLY. THE PROBLEM WAS THE LT UPLOCK BRACKET TIP HAD JAMMED IN	TO THE KNEE JOINT, PREVENTING GEAR FROM COMING DOWN. ON REMOVAL, UPLOCK BRACKET OBSERVED TO HAVE AN ELONGATED HINGE BOL	T HOLE WHICH HAD ALLOWED TIP TO MOVE FORWARD (TOWARD THE FRONT OF AIRPLANE) INTO THE KNEE JOINT INSTEAD OF LINING UP WIT	H ITS ROLLER. TT, 3,500 HOURS.	1	L	7	1 	3O				3A15 					 
1996011900151	19960119	00151	SO 	1996	1	19	96ZZZX252 	1	19951101	G	5711		SPAR 			PIPER 	PA28 	PA28180 	7102808	SO 										FUSELAGE ATTACH	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	7091W					28878				A STUDENT PILOT WAS CONDUCTING ROUTINE PRE-FLIGHT INSP & WITH FLAPS DOWN, HE NOTICED 2 RIVETS MISSING HEADS ON RT WING R	EAR SPAR NEXT TO FUSELAGE. BROUGHT PLANE INTO SHOP & INVESTIGATED. STABILIZED ACFT ON JACKS UNDER WING & FUSELAGE & DR	ILLED PLATE OFF THE SPAR. BEHIND PLATE, ALUM SPAR WAS ENTIRELY EATEN AWAY BY INTERGRANULAR CORROSION. STEEL PLATE ON O	PPOSITE WING DRILLED OFF & FND ALMOST AS BAD. COMPLETING REPLACEMENT OF BOTH SPARS. IMPORTANT FACT HERE IS THIS CONDIT	ION EXTREMELY DIFFICULT TO SPOT. VISUAL ACCESS TO BACK OF THE REAR SPAR AT REAR LOWER INBD PANEL IS ESSENTIAL. PIPER S	B 789A PROVIDES FOR INSP PANEL IN THIS AREA & WOULD ALLOW INSP TO PROBE BACK OF SPAR. KIT REFERERENCE IS PN 765-106V.	1	L	7	1 	3O				2A13 					 
1996011900152	19960119	00152	GL 	1996	1	19	96ZZZX253 	1	19951101	G	7921	8406R	COOLER 	STWARNER 		AMTR 	T18 	THORPT18 		GL 										INBD BOSS	SPLIT 	H	L			A				UNSCHED LANDING 				B	K	J	SMOKE/FUMES/ODORS/SPARKS 	FLUID LOSS 	WARNING INDICATION 	NR	NOT REPORTED 	1			WP	05	992PE	112 			6186	1992				OIL COOLER WELD BROKE WHERE THE BOSS IS WELDED ONTO THE COOLER ON INBOARD SIDE. OIL WAS QUICKLY PUMPED OUT OF THE ENGIN	E SPRAYING OVER THE ENGINE CREATING MUCH SMOKE IN THE COCKPIT AND ZERO READING ON THE OIL PRESSURE GAUGE. FORTUNATELY, 	ACFT WAS OVER AN AIRPORT AND MADE A SAFE LANDING. THE INSTALLATION OF THE COOLER IS STANDARD ON T18.				1	L	7	1 	3O				EXPA1L71					 
1996052300221	19960523	00221	SO 	1996	5	23	96ZZZX2554 	1	19950801	G	7110	6979100	BRACKET 		62798803 	PIPER 	PA28 	PA28180 	7102808	SO 										LOWER ENG COWL	MISSING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	5154S	6341 				287105008				DURING REMOVAL OF UPPER ENGINE COWLING, FOUND SMALL PORTION OF LT BRACKET MISSING. SUBSEQUENT INSPECTION OF RT BRACKET 	REVEALED SEVERE EXFOLIATION ALONG UPPER PORTION OF BRACKET. SUSPECT CAUSE AS DISSIMILAR METAL AND GALVANIC CORROSION IN	 LATENT STAGES.				1	L	7	1 	3O				2A13 					 
1996011900155	19960119	00155	CE 	1996	1	19	96ZZZX256 	1	19951207	G	3242	3052N	DISC 	PARKERHANFIN		CESSNA	185 	A185F 	2072821	CE 										RT BRAKE	BROKEN 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			GL	13	83SS	262 				18502166				RIGHT BRAKE DISC SEPARATED FROM WHEEL AFTER LANDING, AND SUBSEQUENT BRAKE APPLICATION. SUBMITTER STATED IT APPEARS AS I	F THE BRAKE DISC MATERIAL FAILED AND PULLED AWAY FROM WHEEL BOLTS. THICKER MATERIAL WOULD HELP SOLVE PROBLEM. ADDING A	NOTHER BOLT TO THE WHEEL/DISC WOULD HELP ALSO.				1	H	7	1 	3O				3A24 					 
1996052300227	19960523	00227	EA 	1996	5	23	96ZZZX2560 	2	19951022	G	8520	SL18840	CAMSHAFT 			PIPER 	PA28 	PA28140 	7102802	SO 	LYC 	O320 	O320D2A 	41508	EA 					NR 2 EXH LOBE	SEVERELY GALLED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	95154	128 			362179	2825825	L2544727A			WHILE CONDUCTING ANNUAL INSPECTION, MANY SMALL STEEL FRAGEMENTS FOUND IN OIL SUCTION SCREEN AND IN FULL FLOW OIL FILTER.	 REMOVED CYLINDERS NR 3, 4, AND 1. FOUND NR 2 EXHAUST LOBE AND NR 2 LIFTER BODY BADLY DAMAGED. REMAINDER OF CAM LOBES	 AND LIFTER BODIES LOOKED GOOD. THIS ENGINE HAD 127.6 HRS SMOH WITH NEW SUPERIOR AIR PARTS CAMSHAFT AND LIFTER BODIES. 	 CHANGED OIL AND FILTER AT 15 HRS AND NO METAL FRAGMENTS WERE NOTICED. OWNER CHANGED OIL AND FILTER UNTIL IT WAS BROUGH	T IN FOR ANNUAL AT WHICH TIME FOUND THE METAL.		1	L	7	1 	3O	3	O		2A13 	E274				 
1996011900156	19960119	00156	CE 	1996	1	19	96ZZZX257 	1	19951222	G	5711	052302011	ANGLE 			CESSNA	172 	172P 	2072436	CE 										SPAR CAP	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	51208	6526 				17274280				INSPECTION FOUND INTERGRANULAR CORROSION IN SPAR CAP ANGLE. CORROSION MIGRATED TO DOUBLER PLATE, PN 0523315-11.						1	H	7	1 	3O			NT	3A12 					 
1996052300328	19960523	00328	EA 	1996	5	23	96ZZZX2574 	2	19951030	G	7322	95473	VENT LINE FTNG 			GRUMAN	TS2 	TS2ACALFORST	3951102	WP 	WRIGHT	R1820 	R182080 	67020	EA 					NAC CARB VENT	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	448DF	7768 				144723				DURING ANNUAL INSPECTION, FUEL STAINS WERE NOTED ON NACELLE BULKHEAD. LEAK WAS FOUND BY PRESSURIZING THE FUEL SYSTEM. C	RACK BELIEVED TO HAVE BEEN CAUSED BY OVERTORQUING THE PIPE TYPE FITTING DURING OVERHAUL OR ASSEMBLY. LEFT AND RIGHT WER	E CRACKED. SUBMITTER STATED THIS IS THE THIRD OCCURRENCE NOTED.				2	H	7	2 	4R	4	R		A25WE 	E259				 
1996011900157	19960119	00157	CE 	1996	1	19	96ZZZX258 	1	19951116	G	2841	C6695250101	GAUGES 	STWARNER 		CESSNA	210 	T210M 	2073451	CE 										FUEL INDICATION	ERRORS 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	6508B	2638 				21062777				FUEL GAUGES HAVE INACCURATE READINGS CAUSING MISFUELING OF AIRCRAFT AND FUEL STARVATION. SUBMITTER RECOMMENDS GAUGES BE	 CHECKED FOR ACCURACY AT INSPECTIONS. IF INACCURATE GAUGES ARE PRESENT, REPLACE THEM WITH REBUILT UNITS OR THE NEW KIT 	OFFERED BY CESSNA.				1	H	7	1 	3O				3A21 					 
1996011900158	19960119	00158	SO 	1996	1	19	96ZZZX259 	1	19951215	G	3230	25720003	GEARBOX 			PIPER 	PA30 	PA30 	7103002	SO 										MLG	FAILED 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	5WK	4950 				301853				REFERENCE, AIRCRAFT MAIN LANDING GEAR SYSTEM. DURING EMERGENCY LANDING, GEAR WOULD NOT EXTEND. GEAR COLLAPSED UPON LAN	DING. SUBMITTER RECOMMENDS THE GEAR BE OVERHAULED EVERY 5 YEARS, OR BE PULLED AND INSPECTED EVERY 2 YEARS.					1	L	7	2 	3O				A1EA 					 
1996010500276	19960105	00276	NE 	1996	1	5	96ZZZX26 	2	19951201	G	7250	825601	DISC 			BOEING	747 	747* 		NM 	PWA 	JT9 	JT9D7 	52054	NE 					HPT STAGE 1	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99		34540					662325			HPT INSPECTION FOUND ON THE FORWARD OUTSIDE DIAMETER OF THE DISC IN THE RADIUSED PORTION, OVER AN 0.5 INCH WIDE BAND FOR	 360 DEGREES, MULTIPLE CIRCUMFERENTIAL CRACKING CAUSED BY COALESCED CORROSION PITS APPROXIMATELY 0.007 INCH DEEP. CYCLE	S, 10,324.				2	L	7	4 	4F	4	F	RT	A20WE 	E20EA				 
1996011900159	19960119	00159	GL 	1996	1	19	96ZZZX260 	3	19951222	G	6114	D4344	HUB 													MCAULY	3AF32C	3AF32C93 	GL 	NR 1 BLD SOCKET	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15		4918 	907 					782026		WHILE COMPLYING WITH AD 95-24-05, PERFORMING EDDY CURRENT INSPECTION IAW MCAULEY SL 1993-11A AND SB 205B, DISCOVERED CRA	CK IN THREAD NR 1 BLADE RETAINING SLOT OF HUB.															5	C	P22EA	 
1996052300737	19960523	00737	SW 	1996	5	23	96ZZZX2609 	1	19950909	G	6410	222016001111	BLADE 		222012701119	BELL 	230 	230 	1182149	SW 										T/R	DOUBLER FAILED 	B		A	BAQR	A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			EA	03	232UM	1153 			501	23013				AFTER 1 MINUTE INTO A FLIGHT, A LOUD BANG WAS HEARD FROM THE REAR OF THE AIRCRAFT WITH A RIGHT YAW AND NOSE DOWN PITCH. 	 PILOT HAD NO PEDAL CONTROL. THE PILOT PERFORMED A RUN-ON LANDING WITH NO DAMAGE TO AIRCRAFT. THE TAIL ROTOR GEARBOX D	EPARTED THE AIRCRAFT. NO CAUSE HAS BEEN DETERMINED. THE FAA, NTSB, AND BELL HELICOPTER ARE INVESTIGATING. A DAILY INS	PECTION OF THE T/R DRIVE SYSTEM HAS BEEN IMPLEMENTED UNTIL FURTHER NOTICE.			1	G	7	2 	3U			NC	H9SW 					 
1996011900160	19960119	00160		1996	1	19	96ZZZX261 	4	19951215	G	3416	3431	CASTING 	UNITEDINST 	5934PD1 	PIPER 	PA32 	PA32R301 	7103218	SO 										ALTIMETER	CREEP 	B			EI4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	886JH				3A975	32R8213006				WHEN THIS INSTRUMENT WAS BENCH CHECKED, IT HAD STICK AND JUMP FRICTION OF 100 FEET TO 200 FEET. THE BACK OF THE DISC PO	INTER HAD A CIRCULAR SCRATCH ON THE BACK SIDE WHERE SCREWS HAD BEEN HITTING IT. ADDITIONALLY, ONE OF THE END-SHAKES ON 	ONE OF THE CRITICAL MECHANISM SHAFTS MEASURED .0005 INCH. THE SPECS IN THE OVERHAUL MANUAL CALLS OUT .002 INCH MINIMUM.	 THE MFG OF UNITED INST ALTIMETERS HAD INDICATED THAT AN END-SHAKE OF .0004 INCH OR LESS WILL CAUSE ALTIMETER TO HANG U	P IN A NORMAL COLD TEST. NOTE: THIS WAS A FACTORY SEALED ALTIMETER.		1	L	7	1 	3O				A3SO 					 
1996052300738	19960523	00738	SW 	1996	5	23	96ZZZX2610 	1	19950909	G	6410	222016001111	BLADE 		222012701119	BELL 	230 	230 	1182149	SW 										T/R	FAILED 	B			BAQR	A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			EA	03	232UM	1153 			508	23013				AFTER 1 MINUTE INTO A FLIGHT, A LOUD BANG WAS HEARD FROM THE REAR OF THE AIRCRAFT WITH A RIGHT YAW AND NOSE DOWN PITCH. 	 PILOT HAD NO PEDAL CONTROL. THE PILOT PERFORMED A RUN-ON LANDING WITH NO DAMAGE TO AIRCRAFT. THE TAIL ROTOR GEARBOX D	EPARTED THE AIRCRAFT. NO CAUSE HAS BEEN DETERMINED. THE FAA, NTSB, AND BELL HELICOPTER ARE INVESTIGATING. A DAILY INS	PECTION OF THE T/R DRIVE SYSTEM HAS BEEN IMPLEMENTED UNTIL FURTHER NOTICE.			1	G	7	2 	3U			NC	H9SW 					 
1996052300739	19960523	00739	SO 	1996	5	23	96ZZZX2611 	2	19951130	G	8520	530196A1	CRANKSHAFT 			COMWTH	185 	REWN185 	2370604	EA 	CONT 	C85 	C8512 	17008	SO 					NR 1 MAIN FWD	CRACKED 	D				A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			NM	11	92828	1529 	50 		19F94	1624	200685125			DURING FLIGHT, A SLIGHT VIBRATION WAS NOTICED. A PRECAUTIONARY LANDING WAS MADE WITHOUT FURTHER INCIDENT. DURING AN IN	SPECTION TO DETERMINE CAUSE, NOTED THE PROPELLER COULD BE ROCKED FROM SIDE TO SIDE. SUBSEQUENT ENGINE TEAR-DOWN REVEALE	D A HORIZONTAL CRACK EXTENDING AROUND THE ENTIRE DIAMETER OF THE CRANKSHAFT FORWARD OF THE NR 1 MAIN BEARING SURFACE. T	HE CRACK CAUSED THE PROPELLER HUB TO LOOSEN CAUSING EXTENSIVE DAMAGE TO THE TAPERED CRANKSHAFT.			1	H	7	1 	3O	3	O		A729 	E233				 
1996052300742	19960523	00742	CE 	1996	5	23	96ZZZX2614 	1	19950430	G	5210	MS203922C15	CLEVIS PIN 			BEECH 	B300 	B300 	1159232	CE 										DOOR LATCH	BROKEN 	D		A		A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			EA	21	1551A	483 				FL24				CREW NOTICED LOUD NOISE AND DOOR UNSAFE LIGHT ON AT 28,000 FEET. SAFE LANDING MADE. MAINTENANCE FOUND TOP FORWARD CABI	N DOOR LATCH HOOK UNATTACHED FOR DOOR. DISASSEMBLED DOOR AND FOUND CLEVIS PIN ON WHICH THE HOOK PIVOTS BROKEN IN HALF. 	 CAUSE OF FAILURE UNKNOWN. INSTALLED NEW PIN, DOOR OPERATED OK. SUBMITTER RECOMMENDS TIME CHANGE OF THIS ITEM. PART I	NACCESSIBLE FOR INSPECTION.			2	L	7	2 	4T			RT	A24CE 					 
1996011900161	19960119	00161	CE 	1996	1	19	96ZZZX262 	1	19951214	G	3297		WIRE 			BEECH 	58 	58 	1152740	CE 										LT WHEELWELL	BROKEN 	D				O				OTHER 				O			OTHER 			CL	CLIMB 	1			GL	07	696BD					TH352				FOLLOWING TAKEOFF, GEAR ONLY GOES UP HALF-WAY. INSPECTION FOUND BROKEN WIRE IN LEFT WHEELWELL. REPAIRED WIRE. OPS CHE	CKS GOOD.					1	L	7	2 	3O			 	3A16 					 
1996011900162	19960119	00162	GL 	1996	1	19	96ZZZX263 	1	19951128	G	3230		ROD END 			AMTR 	LANCAR	LANCAIR 	05616TS	GL 										MLG	FAILED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			WP	07	70337					637				ROD END FROM GEAR LEG TO OVERCENTER LINK FAILED. SUBMITTER STATED PART NEEDS TO BE REDESIGNED FROM TUBE TO SOLID BOLT.						1	L	7	1 	3O			RT	EXPA1L71					 
1996011900163	19960119	00163	EA 	1996	1	19	96ZZZX264 	2	19951214	G	8500		ENGINE 			PIPER 	PA60 	PA60600 	7106001	NM 	LYC 	O540 	IO540K1J5 	41532	EA 					INDUCTION	LOST POWER 	D				A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			GL	07	6896B					600919816126	L2124748A			DURING FLIGHT, RT ENGINE LOSING POWER, LANDED. ENGINE CHECKED, NO PROBLEMS NOTED. SUSPECT INDUCTION PARTIALLY PLUGGED 	WITH SNOW.					1	M	7	2 	3O	3	O	RT	A17WE 	1E4				 
1996053000010	19960530	00010	EU 	1996	5	30	96ZZZX2647 	2	19950929	G	7414		POINTS 			AMTR 	KITFOX	KITFOX 	05613LZ	GL 	ROTAX 	912 	ROTAX912 	55555	EU 					ENGINE IGNITION	FAILED 	G				O				OTHER 				Y			ENGINE STOPPAGE 			TO	TAKEOFF 	1			WP	25	42AR	60 				036	4005261			ENGINE FAILED ON TAKEOFF. FOUND METAL FILINGS AROUND TRIGGER POINTS WHICH GROUNDED OUT IGNITION SYSTEM. UNABLE TO FIND	 WHERE FILINGS CAME FROM.					1	H	7	1 	3I	3	I	NC	EXPA1H71	EXPE3I				 
1996011900164	19960119	00164	SW 	1996	1	19	96ZZZX265 	1	19951212	G	6700	4772591715	TUBE 			BELL 	47 	47G5A 	1181034	SW 										FLT CONTROL	RUSTED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	4348P		1207 			25059				DURING 1,200-HOUR INSPECTION OF INTERIOR OF FLIGHT CONTROL TUBES, 2 TUBES HAD INTERNAL RUST. REPLACED TUBES. (AD 74-07	-01.) SUBMITTER STATED THIS INSPECTION INTERVAL IS ADEQUATE AND IT COINCIDES WITH THE AIRFRAME OVERHAUL CYCLE. BELL SB	 47-11-73-1.				1	G	7	1 	3O				2H3 					 
1996011900165	19960119	00165	SW 	1996	1	19	96ZZZX266 	1	19951212	G	6700	4772414933	TUBE 			BELL 	47 	47G5A 	1181034	SW 										FLT CONTROL	RUSTED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	4348P		1207 			25059				DURING 1,200-HOUR INSPECTION OF INTERIOR OF FLIGHT CONTROL TUBES, 2 TUBES HAD INTERNAL RUST. REPLACED TUBES. (AD 74-07	-01.) SUBMITTER STATED THIS INSPECTION INTERVAL IS ADEQUATE AND IT COINCIDES WITH THE AIRFRAME OVERHAUL CYCLE. BELL SB	 47-11-73-1.				1	G	7	1 	3O				2H3 					 
1996011900166	19960119	00166	SW 	1996	1	19	96ZZZX267 	1	19951106	G	2436	15891F	REGULATOR 			BELL 	206 	206B 	1181511	SW 										DC SYSTSEM	FAILED 	B			DFUR	A				UNSCHED LANDING 				H			ELECT. POWER LOSS-50 PC 			NR	NOT REPORTED 	1			SO	09	67534	372 			4E5037	5167				PRECAUTIONARY LANDING DUE TO TOTAL ELECTRICAL FAILURE. PILOT WRITE UP: LOST ALL ELECTRICAL POWER, INSTRUMENT WENT TO Z	ERO, NO LOADMETER INDICATION. MAINTENANCE EVALUATION REVEALED VOLTAGE REGULATOR FAILED.					1	G	7	1 	3U				H2SW 					 
1996011900167	19960119	00167	WP 	1996	1	19	96ZZZX268 	1	19951130	G	5302	A02320	BRACKET 			ROBSIN	R22 	R22ALPHA 	7640104	WP 										NR 2 BULKHEAD	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	8536Y	993 				0438				INSPECTION FOUND BEARING SUPPORT BRACKET BROKEN OFF AT ATTACH POINT IN TAILBOOM. NOTE: BRACKET WAS SENT BACK TO RHC FO	R SAME REPAIR AT 617.6 HOURS TT ON SHIP 1610.					1	G	7	1 	3O				H10WE 					 
1996010500277	19960105	00277	EU 	1996	1	5	96ZZZX27 	1	19951026	G	3246	5010488	WHEEL 			SAAB 	SF340 	SF340A 	7850100	EU 										MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										AIRCRAFT'S MAIN WHEEL ASSY EXHIBITING NUMEROUS BEAD SEAT FAILURES. SUBMITTER STATED CIRCUMSTANCES OR CAUSES ARE NOT APP	ARENT, BUT THE RECURRENCE SEEMS TO INDICATE A FATIGUE OR POSSIBLE MANUFACTURING DEFECT.					2	L	7	2 	4T			RT	A52EU 					 
1996011900169	19960119	00169	GL 	1996	1	19	96ZZZX270 	2	19950718	G	7230	6871484	DIFFUSER 		6890550 	BELL 	206 	206B3 	1181506	SW 	ALLSN 	250C 	250C20B 	03013	GL 					SCROLL ASSY	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	21	2150K	4540 	857 		37682	3462	CAE834209			COMPRESSOR WAS FOUND CRACKED CAUSING HIGH TOT. COMPRESSOR IS OUT OF BALANCE AND ALSO NR 1 BEARING OIL SEAL WAS LEAKING.						1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1996011900246	19960119	00246	CE 	1996	1	19	96ZZZX271 	1	19951120	G	2750	08615584	GEAR 		556517531 	CESSNA	500 	550 	2076604	CE 										LT FLAP GEARBOX	TEETH SHEARED 	B	P		EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	1883M		271 		1128941	5500674				PILOT INDICATED THE FLAPS WOULD NOT FULLY EXTEND AT THE UPPER AIRSPEED LIMITS. INSPECTION REVEALED THE LEFT FLAP GEARBO	X WAS BAD. GEARBOX WAS DISASSEMBLED AND IT WAS FOUND TO HAVE SHEARED GEAR TEETH. INSTALLED EXCHANGE GEARBOX.					1	L	7	2 	4F				A22CE 					 
1996011900247	19960119	00247	WP 	1996	1	19	96ZZZX272 	2	19951106	G	7321	S9412028	O-RING 	WOODWARD 	8977709 	BEECH 	100 	B100 	1152919	CE 	GARRTT	TPE331	TPE3316252B 	01514	WP 					FUEL CONTROL	MISSING 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	25	49E				1709714	BE47	P27097			AFTER THE ENGINE WAS REINSTALLED IN LEFT SIDE OF AIRCRAFT AND A GROUND RUN WAS COMPLETED, A FUEL LEAK WAS NOTED AT THE F	UEL CONTROL FUEL PUMP MATING SURFACE. UPON DISASSEMBLY, FOUND O-RING WAS NOT INSTALLED. INSTALLED NEW O-RING, AND REAS	SEMBLED. GROUND RUN AND LEAK CHECK WAS SATISFACTORY. NOTE: ENGINE WAS REMOVED FOR ITT HARNESS CHANGE ONLY.				1	L	7	2 	4T	4	T		A14CE 	E2WE				 
1996011900248	19960119	00248	SW 	1996	1	19	96ZZZX273 	1	19951221	G	2435	03601018	BEARING 	LEARSIEGLER 	230790001 	SWRNGN	SA227 	SA227AT 	8780610	SW 										START/GEN AFT	FAILED 	H				A				UNSCHED LANDING 				H	E		ELECT. POWER LOSS-50 PC 	VIBRATION/BUFFET 		CR	CRUISE 	1			GL	25	300ZD		455 		3985	AT469				DURING A FLIGHT, PILOT NOTICED LEFT GENERATOR DROPPED OFF LINE AND A VIBRATION INCREASE WAS NOTICED. THE AIRCRAFT LANDE	D SAFELY AT THE MAINTENANCE FACILITY. AN INVESTIGATION FOUND THE LEFT STARTER/GENERATOR REAR BEARING HAD FAILED WHICH D	ESTROYED THE FAN AND BRUSHES AND SEVERAL OTHER PARTS. THE GENERATOR WAS REPLACED AND NO FURTHER PROBLEMS WERE NOTED. T	HE NORMAL OVERHAUL TIME FOR THIS GENERATOR IS 1,000 HOURS. IT ALSO HAS HAD MODIFICATION 'B' C/W WHICH IS AN IMPROVED BE	ARING.		1	L	7	2 	4T				A5SW 					 
1996011900250	19960119	00250	EU 	1996	1	19	96ZZZX275 	1	19951115	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GENERATOR	EXCESS WORN 	B		A	XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		200 			827					STARTER/GENERATOR BRUSHES ARE SEVERELY WORN. THE BRUSHES WERE WORN 80 PERCENT WITHIN 200.0 FLIGHT HOURS. SUBMITTER REC	OMMENDS RE-DESIGNING DEFECTIVE BRUSHES. SUBMITTER'S OPERATOR CONTROL NR XC4R95115209.					2	L	7	3 	4F				A46EU 					 
1996053000283	19960530	00283	WP 	1996	5	30	96ZZZX2750 	2	19951004	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE331* 	01514	WP 					1ST STAGE TURB	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		6487 			1233152025		P70087C			DURING REPAIR, FOUND PART CRACKED AT SEAL FLANGE. CRACK RESULTED IN .025 INCH DEFLECTION OF SEALING FLANGE AND CORRESPO	NDING LOSS OF TURBINE SECTION COOLING AIR AROUND ENTIRE DIAMETER OF SEAL CAUSING SECONDARY DAMAGE TO TURBINE SECTION COM	PONENTS. THIS IS A CRITICAL SERVICE LIFE-LIMITED COMPONENT. LIMIT - 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL E	NGINEERING DETERMINE/CORRECT CAUSE OF CRACKING. NOTE: THIS IS THE 17TH ROTATING AIR SEAL FOUND CRACKED. TOTAL CYCLES	, 7,920.							3	T			E2WE				 
1996053000284	19960530	00284	WP 	1996	5	30	96ZZZX2751 	2	19950930	G	7250	31033021	DEFLECTOR 								GARRTT	TPE331	TPE331* 	01514	WP 					2ND STG STATOR	SEPARATED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		9235 	9656 				P70013C			DEFLECTOR CHAFED ON RETAINER UNTIL COMPLETE SEPARATION FROM RETAINER. DEFLECTOR MOVED INTO CONTACT WITH 2ND STAGE TURBI	NE WHEEL RUBBING BLADE FIR TREES. IF UNDETECTED, THIS CONDITION COULD RESULT IN ROTOR BLADE FAILURE.										3	T			E2WE				 
1996053000285	19960530	00285	WP 	1996	5	30	96ZZZX2752 	2	19950706	G	7250	31038391	SEAL 		31033152 						GARRTT	TPE331	TPE331* 	01514	WP 					1ST STG TURB	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		9235 			9233151501		P70013			FOUND SEAL CRACKED AT FLANGE APPROXIMATELY 14 PLACES. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIMIT - 20,000 CYCLES	. SUGGEST ALLIED SIGNAL ENGINEERING DETERMINE/CORRECT CAUSE. THIS IS THE 12TH SEAL PLATE FOUND CRACKED AT THIS FACILIT	Y. TOTAL CYCLES, 9,656.									3	T			E2WE				 
1996053000286	19960530	00286	WP 	1996	5	30	96ZZZX2753 	2	19950928	G	7250	31038391	SEAL 		31033152 						GARRTT	TPE331	TPE331* 	01514	WP 					1ST STG TURB	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		10385			9233151437		P70010C			DURING SCHEDULED HOT SECTION INSPECTION, FOUND PART CRACKED AT FLANGE APPROXIMATELY 19 PLACES. SUGGEST ALLIED SIGNAL EN	GINEERING REVIEW PROBLEM. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT - 20,000 CYCLES. THIS IS THE 16TH ROT	ATING AIR SEAL FOUND CRACKED AND 16TH M OR D REPORT FILED ON THIS PART. TOTAL CYCLES, 10,734.									3	T			E2WE				 
1996053000287	19960530	00287	WP 	1996	5	30	96ZZZX2754 	2	19950925	G	7250	31033021	DEFLECTOR 		31037838 						GARRTT	TPE331	TPE331* 	01514	WP 					2ND STG TURB	SEPARATED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		3556 					P70128C			DEFLECTOR CHAFED ON RETAINER UNTIL IT SEPARATED COMPLETELY AND WAS LOOSE BETWEEN 2ND STATOR AND 2ND STAGE TURBINE WHEEL,	 MOVED INTO CONTACT WITH 2ND STAGE TURBINE WHEEL BLADE FIR TREE. RUBBED GROOVE IN BLADE FIR TREES. IF UNDETECTED, THIS	 CONDITION COULD RESULT IN ROTOR BLADE FAILURE - CATASTROPHIC ENGINE FAILURE. TOTAL CYCLES, 3,550.									3	T			E2WE				 
1996053000288	19960530	00288	WP 	1996	5	30	96ZZZX2755 	2	19950925	G	7250	31033021	DEFLECTOR 		31037838 						GARRTT	TPE331	TPE331* 	01514	WP 					2ND STG TURB	SEPARATED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		7335 					P70059C			DEFLECTOR CHAFED ON RETAINER UNTIL COMPLETE SEPARATION FROM RETAINER. DEFLECTOR MOVED INTO CONTACT WITH 2ND STAGE TURBI	NE WHEEL BLADE FIR TREES RUBBING ALL BLADES. IF UNDETECTED, THIS CONDITION COULD RESULT IN 2ND STAGE TURBINE WHEEL BLAD	E FAILURE. TOTAL CYCLES, 9,604.									3	T			E2WE				 
1996053000289	19960530	00289	WP 	1996	5	30	96ZZZX2756 	2	19950823	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE331* 	01514	WP 					TURB 1ST STAGE	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		5482 			1233151991		P70113C			FOUND SEAL FLANGE CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO INCREASE TENSION AGAINST 1ST STAGE ROTOR.	 INCREASED TENSION RESULTED IN CRACKING AT THE SEAL FLANGE. THIS IS A CRITICAL SERVICE LIFE-LIMITED COMPONENT. LIMIT 	- 20,000 CYCLES. SUBMITTER STATED THIS IS THE 18TH SEAL FOUND CRACKED. SUGGEST ALLIED SIGNAL REVIEW/CORRECT CONDITION.	 TOTAL CYCLES, 5,574.								3	T			E2WE				 
1996011900251	19960119	00251	CE 	1996	1	19	96ZZZX276 	1	19951212	G	3610	1013810111	VALVE 			BEECH 	300 	300BEECH 	1152930	CE 										FIREWALL SOV	DEFECTIVE 	B			VIB2	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	03	6812W	3295 			0282	FA38				RUDDER BOOST ENGAGED WHEN POWER WAS ADVANCED ABOVE 85 PERCENT. CHECKED SYSTEM, FOUND RIGHT FIREWALL SHUT-OFF VALVE OPER	ATED NORMALLY UNTIL APPLYING APPROXIMATELY 30 PSI SHOP AIR. THEN VALVE WOULD CLOSE, INDICATING ENGINE FAILURE.					2	L	7	2 	4T				A24CE 					 
1996011900252	19960119	00252	NE 	1996	1	19	96ZZZX277 	2	19951220	G	7321		FUEL CONTROL 			CESSNA	500 	560CESSNA 	2076750	CE 	PWA 	JT15 	JT15D5 	52112	NE 					LT/RT ENGINE	REQUIRED ADJUST 	D		A		D				RETURN TO BLOCK 				X			ENGINE FLAMEOUT 			TX	TAXI/GRND HDL 	1			CE	03	953F	2702 				5600005	108007			PILOT STARTED AIRCRAFT AND BEGAN TO TAXI FOR TAKEOFF, LEFT ENGINE FLAMES OUT. SHORTLY THEREAFTER, RIGHT ENGINE FLAMED OU	T WHILE RETURNING TO RAMP. CHECK MINIMUM FUEL FLOW SETTINGS. FOUND LOW, RESET PER SB 7458R1. OPERATION CHECKED GOOD. 	 SUBMITTER STATED MINIMUM FUEL FLOW SETTINGS ARE A KNOWN PROBLEM ON THIS MODEL ENGINE.				2	L	7	2 	4F	4	F	RT	A22CE 	E25EA				 
1996011900284	19960119	00284	SW 	1996	1	19	96ZZZX278 	1	19951213	G	6230	206010335001	LEVER ASSY 			BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5740L	684 				45459				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 684.2 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900285	19960119	00285	SW 	1996	1	19	96ZZZX279 	1	19951213	G	6230	206010336005	LINK IDLER 		20601350021 	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5740L	684 				45459				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 684.2 HOURS.				1	G	7	1 	3U				H2SW 					 
1996010500278	19960105	00278	NE 	1996	1	5	96ZZZX28 	2	19951213	G	7250	311269202	BEARING 			BEECH 	200 	B200 	1152922	CE 	PWA 	PT6 	PT6A42 	52043	NE 					NR 4	SPALLED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	887T					BB1233	PCE93939			DURING PRE-FLIGHT WHILE TURNING RIGHT PROPELLER, HEARD AN UNUSUAL NOISE COMING FROM POWER SECTION. INSPECTED CHIP DETEC	TOR AND MAIN OIL SCREEN AND FOUND SMALL QUANTITIES OF METAL. REMOVED POWER SECTION FOR REPAIR. FOUND NR 4 BEARING RACE	 STARTING TO SPALL. CAUSED BY METAL FATIGUE. REINSTALLED POWER SECTION AFTER REPAIR. FLUSHED OIL SYSTEM PER P & W MM.	 ENGINE WAS RETURNED TO SERVICE IAW P & W MM, PROCEDURES, AND P & W TECH REP RECOMMENDATIONS. ENGINE TT, 4,618.1 HOURS	. ENGINE TSO, 1,569.3 HOURS.		1	L	7	2 	4T	4	T		A24CE 	E4EA				 
1996011900286	19960119	00286	SW 	1996	1	19	96ZZZX280 	1	19951213	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	171AL	645 				52064				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 645.0 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1996011900287	19960119	00287	SW 	1996	1	19	96ZZZX281 	1	19951213	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L4 	1182110	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	171AL	645 				52064				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 645.0 HOURS.				1	G	7	1 	3U			NC	H2SW 					 
1996011900288	19960119	00288	SW 	1996	1	19	96ZZZX282 	1	19951113	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PLYON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3186P	427 				45776				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 426.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900289	19960119	00289	SW 	1996	1	19	96ZZZX283 	1	19951113	G	6230	206010336005	LINK IDLER 		206010336005	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3186P	427 				45776				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 426.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900290	19960119	00290	SW 	1996	1	19	96ZZZX284 	1	19951213	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2018R	364 				45681				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 363.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900291	19960119	00291	SW 	1996	1	19	96ZZZX285 	1	19951213	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2018R	364 				45681				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 363.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1996060600865	19960606	00865	EU 	1996	6	6	96ZZZX2858 	1	19951207	G	8011	31B21064	STARTER 			ZLIN 	242 	Z242L 	9970204	EU 										RING GEAR	TEETH DAMAGE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	242MC	200 				0671				DURING 400-HOUR INSPECTION WITH 200 HOURS TT, THE STARTER RING GEAR HAD TEETH MISSING FROM THE LIGHT WEIGHT STARTER 31B2	1064. SUBMITTER STATED THE STARTER DOES NOT STAY ENGAGED, SO WHEN STUDENTS ARE STARTING, THEY DO NOT HOLD KEY IN HARD E	NOUGH AND IT LETS GO AND THEN THEY JAM IT IN AGAIN.				1	L	7	1 	3O			0	A76EU 					 
1996060600866	19960606	00866	NE 	1996	6	6	96ZZZX2859 	2	19951205	G	8530		CYLINDER 			AIRTRC	AT500 	AT501 		SW 	PWA 	R1340 	R1340AN1 	52016	NE 					NR 2 EXH RKR	CRACKED 	D				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			SW	17	501BR		718 			5010123	16292			CYLINDER CRACKED COMPLETELY AT EXHAUST ROCKER ARM. THE ROCKER ARM CEASED TO FUNCTION THROWING THE FLOATING CAM RING OUT	 OF TIME. ENGINE QUIT, LANDED IN ROAD, CHANGED CYLINDER, FLEW HOME. SUSPECT POSSIBLE OVER-TORQUING OF ROCKER ARM SHAFT	 OR STUCK EXHAUST VALVE. RECOMMEND CHECKING ANY OIL LEAKS AT VALVE ROCKER ARM AND SHAFT NUTS.				1	L	7	1 	3T	3	R	NC	A17SW 	5E2				 
1996011900292	19960119	00292	SW 	1996	1	19	96ZZZX286 	1	19951213	G	6230	206010335001	LEVER ASSY 		20610350021 	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	364AL	568 				51434				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 567.5 HOURS.				1	G	7	1 	3U				H2SW 					 
1996060600869	19960606	00869	SO 	1996	6	6	96ZZZX2862 	1	19950928	G	7810		HEADER 			MAULE 	MT7235	MT7235 	5470209	SO 										EXIT JOINT	EXHAUST LEAK 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	05	773BC	146 				18012C				NUMEROUS EXHAUST HEADERS LEAKING EXCESS EXHAUST GASSES AT JOINTS TO MUFFLER. SUBMITTER STATED THE MANUFACTURER SHOULD S	IZE THESE PARTS CLOSER ON ASSY TO PREVENT CONTAMINANTS AND HEAT FROM GOING ONTO SPARK PLUG AND LEADS, AND SURROUNDING EN	GINE COMPARTMENT.				1	H	7	1 	3O			NC	3A23 					 
1996011900293	19960119	00293	SW 	1996	1	19	96ZZZX287 	1	19951213	G	6230	206010336005	LINK IDLER 		206010336005	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	364AL	568 				51434				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 567.5 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900294	19960119	00294	SW 	1996	1	19	96ZZZX288 	1	19951213	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1078N	548 				45389				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 547.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900295	19960119	00295	SW 	1996	1	19	96ZZZX289 	1	19951213	G	6230	206010336005	LINK IDLER 		206010336005	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1078N	548 				45389				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 547.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1996010500279	19960105	00279	CE 	1996	1	5	96ZZZX29 	1	19951215	G	2432	17494	BATTERY 	SAFT 		LEAR 	24 	24B 	5170306	CE 										RT BATTERY	DESTROYED 	G				O				OTHER 				H	M		ELECT. POWER LOSS-50 PC 	OVER TEMP 		CR	CRUISE 	1			GL	03	915US	63 				189				DURING FLIGHT, AIRCRAFT LOST ELECTRICAL POWER FROM RIGHT BATTERY. MAINTENANCE DISCOVERED THE RIGHT BATTERY WAS DESTROYE	D BY THERMAL RUNAWAY. THE HEAT FROM THE RIGHT BATTERY ALSO DESTROYED LEFT BATTERY. BATTERIES WERE BOTH REPLACED WITH L	EAD ACID BATTERIES.				2	L	7	2 	4J				A10CE 					 
1996011900296	19960119	00296	SW 	1996	1	19	96ZZZX290 	1	19951213	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	366AL	358 				51470				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 358.1 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900297	19960119	00297	SW 	1996	1	19	96ZZZX291 	1	19951213	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	366AL	358 				51470				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 358.1 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900298	19960119	00298	SW 	1996	1	19	96ZZZX292 	1	19951213	G	6230	20601035001	LEVER ASSY 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27554	548 				45246				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 548.2 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900299	19960119	00299	SW 	1996	1	19	96ZZZX293 	1	19951213	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L1 	1182107	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27554	548 				45246				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 548.2 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900300	19960119	00300	SW 	1996	1	19	96ZZZX294 	1	19951213	G	6230	206010335001	LEVER ASSY 		206010335001	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	343AL	376 				51372				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 375.8 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900301	19960119	00301	SW 	1996	1	19	96ZZZX295 	1	19951213	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	343AL	376 				51372				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 375.8 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900302	19960119	00302	SW 	1996	1	19	96ZZZX296 	1	19951212	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	355AL	450 				51444				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 449.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900303	19960119	00303	SW 	1996	1	19	96ZZZX297 	1	19951212	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	355AL	450 				51444				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 449.9 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900304	19960119	00304	SW 	1996	1	19	96ZZZX298 	1	19951213	G	6230	206010335001	LEVER ASSY 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL	522 				51460				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 521.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1996011900305	19960119	00305	SW 	1996	1	19	96ZZZX299 	1	19951213	G	6230	206010336005	LINK IDLER 		206010350021	BELL 	206 	206L3 	1182108	SW 										PYLON	WORN 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	358AL	522 				51460				DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3	38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01	0-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 521.7 HOURS.				1	G	7	1 	3U				H2SW 					 
1996010500280	19960105	00280	EA 	1996	1	5	96ZZZX3 	2	19950615	G	7230	3032208	BEARING 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					COMP NR 1	FRACTURED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	119YV	76 			FC27221	UC119	32026			THERE ARE TWO AREAS THAT ARE BEING TAKEN UNDER INVESTIGATION WITH THIS ENGINE. A MATERIAL FAILURE OF THE NR 1 BEARING A	ND A BAD STARTER GENERATOR.					2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1996011900306	19960119	00306	SW 	1996	1	19	96ZZZX300 	1	19951213	G	6720	206011809109	PITCH HORN 		206011810151	BELL 	206 	206L4 	1182110	SW 										T/R BLADE	LOOSE STUD 	B			ALGR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	175AL	1593 			PEFS1433	52117				DURING DAILY INSPECTION, FOUND THE PITCH LINK STUD ON THE PITCH HORN WAS LOOSE. SUSPECT CAUSE IS THE STUD WAS NOT PERMA	NENTLY SECURED AT THE FACTORY. ALSO, THE PITCH HORN WAS NOT PROPERLY TORQUED AT THE FACTORY CAUSING THE PITCH HORN TO B	ECOME LOOSE ON THE TAIL ROTOR BLADE.				1	G	7	1 	3U			NC	H2SW 					 
1996011900307	19960119	00307	NE 	1996	1	19	96ZZZX301 	1	19951219	G	6210	7615009015050	TIP RIB 			SKRSKY	S76 	S76A 	8143006	NE 										M/R BLADE	SEPARATED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1547N	3431 	318 			760088				MAIN ROTOR BLADE TIP RIB WAS FOUND SEPARATED. IT WAS DISCOVERED DURING THE 500-HOUR INSPECTION. TIP RIB AND DOUBLER SE	PARATED. SUBMITTER STATED POSSIBLY CAUSED BY EXCESS PRESSURE APPLIED TO TIP CAP SCREWS DURING TIP CAP INSTALLATION. CO	MPONENT NR 7615009100051A.				1	G	7	2 	3U				H1NE 					 
1996061300711	19960613	00711	SW 	1996	6	13	96ZZZX3015 	1	19951208	G	2910	P10M47	SWITCH 			GULSTM	690TP 	695 	7630518	SW 										LT MLG WELL	FAILED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	23	3U	3111 			631	95041				UPON ARRIVAL OF AIRCRAFT, PILOT REPORTED HYDRAULIC FLUID COMING FROM LT GEAR WELL. UPON FURTHER INVESTIGATING, FOUND FA	ILED HYDRAULIC SWITCH.					1	H	7	2 	3T				2A4 					 
1996062000752	19960620	00752	EU 	1996	6	20	96ZZZX3068 	1	19950731	G	2731	LP150270105	DRIVE MOTOR 			WSK 	150A 	PZL150A 	05625QK	EU 										PITCH TRIM	SEIZED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	150P	99 			9406005	04940065				REFERENCED AIRCRAFT WAS BROUGHT TO MAINTENANCE WITH A REPORT OF 'PITCH TRIM INOPERATIVE'. INVESTIGATION TRIM MOTOR/DRIV	E ASSEMBLY SEIZED WHICH RENDERED TRIM UNUSABLE AND JAMMED IN FAILED POSITION. THE ENTIRE MOTOR AND GEARBOX WAS FULL OF 	RUST FROM WATER INTRUSION. THIS IS A FOREIGN-BUILT, IMPORTED AIRCRAFT.				1	L	7	1 	3O			NT	A69EU 					 
1996062000766	19960620	00766	EU 	1996	6	20	96ZZZX3082 	1	19950929	G	3213	LF880420041	AXLE 			WSK 	150A 	PZL150A 	05625QK	EU 										NLG	FAILED 	D				C				ABORTED TAKEOFF 				O			OTHER 			TO	TAKEOFF 	1			EA	25	150AD	682 				03930057				NOSE WHEEL AXLE BROKE OFF ON TAKEOFF ROLL, DAMAGE TO NOSE GEAR FORK ASSEMBLY. REPLACED FORK AND AXLE. OPS CHECK OK.						1	L	7	1 	3O			NT	A69EU 					 
1996062000767	19960620	00767	SO 	1996	6	20	96ZZZX3083 	2	19951121	G	8530	640501	SLEEVE 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520L 	17032	SO 					NR 3 CYLINDER	AIR LEAK 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	37404	19 				421C0339	292086R			PILOT REPORTED HAVING A LOW FUEL FLOW INDICATION. INSPECTION REVEALED AN AIR LEAK IN THE UPPER DECK, NR 3 CYLINDER SLEE	VE, WHERE THE SHAFT AND BLOCK CONNECT. SUBMITTER RECOMMENDS VISUAL INSPECTION AND IF NECESSARY, PART REPLACEMENT.					1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1996010500389	19960105	00389	CE 	1996	1	5	96ZZZX31 	1	19951120	G	2910	228000113	LINE 			CESSNA	182 	TR182 	2072735	CE 										HYD PRES	CHAFED 	D	L	A		O				OTHER 				K			FLUID LOSS 			AP	APPROACH 	1			NM	11	4664S	2017 				R18201371				PILOT UNABLE TO GET A GREEN MLG DOWN LIGHT WITH EITHER THE HYD POWER PACK OR USING EMERGENCY GEAR EXT HAND PUMP. AFTER 	TOUCH DOWN, THE RT MLG COLLAPSED CAUSING MODERATE DAMAGE TO ACFT. AN INVESTIGATION FOR THE CAUSE DETERMINED THE THROTTL	E CABLE HAD CHAFED A HOLE IN THE HYD PRESS LINE RESULTING IN A LOSS OF ALL THE HYDRAULIC FLUID. THE LINE RUNS FROM LAND	ING GEAR SELECTOR VALVE. THE CHAFING OCCURRED JUST AFT OF THE FIREWALL AT THE POINT WHERE THE THROTTLE CABLE PASSES THR	OUGH THE FIREWALL.		1	H	7	1 	3O				3A13 					 
1996062700353	19960627	00353	SW 	1996	6	27	96ZZZX3168 	1	19950822	G	6210	206015001107	BLADE 			BELL 	206 	206L4 	1182110	SW 										M/R	DEBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	171AL	2214 			A1071	52064				DAILY INSPECTION FOUND OUTBOARD SKIN AT TIP OF BLADE DEBONDED (TOP SIDE). PART DEBONDED BEYOND REPAIR.						1	G	7	1 	3U			NC	H2SW 					 
1996010500390	19960105	00390	EA 	1996	1	5	96ZZZX32 	2	19951128	G	8530		INJECTOR TUBE 			PIPER 	PA31 	PA31P350 	7103111	SO 	LYC 	O540 	TIO540V2AD 	41532	EA 					LT ENG NR 4 CYL	BROKEN 	D	L			C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		TO	TAKEOFF 	1			SW	01	9224Y					31P8414012	L846061A			PILOT REPORTED LT ENGINE RAN ROUGH & RPM WAS LOW ON TAKEOFF. TAKEOFF ABORTED. FOUND LT ENG, NR 4 CYL FUEL INJECTOR TUB	E FROM FUEL MANIFOLD TO FUEL INJECTOR NOZZLE BROKEN AT SOLDERED FITTING ON MANIFOLD END OF TUBE. TUBE APPEARED TO HAVE 	BEEN PREVIOUSLY BENT ON THE SOLDERED PART OF TUBE, POSSIBLY DURING ENGINE MAINTENANCE. ALSO NOTED ALL INJECTOR TUBES ON	 BOTH ENGINES WERE CLAMPED IN A RANDOM MANNER WITH INSUFFICIENT CLEARANCES AND INCORRECT HARDWARE, NOT IAW WITH AD 93-02	-5 AND LYCOMING SB 342A.		1	L	7	2 	3O	3	O	RT	A8EA 	E14EA				 
1996062700690	19960627	00690	GL 	1996	6	27	96ZZZX3243 	1	19951012	G	2810		VENT LINE 			AMTR 	N3 	N3 	05628FX	GL 										HEADER TANK	MISINSTALLED 	D				O				OTHER 				Y			ENGINE STOPPAGE 			NR	NOT REPORTED 	1			WP	07	48HP					N32HP				FUEL HEADER TANK NOT VENTED PROPERLY - TANK PRESSURIZED (APPARENTLY) AND STARVED ENGINE. FUEL VENT LINE INSTALLED PROPE	RLY TO SOLVE MALFUNCTION.					1	H	7	1 	3O			NC	EXPA1H71					 
1996010500391	19960105	00391	SW 	1996	1	5	96ZZZX33 	1	19951201	G	3213		GEAR LEG 			TMPSON	NAVION	NAVIONA 	6150104	SW 										LT/RT MLG	WELD BROKEN 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	91689					4432				DURING INSPECTION, FOUND EXCESS FORE/AFT MOVEMENT OF MLG LEG DUE TO A BROKEN WELD.						1	L	7	1 	3O				A782 					 
1996010500392	19960105	00392	SO 	1996	1	5	96ZZZX34 	1	19951120	G	5320	6867800	DOUBLER 			PIPER 	PA32 	PA32260 	7103206	SO 										CABIN STEPS	CORRODED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	3369W	17723				321054				STEEL CHANNEL THAT SUPPORTS CABIN STEP WAS SEVERELY CORRODED AND CORROSION CARRIED THROUGH TO SKIN. STEP BEGAN TO BREAK	 THROUGH SKIN. SUBMITTER SUGGESTS STEP REMOVAL AND CLOSE INSPECTION OF SKIN. THERE IS NO WAY TO INSPECT CHANNEL UNLESS	 IT IS BEING REMOVED. SMALL DRAIN HOLE SHOULD BE PLACED FORWARD OF CHANNEL TO HELP PREVENT THIS.				1	L	7	1 	3O				A3SO 					 
1996012600421	19960126	00421	CE 	1996	1	26	96ZZZX345 	1	19951130	G	3230	571304022	ATTACH LUG 			CESSNA	421 	421C 	2076016	CE 										NLG ACTUATOR	FAILED 	B	L	A	LN3R	O				OTHER 				J			WARNING INDICATION 			CL	CLIMB 	1			WP	07	888HT	3078 				421C0290				PILOT REPORTED 'GEAR UNLOCKED' LIGHT STAYED ON WHEN GEAR SELECTED UP AFTER TAKEOFF. AFTER A FLY-BY, THE TOWER TOLD PILO	T NOSE GEAR WAS HANGING DOWN, IN TRAIL. PILOT SELECTED GEAR DOWN AND ALL 3 GREEN DOWN AND LOCKED LIGHTS CAME ON AS THE 	UNLOCKED LIGHT WENT OUT. A NORMAL LANDING WAS MADE AND ACFT WAS TURNED OVER FOR REPAIR. INSPECTED THE LANDING GEAR RET	RACTION SYSTEM AND FOUND BOTH NOSE LANDING GEAR RETRACT ACTUATOR ATTACH LUGS (PN 5713040-22'S) HAD BROKEN WHERE THEY ATT	ACH TO THE END BOSS OF THE ACTUATOR. THIS PROBABLY HAPPENED WHEN THE GEAR WAS SELECTED UP AFTER TAKEOFF AND ALLOWED THE	 NOSE GEAR TO TRAIL IN THE SLIPSTREAM.	1	L	7	2 	3O				A7CE 					 
1996012600422	19960126	00422	SO 	1996	1	26	96ZZZX346 	1	19950927	G	5610	1815604	WINDOW 			PIPER 	PA23 	PA23250 	7102308	SO 										COCKPIT LT FWD	DEPARTED 	D		A		O				OTHER 				D			INFLIGHT SEPARATION 			CR	CRUISE 	1			NM	04	40215					277305014				LEFT FRONT WINDOW BLEW OUT AT FL 250, PUTTING AIRCRAFT IN SPIN. THE WINDOW DEPARTED AND HIT AFT SECTION OF ENGINE NACEL	LE AND TORE SKIN. RIGHT FRONT WINDOW ALSO CRACKED.					1	L	7	2 	3O				1A10 					 
1996012600423	19960126	00423	CE 	1996	1	26	96ZZZX347 	1	19951117	G	3230	HM5S	ROD END 			BEECH 	35 	E35 	1151512	CE 										NLG RETRACT	FAILED 	G	S			O				OTHER 				O			OTHER 			LD	LANDING 	1			CE	01	7309B	4590 				D3772				NOSE GEAR COLLAPSED ON LANDING. SUBSEQUENT INSPECTION REVEALED A FAILED ROD END ON THE NOSE GEAR RETRACT LINK. INSPECT	ION OF THE FAILED ROD END SHOWS INDICATIONS OF STRESS FRACTION PRIOR TO TOTAL FAILURE. EVIDENCE SUGGESTS THE ROD END WA	S BENT AT SOME TIME PREVIOUS TO THE INCIDENT. SUBMITTER STATED PERHAPS THE RETRACT LINK ROD ENDS SHOULD BE INSPECTED AT	 REGULAR INTERVALS FOR SIGNS OF BENDING OR IMMINENT FAILURE.			1	L	7	1 	3O				A777 					 
1996012600425	19960126	00425	EA 	1996	1	26	96ZZZX349 	2	19951204	G	8520	71105ASR177	TAPPET 			CESSNA	150 	152 	2071835	CE 	LYC 	O235 	O235L2A 	41505	EA 					NR 4 CYLINDER	DEFECTIVE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	24883		1770 			15280430	L1987815			ENGINE EXPERIENCED INTERMITTENT MISS. WHILE TROUBLESHOOTING, DISCOVERED NR 4 CYLINDER ROCKER TO VALVE CLEARANCE COULD N	OT BE SET PROPERLY. ENGINE TORN DOWN AND FOUND TWO TAPPETS DEFECTIVE. SOCKET END WAS LOOSE AND TURNED FREELY IN END OF	 BODY. CAUSED EXCESSIVE WEAR ON SOCKET TO THE POINT THAT VALVE ADJUSTMENT NOT ATTAINABLE. TWO OF THE EIGHT HAD THIS CO	NDITION. BOTH ON NR 4 CYLINDER.			1	H	7	1 	3O	3	O	NT	3A19 	E223				 
1996010500393	19960105	00393	SW 	1996	1	5	96ZZZX35 	1	19951127	G	3710	860015	HOSE 	KING 	KI526 	MOONEY	M20 	M20J 	5870219	SW 										GYRO VACUUM	FAILED 	D		A		A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			GL	25	9119Y					243265				AFTER PERFORMING AN ANNUAL INSPECTION WHICH INCLUDED CHANGING THE VACUUM SYSTEM CENTRAL AIR FILTER, THE ACFT DIVERTED FR	OM ITS FLIGHT PLAN TO MAKE A PRECAUTIONARY LANDING DUE TO A HORIZON GYRO FAILURE. FOUND ONE OF THE LATEX TUBES USED AS 	A VACUUM LINE IN THE LATE MODEL MOONEYS HAD FOLDED OVER RESTRICTING VACUUM TO THE HORIZON AND CAUSING THE HORIZON TO FAI	L.			1	L	7	1 	3O				2A3 					 
1996012600426	19960126	00426	EA 	1996	1	26	96ZZZX350 	2	19951215	G	7313	LW18265	INJECTOR 			PIPER 	PA28 	PA28R201 	7102816	SO 	LYC 	O360 	IO360C1C6 	41514	EA 					CYL INTAKE PORT	NOZZLE CLOGGED 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			NE	01	53995		1 			28R7918258	L2000151A			THE ENGINE HAD BEEN INSTALLED AFTER OVERHAUL. OVERHAULER DID RUN-UP AND REPORTED THAT ENGINE WAS SATISFACTORY. COMPLET	ED THE INSTALLATION WITH NEW MOUNT, VIBRATION ISOLATORS, AND COMPLETE HOSE KIT. TEST RAN ON THE GROUND FOR .7 HOUR WHIC	H GAVE SATISFACTORY RESULTS. APPROXIMATELY 10 SECONDS INTO FIRST FLIGHT, VIBRATION WAS ENCOUNTERED. FLOW CHECKED NOZZL	ES, ONE WAS CLOGGED. CALLED OVERHAULER ABOUT PROBLEM AND RECEIVED NEW NOZZLE. OPERATION SINCE THEN HAS BEEN SATISFACTO	RY.		1	L	7	1 	3O	3	O		2A13 	1E10				 
1996012600427	19960126	00427	SO 	1996	1	26	96ZZZX351 	1	19951218	G	3020	P461	CONNECTOR 			PIPER 	PA31T 	PA31T 	7103124	SO 										DEICE SYSTEM	WIRES BURNED 	D				K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			CE	01	150BC					31T8104045				ON START-UP, PILOT REPORTED SEVERAL ENVIRONMENTAL AND DE-ICE SYSTEM CIRCUIT BREAKERS 'POPPED'. INVESTIGATION REVEALED W	IRE BUNDLES AT PLUGS P461 AND P462, BURNED AND MELTED. FURTHER INVESTIGATION REVEALED SHORTED WIRES. INVESTIGATION REV	EALED SHORTED WIRES AT LT ENGINE DE-ICE DIVERTER MOTOR PLUG AND SHORTED/MELTED WIRES AT RT ENGINE INLET LIP PLUG. ALSO,	 SOME WIRES MELTED BEHIND INSTRUMENT PANEL.			1	L	7	2 	3T				A8EA 					 
1996012600430	19960126	00430	SO 	1996	1	26	96ZZZX354 	1	19951107	G	2720		CONTROL CABLE 			PIPER 	PA28 	PA28181 	7102807	SO 										RUDDER	CROSSED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	01	3344Q	1567 				287790452				WHILE PERFORMNG AN ANNUAL INSPECTION, FOUND THE RUDDER CABLES WERE CROSSED IN THE TAIL. THE CONTROL SURFACES WERE REMOV	ED FOR BALANCE CHECKING AFTER REPAINTING ABOUT SIX MONTHS PRIOR. THIS WAS THE ONLY LOGGED ENTRIES ABOUT THE CONTROL SYS	TEM IN THE LAST YEAR.				1	L	7	1 	3O			 	2A13 					 
1996012600431	19960126	00431	CE 	1996	1	26	96ZZZX355 	1	19951221	G	2510		SUPPORT STRAP 			BBAVIA	8 	8KCAB 	2110612	CE 										FORWARD SEAT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	1177E	620 				31577				FACTORY EXCHANGE FORWARD PILOT SEAT PREVIOUSLY INSTALLED 11-03-89 IAW AD 89-18-06, FOUND SEVERELY BENT, STRETCHED, AND C	RACKED SUPPORT WEB STRIPS. SUBMITTER STATED WITH HIGH G-LOAD FACTORS, SUGGEST RE-ENGINEERING OF SUPPORT SYSTEM.					1	H	7	1 	3O				A21CE 					 
1996012600432	19960126	00432	CE 	1996	1	26	96ZZZX356 	1	19951227	G	8011	MHB4016R	STARTER 	PRESTOLITE 		CESSNA	172 	172P 	2072436	CE 										HOUSING	SCREWS BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	99870				5020876	17276519				FOUND STARTER WITH 3 OUT OF 4 HOUSING SCREWS BROKEN OFF. 212 HOURS SINCE OVERHAUL.						1	H	7	1 	3O			NT	3A12 					 
1996012600433	19960126	00433	CE 	1996	1	26	96ZZZX357 	1	19951219	G	5320	504300431183	INTERCOSTAL 		504300431257	BEECH 	90 	E90 	1152914	CE 										DOOR SUPPORT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	99AC	7608 				LW120				INTERCOSTAL FOUND CRACKED. THIS PART SUPPORTS CABIN DOOR HAND RAIL AND IF FAILED, WILL CAUSE DOOR TO STRIKE THE GROUND.	 SUBMITTER STATED DOOR NEEDS DUAL SUPPORT CABLES TO ELIMINATE THIS PROBLEM.					1	L	7	2 	3T				3A20 					 
1996012600435	19960126	00435		1996	1	26	96ZZZX359 	4	19951128	G	6113	3532309	BULKHEAD 			PIPER 	PA28 	PA28161 	7102803	SO 										SPINNER FORWARD	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	38989	310 				287716310				FRONT SPINNER BULKHEAD BROKEN. SUBMITTER STATED THIS HAS BEEN AN ONGOING PROBLEM SINCE THEY WERE HEAT TREATED.						1	L	7	1 	3O				2A13 					 
1996010500394	19960105	00394	CE 	1996	1	5	96ZZZX36 	1	19951121	G	5510	17320631	BRACKET 			CESSNA	177 	177B 	2073708	CE 										STAB BAL WT	MISMANUFACTURED 	B		A	VWIR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	11	34695					177001943				AFTER RECEIVING PARTS FROM CESSNA PARTS DIVISION TO ACCOMPLISH SEB 89-1, 'STABILATOR BALANCE WEIGHT ATTACH BRACKETS' NOT	ICED THAT LT BRACKET WAS MANUFACTURED BACKWARDS TO RESEMBLE THE DASH 2 RT BRACKET. LATER, WAS NOTIFIED THE WHOLE BATCH 	FROM CESSNA WAS MADE WRONG.				1	H	7	1 	3O				A13CE 					 
1996012600436	19960126	00436		1996	1	26	96ZZZX360 	4	19951222	G	6113	3532309	BULKHEAD 			PIPER 	PA28 	PA28161 	7102803	SO 										SPINNER FORWARD	BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	2289M	205 				287816274				FRONT SPINNER BULKHEAD BROKEN. SUBMITTER STATED THIS HAS BEEN AND ONGOING PROBLEM.						1	L	7	1 	3O				2A13 					 
1996012600437	19960126	00437	SO 	1996	1	26	96ZZZX361 	1	19951103	G	5540	2570400	BEARING 		7760502 	PIPER 	PA38 	PA38112 	7103812	SO 										LOWER RUDDER	WRONG PART 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NE	01	4447E	238 				3878A0609				LOWER RUDDER HINGE HAD EXCESS PLAY WITH ATTACH BOLT COCKED IN HINGE. DISASSEMBLY REVEALED A SPHERICAL SELF-ALIGNING BEA	RING INSTALLED IN LOWER HINGE AND A FIXED BEARING INSTALLED IN UPPER HINGE. REPLACEMENT PART FOR LOWER BEARING WAS AN I	DENTICAL SPHERICAL BEARING. THE UPPER HINGE BEARING WITH FIXED BUSHING IS ORIGINAL TO AIRCRAFT. SUBMITTER STATED THE S	PHERICAL SELF-ALIGNING BEARING NOW SUPPLIED AS PN 25704-00 MERELY SERVES TO INTRODUCE EXCESSIVE MOVEMENT OF THE HINGE AN	D IS THE WRONG TYPE OF BEARING FOR A CONTROL SURFACE HINGE.		1	L	7	1 	3O				A18SO 					 
1996012600438	19960126	00438	GL 	1996	1	26	96ZZZX362 	1	19951224	G	3250	1944140	STEERING COLLAR 			BLANCA	17 	1730A 	1220433	GL 										NLG	FAILED 	H		A		O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			SO	03	9558E	2050 				7630798				DURING TAKEOFF ROLL, NOSE GEAR COLLAPSED. UPON INVESTIGATION, THE REAR STEERING COLLAR ASSEMBLY WAS FOUND BROKEN, WHICH	 ALLOWED NOSE WHEEL TO PIVOT FREELY. THE NOSE WHEEL PREPARED TO HAVE TURNED 90 DEGREES FROM ITS CENTER POSITION WHICH, 	IN TURN, ALLOWED THE NOSE GEAR TO OVERCENTER AND RETRACT. SUBMITTER STATED CAREFUL ATTENTION SHOULD BE PAID IN THE VICI	NITY OF NOSE GEAR AND STEERING COLLAR FOR FATIGUE AND CRACKS. EXTREME CARE SHOULD BE EXERCISED WHEN TOWING THE AIRCRAFT	 NOT TO EXCEED THE TOWING LIMITS.		1	L	7	1 	3O				A18CE 					 
1996012600439	19960126	00439	CE 	1996	1	26	96ZZZX363 	1	19951204	G	5522	9661000515	SKIN 			BEECH 	55 	95B55A 		CE 										LT UPPER ELEV	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	661KQ					TC2293				CORROSION IN THE ELEVATOR AND VIBRATION APPEARS TO HAVE CAUSED THE SKIN TO CRACK. PREVIOUS CRACKING AND PIECE CAME OUT.	 ALUMINUM PATCH PUT ON MAG SKIN USING BONDO AND CHERRY RIVETS, WITHOUT ANY BALANCING OR LOG ENTRIES. BHM ALSO ISSUED A	 CONDITION REPORT AND THIS EXPLAINS WHAT WAS FOUND. AIRCRAFT HAS 4,781 HOURS.				1	L	7	2 	3O				3A16 					 
1996012600440	19960126	00440	SO 	1996	1	26	96ZZZX364 	1	19951204	G	8120	LW318444	BOLT 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					TURBO MOUNT	LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	3582X	1300 				318052105				BOLTS THAT SECURE TURBO MOUNT TRUSS TO ENGINE MOUNT PYLONS CONTINUALLY WORK LOOSE. NUTS CHATTER ON THREADS AND WEAR TO 	A POINT WHERE RE-TORQUING IS NOT POSSIBLE. MAIN PROBLEM IS STEEL BOSS ON TURBO MOUNT EATING INTO ALUMINUM MOUNT PYLON. 	 SUBMITTER SUGGESTS SHOULDERED STEEL BUSHING BE PRESS-FIT INTO ALUMINUM ENGINE MOUNT PYLON TO BEAR STRAPS OF TURBO MOUNT	. ALSO, SUGGEST FINE THREAD BOLTS RATHER THAN COARSE TO HELP PREVENT TORQUE LOSS WITH MINOR SHIFTING OF KEYED, CASTELLA	TED NUT.		1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1996012600441	19960126	00441	SO 	1996	1	26	96ZZZX365 	1	19951206	G	2140	07D67	FAN WHEEL 	JANITROL 		PIPER 	PA31 	PA31350 	7103110	SO 										COMB BLOWER	DISINTEGRATED 	B			APCR	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	01	2140	289 				318052105				FAN WHEEL DISINTEGRATED - ONLY END PLATE LEFT. ALL VANES GONE. MULTIPLE FAILURES OF THESE UNITS RECENTLY. SUBMITTER S	TATED APPEARS TO BE CAUSED BY IMBALANCE. FAN WHEELS USED TO COME WITH METAL BALANCE - CLIPS ON VANES. NO LONGER COME T	HAT WAY. SOME VIBRATE SO BADLY THAT COMBUSTION BLOWER MOTORS HAVE BEEN DESTROYED.				1	L	7	2 	3O				A20SO 					 
1996012600443	19960126	00443	CE 	1996	1	26	96ZZZX367 	1	19951213	G	2720	0433113	BELLCRANK 			CESSNA	170 	170B 	2072306	CE 										RUDDER	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	2799C	3409 				26343				CHECKED PLAY IN RUDDER BOLT, FOUND HOLE WORN ALMOST THROUGH TOP OF BELLCRANK. HOLE CAUSED BY BEARING BLOCK. SUBMITTER 	STATED UNABLE TO INSPECT HOLE UNLESS BOLT AND WASHER ARE REMOVED.					1	H	7	1 	3O				A799 					 
1996010500395	19960105	00395	CE 	1996	1	5	96ZZZX37 	1	19951030	G	7602	5038901223	CONTROL CABLE 			BEECH 	58 	58 	1152740	CE 										RT ENG MIXTURE	SEPARATED 	E		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	1888W	284 				TH340				RIGHT ENGINE FAILED TO START. FOUND RT MIXTURE CABLE THREADED END AT ENGINE HAD SEPARATED FROM THE CABLE WHERE END IS S	WAGED TO INNER CABLE.					1	L	7	2 	3O			 	3A16 					 
1996012600446	19960126	00446	SO 	1996	1	26	96ZZZX370 	1	19951211	G	7810	4031010	PIPE 			PIPER 	PA31 	PA31350 	7103110	SO 										TURBO EXHAUST	CRACKED 	B			W6NR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25	27368					317852010				UPON UNCOWLING THE RIGHT ENGINE FOR AN OIL CHANGE, A HOLE WAS FOUND IN THE EXHAUST PIPE OF THE TURBOCHARGER. A NEW PIPE	 WAS INSTALLED. THE HOLE WAS APPROXIMATELY 2 INCHES BY 2 INCHES WITH A 4 INCH CRACK OUT FROM THE EDGE OF THE HOLE. NO 	OTHER DAMAGE WAS FOUND.				1	L	7	2 	3O				A20SO 					 
1996012600447	19960126	00447	EA 	1996	1	26	96ZZZX371 	2	19951222	G	8550		LINE 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					OIL RETURN	LOOSE 	D				O				OTHER 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			EA	23	738UD	980 				17270240	L829076T			PILOT REPORTED SMOKE IN COCKPIT AFTER APPLYING CABIN HEAT. REMOVED COWLING AND INSPECTED MUFFLER ASSEMBLY. SMALL OIL S	TAIN ON MUFFLER SHROWD. FOUND OIL RETURN LINES WERE SLIGHTLY 'WET' WITH OIL. TIGHTENED OIL RETURN LINE CLAMPS. WASHED	 DOWN ENGINE AND MUFFLER SHROWD. MADE A LOG BOOK ENTRY, AND RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1996012600448	19960126	00448	EA 	1996	1	26	96ZZZX372 	2	19951227	G	8510	71328	RING GEAR 			PIPER 	PA24 	PA24250 	7102404	SO 	LYC 	O540 	O540A1C5 	41532	EA 					STARTER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	13	5252P	3288 				24284	L161440			DURING ANNUAL INSPECTION, STARTER RING GEAR SUPPORT ASSEMBLY WAS FOUND CRACKED BETWEEN 2 BOLT HOLES, 1 INCH LONG. THIS 	CAN BE INSPECTED ONLY IF PROPELLER IS REMOVED. SUBMITTER SUGGESTS THIS AREA BE INSPECTED AT LEAST EVERY 1,000 HOURS.					1	L	7	1 	3O	3	O		1A15 	E295				 
1996072500571	19960725	00571	WP 	1996	7	25	96ZZZX3725 	2	19951028	G	7250	31081261	BLADE 								GARRTT	TPE331	TPE33112UAR 	01514	WP 					1ST STAGE TURB	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		2672 					P70012			ENGINE DISASSEMBLY TO INVESTIGATE AND REPAIR TURBINE SECTION FAILURE REVEALED CAUSE TO BE FIRST STAGE ROTOR BLADE FAILUR	E. BLADE SEPARATED AT FIR TREE AIR PASSAGE. TURBINE SECTION COMPONENTS IN DOWNSTREAM GAS PATH EXPERIENCED SEVERE UNREP	AIRABLE DAMAGE DUE TO BLADE FAILURE/IMPACT. NO SIGNS OF ABNORMAL OPERATION PRIOR TO BLADE FAILURE. METALLURGICAL CASTI	NG DEFECT (MICRO-SHRINGKAGE) AS POSSIBLE CAUSE. CYCLES, 2,639.								4	T			E4WE				 
1996012600450	19960126	00450	SO 	1996	1	26	96ZZZX374 	1	19951207	G	7160	5325998	AIR BOX 			MAULE 	M5 	M5180C 	5460204	SO 										CARBURETOR	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	66VJ	198 				8077C				FOUND CARBURETOR AIR BOX EXTENSIVELY CRACKED IN THROAT AREA. SUBMITTER STATED THIS IS A CONTINUAL PROBLEM. DESIGN APPE	ARS TO BE FAULTY. NEEDS ADDITIONAL SUPPORT FOR FATIGUE RESISTANCE. THE CRACKED UNIT ALLOWS UNFILTERED AIR INTO ENGINE.					1	H	7	1 	3O				3A23 					 
1996012600451	19960126	00451	CE 	1996	1	26	96ZZZX375 	1	19951113	G	3230	AN6227B10	O-RING 			BEECH 	76 	76 	1153005	CE 										LT MLG CYLINDER	FAILED 	G				K				NONE 				K	W		FLUID LOSS 	INADEQUATE Q C 		IN	INSP/MAINT 	1			SO	15	6701V					ME297				UPON DISASSEMBLY OF THE LEFT LANDING GEAR RETRACT/EXTENSION CYLINDER, THE MAIN END CAP O-RING (AN 6227 B-10) WAS FOUND T	O HAVE FAILED. THIS O-RING CONTAINS THE FLUID AND KEEPS IT FROM ESCAPING TO AN EXTERNAL LEAK ON THE LANDING GEAR DOWN S	IDE. UPON CLOSE EXAMINATION OF THE FAILED O-RING, DETERMINED THE FAILIURE WAS CAUSED BY THE O-RING BEING INSTALLED WITH	 A TWIST, WHICH IS STILL EVIDENT IN THE OLD O-RING. THIS TWIST CAUSED A PRE-LOAD IN THE CROSS SECTION WHICH EVENTUALLY 	CAUSED THE FAILURE AND SUBSEQUENT FLUID LOSS.		1	L	7	2 	3O				A29CE 					 
1996012600452	19960126	00452	CE 	1996	1	26	96ZZZX376 	1	19951219	G	5210	504300431183	INTERCOSTAL 		504300431257	BEECH 	100 	B100 	1152919	CE 										CABIN DOOR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	3699B	5740 				BE107				INTERCOSTAL FOUND CRACKED. THIS PART SUPPORTS CABIN DOOR HAND RAIL AND IF IT FAILS, WILL CAUSE DOOR TO STRIKE THE GROUN	D. DOOR NEEDS DUAL SUPPORT CABLES TO ELIMINATE THIS PROBLEM.					1	L	7	2 	4T				A14CE 					 
1996080200461	19960802	00461	CE 	1996	8	2	96ZZZX3765 	1	19950316	G	2731	17121421	BELLCRANK 			CESSNA	177 	177RG 	2073709	CE 										ELEVATOR TRIM	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	1989Q	3799 				177RG0389				DURING PRE-BUY INSPECTION, FOUND STABILATOR TRIM TAB TO HAVE EXCESSIVE FREE PLAY. THE BELLCRANK AT THE STABILATOR WAS W	ORN. THE BOLT HOLES WERE ENLARGED AND THE RIVETS ATTACHING THE STIFFENER WERE LOOSE. SUBMITTER SUGGESTS CLOSE INSPECTI	ON OF FLIGHT CONTROLS DURING ALL INSPECTIONS.				1	H	7	1 	3O				A20CE 					 
1996012600453	19960126	00453	NE 	1996	1	26	96ZZZX377 	2	19951213	G	7250	694702	SUPPORT ASSY 		589741 						PWA 	JT9 	JT9* 	52054	NE 					NR 3 BEARING	FAILED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	11							X685710			BRITISH AIRWAYS EXPERIENCED AN ENGINE CONDITION SHOWING HIGH OIL CONSUMPTION ON ONE OF THEIR ENGINES. AN INVESTIGATION 	LED TO A COMPONENT ASSEMBLY FAILURE LOCATED IN THE NR 3 BEARING COMPARTMENT. SUBMITTER RECOMMENDATIONS: COMPLY WITH PR	ATT AND WHITNEY'S SB NR 3985.									4	F			E20EA				 
1996012600454	19960126	00454	CE 	1996	1	26	96ZZZX378 	1	19951219	G	2750	556517531	GEARBOX 			CESSNA	500 	500CESSNA 	2076602	CE 										LEFT FLAP	FAILED 	E				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	10UH		113 			5000304				FLAP GEARBOX, LEFT. INTERNAL GEARS FAILED AT 113 HOURS FROM CESSNA OVERHAUL. PART S/N 61995-0.						1	L	7	2 	4F				A22CE 					 
1996010500396	19960105	00396	CE 	1996	1	5	96ZZZX38 	1	19951130	G	7810	NH100089750	COUPLING 	AIRESRCH 		BEECH 	58 	58P 	1152744	CE 										TURBO EXHAUST	FAILED 	D		A		O				OTHER 				D	Y		INFLIGHT SEPARATION 	ENGINE STOPPAGE 		NR	NOT REPORTED 	1			CE	03	6036S	2064 				TJ26				CLAMP FAILED IN-FLIGHT AND ALLOWED THE OVERBOARD EXHAUST STACK THAT ATTACHES TO OUTLET SIDE OF THE TURBOCHARGER TO DEPAR	T THE AIRCRAFT, UNRESTRICTED EXHAUST FLOW THEN MELTED 'P' LEADS CONDUCTOR SHORTING TO OUTER SHIELDING CAUSING ENGINE SHU	T DOWN WITHOUT PILOT INPUT. HAD 'P' LEADS NOT SHORTED, THE EXHAUST DAMAGE COULD HAVE BEEN MORE SEVERE OR CATASTROPHIC.				1	L	7	2 	3O				A23CE 					 
1996012600457	19960126	00457	CE 	1996	1	26	96ZZZX381 	1	19951201	G	3242	133593	BRAKE ROTOR 	BFGOODRICH 	21502 	CESSNA	650 	650 	2076802	CE 										MLG NR 4 BRAKE	CRACKED 	B			XB1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	09	84WU	795 			0816	650008				FOUND ALL 3 ROTORS ON NR 4 BRAKE CRACKED FROM THE HOLES, OUTWARD. TWO OF THE ROTORS WERE BROKEN IN TWO.						2	L	7	2 	4F				A9NM 					 
1996012600458	19960126	00458	SO 	1996	1	26	96ZZZX382 	2	19951015	G	8530		GUIDE 								CONT 	O300 	O300A 	17022	SO 					EXHAUST VALVE	WORN 	D	L	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15										INSTALLED 6 NEW SUPERIOR MILLENIUM CYLINDERS. THREE CYLINDERS LOST COMPRESSION WITHIN 24 HOURS. PULLED ALL 6 CYLINDERS	. ALL 6 EXHAUST GUIDES WORN BEYOND SERVICE LIMITS. THESE WERE THEIR 'POWER PACKS'. PRE-ASSEMBLED WITH NEW VALVES, SPR	INGS, PISTONS, ETC.									3	O			E253				 
1996012600459	19960126	00459	SO 	1996	1	26	96ZZZX383 	2	19951015	G	8530	643767	GUIDE 								CONT 	O520 	TSIO520H 	17040	SO 					VALVES	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15			120 							INSTALLED 6 CERMICHROME CYLINDER REBUILT UNITS WITH 643767 GUIDES. 120 SMOA. COMPRESSION LEAK ON TWO CYLINDERS. PULLE	D ALL 6 AND RETURNED UNITS TO ECI. THEY DIAGNOSED AS JUST WORN OUT. THEY REPAIRED SAME AND SUGGESTED FULL FLOW LIFTERS	 AND DRILLED ROCKERS TO 'HELP ALLEVIATE FUTURE PROBLEMS'.									3	O			E8CE				 
1996012600460	19960126	00460	SO 	1996	1	26	96ZZZX384 	2	19951015	G	8530		GUIDE 								CONT 	O200 	O200A 	17020	SO 					EXHAUST VALVE	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15			300 							ONE YEAR AGO INSTALLED 4 NEW TCM POWER PACKS. DROPPED COMPRESSION ON ONE EXHAUST VALVE AFTER 300 HOURS. WORN GUIDE WAS	 AT FAULT.										3	O			E252				 
1996012600461	19960126	00461	SO 	1996	1	26	96ZZZX385 	2	19951015	G	8530		GUIDE 								CONT 	O470 	IO470K 	17026	SO 					VALVE	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15			110 							INSTALLED 6 RECONDITIONED CHROME UNITS BY DIVCO. AFTER 110 HOURS, LOST COMPRESSION IN TWO CYLINDER GUIDES WORN BEYOND L	IMITS.										3	O			3E1				 
1996012600462	19960126	00462	SO 	1996	1	26	96ZZZX386 	2	19951015	G	8530		GUIDE 								CONT 	C85 	C85* 	17008	SO 					VALVE	WORN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15			24 							INSTALLED 4 NEW TCM POWER PACKS. AFTER 24 HOURS, LOST COMPRESSION ON TWO CYLINDERS. VALVE GUIDES OUT OF LIMITS.											3	O			E233				 
1996020200052	19960202	00052	SW 	1996	2	2	96ZZZX387 	1	19951211	G	5210	2353	HANDLE 			BELL 	412 	412 	1182202	SW 										DOOR	DEFECTIVE 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	2FOR					36013				HANDLE WILL NOT LOCK.						1	G	7	2 	4U				H4SW 					 
1996020200053	19960202	00053	CE 	1996	2	2	96ZZZX388 	1	19951117	G	2820	99162088	CONTROL CABLE 			CESSNA	414 	414A 	2075907	CE 										CROSS FEED LT	BROKEN 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	414BW	3000 				414A0049				WHEN CHECKING CROSS FEED, CABLE BROKE, LEAVING FUEL SELECTION VALVE IN CROSS FEED POSITION. INSTALLED NEW CABLE.						1	L	7	2 	3O			 	A7CE 					 
1996010500397	19960105	00397	SO 	1996	1	5	96ZZZX39 	1	19951118	G	7160		AIR BOX 			MAULE 	MX7 	MX7180 	5460185	SO 										CARBURETOR	FAILED 	D		A		O				OTHER 				Y			ENGINE STOPPAGE 			TO	TAKEOFF 	1			GL	23	758AZ	780 				11007C				SMALL PART OF AIR BOX BROKE LOOSE FROM BOX, LODGING IN CARBURETOR THROAT CAUSING ENGINE TO QUIT ON TAKEOFF. SUCCESSFUL 	LANDING WAS MADE BACK ON RUNWAY. AIR BOX MADE OF ALUMINUM. A NEW AIR BOX FROM MAULE AIR WAS INSTALLED.					1	H	7	1 	3O			NC	3A23 					 
1996020200055	19960202	00055	EA 	1996	2	2	96ZZZX390 	2	19951229	G	7414	4347	MAGNETO TAB 	SLICK 		MOONEY	M20 	M20E 	5870212	SW 	LYC 	O360 	IO360A1A 	41514	EA 					COIL	BENT 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	11		6 			95050011					OPENED MAGNETO TO TROUBLESHOOT TIMING PROBLEM. FOUND COIL TAB BENT AT DOWNWARD ANGLE SUFFICIENT TO CAUSE STEEL BARREL O	F CARBON BRUSH HOLDER TO BE ROTATING ON COIL TAB, DAMAGING IT SUBSTANTIALLY. THE SLICK MANUAL CALLS FOR FLUSH TO .0312 	INCH FROM THE PARTING SURFACE. UPON LEVELING THE COIL TAB, IT WAS FLUSH WITH THE SPACERS USED ON THE 4347 (M3826) AND N	OT THE PARTING SURFACE. THIS PROBLEM WAS UNRELATED TO THE TIMING PROBLEM.			1	L	7	1 	3O	3	O		2A3 	1E10				 
1996020200056	19960202	00056	CE 	1996	2	2	96ZZZX391 	1	19951208	G	3231	55421021	TORQUE TUBE 			CESSNA	501 	501 	2076603	CE 										NLG DOOR	BROKEN 	B		A	DEBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	102HS	4016 				5010130				FOUND NOSE GEAR DOOR HANGING OPEN. THE GEAR DOOR TORQUE TUBE WAS BROKEN AT THE ATTACH POINT. FLIGHT WITH THIS CONDITIO	N COULD CAUSE THE NOSE GEAR TO JAM IN THE UP POSITION. SUBMITTER RECOMMENDED FIT BY CESSNA WAS TO C/W SB 560-32-07. TH	IS BULLETIN DOES NOT APPLY TO THE 501, BUT WILL FIX THIS PROBLEM.				1	L	7	2 	4F				A27CE 					 
1996020200057	19960202	00057	SW 	1996	2	2	96ZZZX392 	1	19951202	G	5542	553300013	SKIN 			CESSNA	500 	560CESSNA 	2076750	CE 										RUDDER L/E	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	561B	1767 				5600008				CRACK IN RUDDER L/E WRAP-ROUND SKIN. CRACK CAME FROM RIVET HEAD, UP AND FORWARD, (HOOK SHAPE) APPROXIMATELY 6 INCHES LO	NG. SUSPECT SHARP EDGE ON STRINGER L/E, LT SIDE OF RUDDER, OR UNDERLAPPING SHARP EDGE OF SKIN.					2	L	7	2 	4F			RT	A22CE 					 
1996020200058	19960202	00058	CE 	1996	2	2	96ZZZX393 	1	19951226	G	2910	240600514	HOSE ASSY 			LEAR 	25 	25B 	5170511	CE 										RT ENG NACELLE	RUPTURED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	99	251JA	2122 				150				HYDRAULIC HOSE BURST WHILE OPERATING UNDER PRESSURE. CAUSE BELIEVED TO BE NORMAL WEAR. HOSE HAS A 2,400-HOUR OR 5-YEAR	 LIFE AND HAD USED MOST OF ITS SERVICEABLE LIFE.					2	L	7	2 	4J				A10CE 					 
1996020200059	19960202	00059	CE 	1996	2	2	96ZZZX394 	1	19950309	G	6120	1013690231	SWITCH 		122FW12 	BEECH 	B300 	B300 	1159232	CE 										PROP PROXIMITY	FAILED 	D				O				OTHER 				N			FALSE WARNING 			CL	CLIMB 	1			NM	01	4S	45 			1872	FL107				ON DEPARTURE, LEFT PROPELLER LOW PITCH LIGHT WILL NOT GO OUT. TROUBLESHOOTING BY SWAPPING SWITCHES LEFT TO RIGHT IDENTI	FIED DEFECTIVE SWITCH. REPLACED SWITCH, CORRECTED THE PROBLEM.					2	L	7	2 	4T			RT	A24CE 					 
1996020200060	19960202	00060	CE 	1996	2	2	96ZZZX395 	1	19951219	G	6120	1013690231	SWITCH 		122FW12 	BEECH 	B300 	B300 	1159232	CE 										PROP PROXIMITY	FAILED 	D				K				NONE 				P			NO WARNING INDICATION 			IN	INSP/MAINT 	1			NM	01	4S	368 			2419	FL107				ON PRE-FLIGHT DEPARTURE RUN-UP AND OPERATIONAL CHECK, DISCOVERED LEFT PROPELLER PITCH LIGHT INOPERATIVE. REPLACED PROXI	MITY SWITCH, CORRECTED THE DEFECT. SUBMITTER STATED THIS IS THE THIRD LOW PITCH STOP PROXIMITY SWITCH FAILURE IN 413 HO	URS, AIRFRAME TIME SINCE NEW. SUBMITTER SUSPECTS DEFECTIVE SWITCH, OR SWITCH WILL NOT TOLERATE THE ENVIRONMENT.				2	L	7	2 	4T			RT	A24CE 					 
1996020200061	19960202	00061	CE 	1996	2	2	96ZZZX396 	1	19951219	G	6120	1013690231	SWITCH 		122FW12 	BEECH 	B300 	B300 	1159232	CE 										PROP PROXIMITY	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4S	358 			1881	FL107				RIGHT LOW PITCH ANNUNCIATOR INOPERATIVE. SYSTEM OPERATIVE, LIGHT BULB OK. REPLACED RT SWITCH ASSY, AND CORRECTED PROBL	EM. SUBMITTER STATED THESE SWITCHES ARE NOT VERY DEPENDABLE, MAYBE SWITCH DESIGN NOT COMPATIBLE WITH ENVIRONMENT WHERE 	INSTALLED, TEMPERATURE HOT/COLD, VIBRATION, WET/DRY, ETC.				2	L	7	2 	4T			RT	A24CE 					 
1996020200063	19960202	00063	CE 	1996	2	2	96ZZZX398 	1	19951202	G	3010	S120120	SEAL 			CESSNA	500 	S550 	2076607	CE 										BLKHEAD FITTING	DEFECTIVE 	B			CWQR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	05	288QS	6614 				S5500088				DURING INSPECTION, FOUND TKS ANTI-ICE FLUID LEAKING FROM RIGHT SIDE OF NOSE WHEELWELL. TRACED LEAK TO AFT SIDE OF FORWA	RD PRESSURE BULKHEAD. FOUND O-RINGS ON FORWARD PRESSURE BULKHEAD FITTINGS DEFECTIVE AND PUDDLE OF TKS FLUID IN FLOOR BO	ARDS. REPLACED O-RINGS. SUBMITTER STATED TKS FORWARD O-RINGS DO NOT HOLD UP WELL AND FITTINGS LOCATION IS RARELY LOOKE	D AT. BETTER O-RINGS NEEDED AND TKS FITTINGS NEED TO BE LOOKED AT CLOSELY.			1	L	7	2 	4F			RT	A22CE 					 
1996010500282	19960105	00282	EA 	1996	1	5	96ZZZX4 	2	19950714	G	7250	3035228	NOZZLE 			BEECH 	1900 	1900C 	1154161	CE 	PWA 	PT6 	PT6A65B 	52043	EA 					GAS GENERATOR	BURNED VANE 	B		A	MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	160AM		449 		1197	UC160	32544			LEFT ENGINE ITT ROSE ABOVE LIMITS MOMENTARILY. WHEN THE ENGINE WAS SEPARATED FROM THE POWER SECTION, DISCOVERED THE CT 	VANE RING HAD A SECTION COMPLETELY BURNED THROUGH. THE INVESTIGATION IS LOOKING AT THE FUEL NOZZLES AS A POSSIBLE CAUSE	. THE FUEL NOZZLES ARE CHANGED OUT AT 480.0 HOURS				2	L	7	2 	4T	4	T	RT	A24CE 	E4EA				 
1996010500398	19960105	00398	SO 	1996	1	5	96ZZZX40 	1	19951118	G	2842	3910C	SENDING UNIT 			MAULE 	M5 	M5180C 	5460204	SO 										FUEL QTY	FLOAT FAILED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	1900Z	1300 				8024C				RIGHT SIDE FUEL SENDER WOULD NOT REGISTER. WITH MIRROR IN FUEL TANK, COULD SEE FLOAT HAD COME OFF FLOAT ARM, WEARING FL	OAT ALMOST IN TWO. FLOAT MADE OF BLACK COMPOSITE LIKE MATERIAL (2ND OCCURRENCE).					1	H	7	1 	3O				3A23 					 
1996082900182	19960829	00182	SO 	1996	8	29	96ZZZX4079 	1	19950430	G	3211	2082900	STUD 			PIPER 	PA24 	PA24250 	7102404	SO 										MLG SIDE BRACE	CRACKED 	B			CTKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	5837P					24918				MAIN LANDING GEAR SIDE BRACE STUD LEFT SIDE, CRACK AT RADIUS OF HEAD. PART TIME UNKNOWN. AD 95-20-7 N/R.						1	L	7	1 	3O				1A15 					 
1996010500399	19960105	00399	CE 	1996	1	5	96ZZZX41 	1	19951130	G	5551	12326231	BRACKET 			CESSNA	210 	T210N 	2073456	CE 										HORIZONTAL STAB	CRACKED 	B		A	WTXR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	7568N	1956 				21063235				UPON INSPECTION OF RIGGING OF THE RUDDER AND ELEVATOR CONTOL SURFACES FOR A MODIFICATION OF AIRCRAFT, FOUND LEFT HORIZON	TAL STABILIZER ATTACH BRACKET CRACKED AT THE BOTTOM OUTBOARD SIDE OF BRACKET. INSTALLED NEW BRACKETS, P/N 1232624-1 IAW	 SE 84-17, REV. 1.				1	H	7	1 	3O				3A21 					 
1996010500400	19960105	00400	EU 	1996	1	5	96ZZZX42 	1	19951106	G	3010		DEICE BOOT 			SOCATA	TBM 	TBM700 	8682000	EU 										WING TAIL	MANUAL ERROR 	B		A	MZER	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	15	300AE	404 				97				DEICE BOOTS CYCLE OUTBOARD WING THEN INBOARD WING AND TAIL. THE MM AND POH SAY THE INBOARD WING AND TAIL SHOULD CYCLE F	IRST, THEN OUTBOARD WING. AFTER TALKING TO TBM NORTH AMERICAN SERVICE REP, FOUND THE BOOKS WERE WRONG. REFERENCE: MM, 	CHAPTER 30, SUB-CHAPTER 20, ITEM 2B.				1	L	7	1 	3T			RT	A60EU 					 
1996090500146	19960905	00146	SO 	1996	9	5	96ZZZX4238 	1	19951115	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	3582X				57761	318052105				DURIGN INSPECTION PER LYCOMING SB 518C, CRIMP NUT FOUND LOOSE ON SHAFT. NOTE THAT SERIAL NUMBER OF THIS UNIT IS BEYOND 	RANGE OF SERVICE BULLETIN AND THEORETICALLY, HAS BEEN REDESIGNED TO ELIMINATE THIS PROBLEM.					1	L	7	2 	3O				A20SO 					 
1996010500401	19960105	00401	CE 	1996	1	5	96ZZZX43 	1	19951114	G	3230	504501032	TORQUE TUBE 			CESSNA	340 	340CESSNA 	2076404	CE 										RT MLG	CRACKED 	D		A		O				OTHER 				P			NO WARNING INDICATION 			AP	APPROACH 	1			EA	05	24EC	2100 				3400009				PILOT REPORTED NO RT GEAR DOWN LIGHT. TRIED TO GET GEAR TO GO DOWN, BUT COULD NOT. LANDED AND RT GEAR SLOWLY RETRACTED	 CAUSING FLAPS, TIP TANK, AND AILERON, RT ENG, AND PROP DAMAGE. FOUND RT MLG TORQUE TUBE CRACKED ADJACENT TO WELDED SUP	PORT FOR BELLCRANK. INITIAL CRACK APPEARED TO BE OLD, ALLOWING DOWNLOCK MECHANISM NOT TO ENGAGE PROPERLY BECAUSE OF TOR	QUE TUBE FLEX IN CRACKED AREA. SUBMITTER SUGGESTS CLOSE INSPECTION OF ALL TORQUE TUBES AND BEEFED UP TORQUE TUBE BE INS	TALLED.		1	L	7	2 	3O				3A25 					 
1996020200065	19960202	00065	SO 	1996	2	2	96ZZZX431 	1	19951210	G	5610	11595CB31024	WINDSHIELD 		91175H3671 	GULSTM	G1159 	GIV 	3980115	SO 										RT COCKPIT	CRACKED 	A			XMRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	21	768J	1914 				1119				RIGHT WINDSHIELD CRACKED DUE TO ARCING DURING FLIGHT. WINDSHIELD REMAINED INTACT, AND UNEVENTFUL LANDING OCCURRED. REP	LACED WINDSHIELD.					2	L	7	2 	4F			RT	A12EA 					 
1996090500699	19960905	00699	SO 	1996	9	5	96ZZZX4311 	2	19951118	G	8530	639323	INTAKE TUBE 			CESSNA	404 	404CESSNA 	2075901	CE 	CONT 	O520 	GTSIO520M 	17032	SO 					FLANGE	CRACKED 	B			BJFR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	23	5409G		946 			4040028	276457R			FUEL STAINS WERE NOTED AROUND SEVERAL INTAKE TUBES. IN REMOVING THE COLLARS FROM THE CYLINDERS TO GAIN ACCESS TO THE IN	JECTORS, TWO OF THE INTAKE TUBES WERE FOUND CRACKED AROUND THE RADIUS OF THE FLANGE.					1	L	7	2 	3O	3	O		A25CE 	E7CE				 
1996020200068	19960202	00068	EU 	1996	2	2	96ZZZX434 	1	19951213	G	5530	11730641	END PLATE 			BOLKMS	117 	BK117A1 	5626010	EU 										VERTICAL FIN	DAMAGED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117LF	126 			S049	7013				REPAIR KNOCK-OUT PLUG IN VERTICAL FIN.						1	G	7	2 	3U				H13EU 					 
1996091200078	19960912	00078	SO 	1996	9	12	96ZZZX4346 	1	19951115	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	27594				57348	317852070				DURING INSPECTION PER LYCOMING SB 518C, NUT FOUND LOOSE ON SHAFT. NOTE THAT SERIAL NUMBER OF THIS UNIT IS BEYOND RANGE 	OF SB AND, THEORETICALLY, HAS BEEN REDESIGNED TO ELIMINATE THIS PROBLEM.					1	L	7	2 	3O				A20SO 					 
1996091200079	19960912	00079	SO 	1996	9	12	96ZZZX4347 	1	19951115	G	7922	53E19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	27594				55033	317852070				DURING INSPECTION PER LYCOMING SB 518C, NUT FOUND LOOSE ON SHAFT. NOTE THAT SERIAL NUMBER OF THIS UNIT IS BEYOND RANGE 	OF SB AND, THEORETICALLY, HAS BEEN REDESIGNED TO ELIMINATE THIS PROBLEM.					1	L	7	2 	3O				A20SO 					 
1996020200069	19960202	00069	EU 	1996	2	2	96ZZZX435 	1	19951213	G	6410	134615P	BUSHING 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117M	5055 				S7023				WORN BUSHING AND WORN FIBER SEAL. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1996020200070	19960202	00070		1996	2	2	96ZZZX436 	4	19951212	G	3444	066106103	ALTIMETER 			BOLKMS	117 	BK117A3 	5626015	EU 										RADAR ALTIMETER	FAILED 	B			TI1R	K				NONE 				W	L		INADEQUATE Q C 	NO TEST 		IN	INSP/MAINT 	1			SW	05	1140H				12992	7078				WILL NOT TEST, NEEDLE GOES PAST 2,500 FEET AND STAYS THERE. ZERO HOURS SINCE LAST REPAIR. RETURN FOR WARRANTY REPAIR.						1	G	7	2 	3U				H13EU 					 
1996020200071	19960202	00071	EU 	1996	2	2	96ZZZX437 	1	19951205	G	3310	1179203103	CONTROL UNIT 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	1140H	13 			0106	7078				COCKPIT LIGHT FLASHES WHEN TURNED ON THEN GOES OUT (INTERMITTENT).						1	G	7	2 	3U				H13EU 					 
1996020200072	19960202	00072		1996	2	2	96ZZZX438 	4	19951208	G	2211	117884141	COMPUTER 			BOLKMS	117 	BK117B1 	5626012	EU 										YAW CSAS	DEFECTIVE 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	117VU				018609001	7211				AIRCRAFT CONSTANTLY YAWS RIGHT AND LEFT WHEN YAW CSAS SYSTEM IS ENGAGED. PART BAD FROM STOCK.						1	G	7	2 	3U				H13EU 					 
1996091200545	19960912	00545	SO 	1996	9	12	96ZZZX4388 	1	19951115	G	7922	53ED19600	VALVE 			PIPER 	PA31 	PA31350 	7103110	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	B			APCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	627HA				60857	317952241				DURING INSPECTION PER LYCOMING SB 518C, NUT FOUND LOOSE ON SHAFT. NOTE THAT SERIAL NUMBER OF THIS UNIT IS BEYOND RANGE 	OF SERVICE BULLETIN AND THEORETICALLY HAS BEEN REDESIGNED TO ELIMINATE THIS PROBLEM.					1	L	7	2 	3O				A20SO 					 
1996020200073	19960202	00073		1996	2	2	96ZZZX439 	4	19951226	G	2350	AA34200	INTERFACE 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	INOPERATIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	206MH				4965	45426				AUDIO INTERFACE INOPERATIVE.						1	G	7	1 	3U				H2SW 					 
1996010500402	19960105	00402	SO 	1996	1	5	96ZZZX44 	1	19951025	G	5320	9689700	GUSSET 			PIPER 	PA34 	PA34200T 	7103406	SO 										SEAT BELT ATTACH	CORRODED 	H	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4079Q					347770237				DURING INSPECTION OF REAR SPAR CARRY-THROUGH ATTACH FITTINGS PER PIPER SB 977, IT WAS NOTED THE FITTING SCREWED TO IT WA	S CORRODED TO THE POINT OF UNAIRWORTHINESS. THIS PART IS NOT INCLUDED AS PART OF THE INSPECTION PER THE SB. BOTH LT AN	D RT SIDE FITTINGS WERE CORRODED.				1	L	7	2 	3O				A7SO 					 
1996020200074	19960202	00074	EU 	1996	2	2	96ZZZX440 	1	19951208	G	6720	11788659	BELLCRANK 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	214AE	75 			197	7206				TEFLON COATING WORN BEYOND LIMITS IN T/R BELLCRANK. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1996020200075	19960202	00075	EU 	1996	2	2	96ZZZX441 	1	19951202	G	5412	1176625501	FIREWALL 			BOLKMS	BK117 	BK117C1 	5626025	EU 										ENGINE AFT	CRACKED 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	974 				7505				CRACKED FIREWALL ASSY. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1996091200573	19960912	00573	SO 	1996	9	12	96ZZZX4416 	1	19950610	G	5741	9010443	SHOULDER BOLT 			GULSTM	AA5 	AA5B 	3960105	SO 										WING ATTACH	SHEARED 	H		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	08	28800					AA5B0821				PART OF HANGAR FELL ON TAIL ASSEMBLY RENDERING PLANE UNFLYABLE. WHEN REMOVED WINGS FOR TRANSPORTATION TO REPAIR SHOP, A	 RIGHT WING SHOULDER ATTACH BOLT WAS SHEARED (DID NOT HAPPEN WHEN THE TAIL WAS DAMAGED). ONLY TWO HOURS SINCE ANNUAL. A	D IN EFFECT, 94-CE-15-AD.				1	L	7	1 	3O				A16EA 					 
1996020200076	19960202	00076	EU 	1996	2	2	96ZZZX442 	1	19951111	G	5210	1172428402	STOP 			BOLKMS	BK117 	BK117C1 	5626025	EU 										RIGHT DOOR	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	913 				7505				RIGHT STOP WORN. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1996020200077	19960202	00077	EU 	1996	2	2	96ZZZX443 	1	19951111	G	5210	1172428401	STOP 			BOLKMS	BK117 	BK117C1 	5626025	EU 										RIGHT DOOR	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	913 				7505				RIGHT STOP WORN. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1996020200078	19960202	00078	EU 	1996	2	2	96ZZZX444 	1	19951111	G	6720	11788659	BELLCRANK 			BOLKMS	BK117 	BK117C1 	5626025	EU 										T/R	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	913 				7505				TEFLON COATED BEARING WORN ON T/R BELLCRANK. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1996020200079	19960202	00079	EU 	1996	2	2	96ZZZX445 	1	19951111	G	5210	1172428111	CATCHER 			BOLKMS	BK117 	BK117C1 	5626025	EU 										LEFT DOOR	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	913 				7505				LEFT CATCHER WORN. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1996020200080	19960202	00080	EU 	1996	2	2	96ZZZX446 	1	19951111	G	5210	1172428211	CATCHER 			BOLKMS	BK117 	BK117C1 	5626025	EU 										LEFT DOOR	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	913 				7505				LEFT DOOR CATCHER WORN. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1996020200081	19960202	00081	EU 	1996	2	2	96ZZZX448 	1	19951111	G	5210	1172427301	GUIDE ASSY 			BOLKMS	BK117 	BK117C1 	5626025	EU 										DOOR	WORN 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	913 				7505				DOOR GUIDE ASSEMBLY WORN. REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU 					 
1996020200082	19960202	00082		1996	2	2	96ZZZX449 	4	19951206	G	3425	066304601	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	B			TI1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4572R				6779	S663				COMPASS CARD TURNS WITH HEADING BUG.						1	G	7	2 	3U				H3EU 					 
1996010500403	19960105	00403	EA 	1996	1	5	96ZZZX45 	2	19951207	G	8520		CRANKSHAFT 			UNIVAR	108 	1083 	9230408	NM 	FRNKLN	6A4165	6A4165B3 	27025	EA 					STARTER GEAR	BROKE 	D	P			K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	99	6817M	2515 	648 			1084817	32543			CRANKSHAFT BROKE AT KEYWAY WHERE STARTER GEAR MOUNTS ON SHAFT.						1	H	7	1 	3O	3	O		A767 	E238				 
1996020200083	19960202	00083	NE 	1996	2	2	96ZZZX450 	2	19951206	G	7310	1742510	FILTER 			BELL 	222 	222U 	1182140	SW 	LYC 	LTS101	LTS101750C1 	41560	NE 					ENGINE	METAL CONTAM 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	6992					47521	LE47020			FILTER WAS INSTALLED IN FILTER BOWL WHEN ADDING OIL (OHI MECHANIC SAW METAL INSIDE).						1	G	7	2 	3U	3	U		H9SW 	E5NE				 
1996091200756	19960912	00756		1996	9	12	96ZZZX4500 	1	19951103	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200757	19960912	00757		1996	9	12	96ZZZX4501 	1	19951108	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200758	19960912	00758		1996	9	12	96ZZZX4502 	1	19951114	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200759	19960912	00759		1996	9	12	96ZZZX4503 	1	19951117	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR.																			 
1996091200760	19960912	00760		1996	9	12	96ZZZX4504 	1	19951128	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200761	19960912	00761		1996	9	12	96ZZZX4505 	1	19951130	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200762	19960912	00762		1996	9	12	96ZZZX4506 	1	19951208	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	CRACKED 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR.																			 
1996091200763	19960912	00763		1996	9	12	96ZZZX4507 	1	19951227	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200764	19960912	00764		1996	9	12	96ZZZX4508 	1	19951010	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	SHORTED 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200765	19960912	00765		1996	9	12	96ZZZX4509 	1	19951102	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996020200084	19960202	00084	SW 	1996	2	2	96ZZZX451 	1	19951201	G	7714	206062627003	TACH GENERATOR 			BELL 	206 	206L1 	1182107	SW 										ENGINE	INOPERATIVE 	B			TI1R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	721SP				11710	45486				INSTALLED TACHOMETER GENERATOR AS SERVICEABLE, BUT DID NOT WORK. RETURN FOR REPAIR.						1	G	7	1 	3U				H2SW 					 
1996091200766	19960912	00766		1996	9	12	96ZZZX4510 	1	19951110	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INTERMITTENT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200767	19960912	00767		1996	9	12	96ZZZX4511 	1	19951121	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	SMOKING 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200768	19960912	00768		1996	9	12	96ZZZX4512 	1	19951204	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200769	19960912	00769		1996	9	12	96ZZZX4513 	1	19951214	G	3320	BR63031201	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	DEFECTIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP.																			 
1996091200770	19960912	00770		1996	9	12	96ZZZX4514 	1	19951214	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200771	19960912	00771		1996	9	12	96ZZZX4515 	1	19951214	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	DEFECTIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP.																			 
1996091200772	19960912	00772		1996	9	12	96ZZZX4516 	1	19951221	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200784	19960912	00784		1996	9	12	96ZZZX4528 	1	19950714	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200785	19960912	00785		1996	9	12	96ZZZX4529 	1	19950907	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200786	19960912	00786		1996	9	12	96ZZZX4530 	1	19950901	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	ARCING 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200787	19960912	00787		1996	9	12	96ZZZX4531 	1	19950702	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200788	19960912	00788		1996	9	12	96ZZZX4532 	1	19950719	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200789	19960912	00789		1996	9	12	96ZZZX4533 	1	19950907	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200790	19960912	00790		1996	9	12	96ZZZX4534 	1	19950922	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	DEFECTIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200791	19960912	00791		1996	9	12	96ZZZX4535 	1	19950919	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200792	19960912	00792		1996	9	12	96ZZZX4536 	1	19950821	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200793	19960912	00793		1996	9	12	96ZZZX4537 	1	19950816	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	DEFECTIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200794	19960912	00794		1996	9	12	96ZZZX4538 	1	19950816	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	WORN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200795	19960912	00795		1996	9	12	96ZZZX4539 	1	19950810	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200796	19960912	00796		1996	9	12	96ZZZX4540 	1	19950808	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200797	19960912	00797		1996	9	12	96ZZZX4541 	1	19950728	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200820	19960912	00820		1996	9	12	96ZZZX4564 	1	19950112	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200821	19960912	00821		1996	9	12	96ZZZX4565 	1	19950208	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200822	19960912	00822		1996	9	12	96ZZZX4566 	1	19950302	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091200823	19960912	00823		1996	9	12	96ZZZX4567 	1	19950313	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: ASA.																			 
1996091200824	19960912	00824		1996	9	12	96ZZZX4568 	1	19950313	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR.																			 
1996091200825	19960912	00825		1996	9	12	96ZZZX4569 	1	19950327	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR.																			 
1996091200826	19960912	00826		1996	9	12	96ZZZX4570 	1	19950201	G	3320	BR630302	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200827	19960912	00827		1996	9	12	96ZZZX4571 	1	19950214	G	3320	BR6303102	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200828	19960912	00828		1996	9	12	96ZZZX4572 	1	19950302	G	3320	BR6303102	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200829	19960912	00829		1996	9	12	96ZZZX4573 	1	19950113	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	DEFECTIVE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200830	19960912	00830		1996	9	12	96ZZZX4574 	1	19950214	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200831	19960912	00831		1996	9	12	96ZZZX4575 	1	19950306	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	ARCING 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200832	19960912	00832		1996	9	12	96ZZZX4576 	1	19950306	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200833	19960912	00833		1996	9	12	96ZZZX4577 	1	19950302	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	SHORTED 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200834	19960912	00834		1996	9	12	96ZZZX4578 	1	19950315	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	LOOSE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200835	19960912	00835		1996	9	12	96ZZZX4579 	1	19950331	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200836	19960912	00836		1996	9	12	96ZZZX4580 	1	19950331	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200837	19960912	00837		1996	9	12	96ZZZX4581 	1	19950323	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	MELTED 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091200838	19960912	00838		1996	9	12	96ZZZX4582 	1	19950216	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	CHAFED WIRE 	B			ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900212	19960919	00212		1996	9	19	96ZZZX4583 	1	19950407	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR.																			 
1996091900213	19960919	00213		1996	9	19	96ZZZX4584 	1	19950419	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR.																			 
1996091900214	19960919	00214		1996	9	19	96ZZZX4585 	1	19950517	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	MELTED 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091900215	19960919	00215		1996	9	19	96ZZZX4586 	1	19950516	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR.																			 
1996091900216	19960919	00216		1996	9	19	96ZZZX4587 	1	19950619	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091900217	19960919	00217		1996	9	19	96ZZZX4588 	1	19950410	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST.																			 
1996091900218	19960919	00218		1996	9	19	96ZZZX4589 	1	19950410	G	3320	BC10047005	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR.																			 
1996091900219	19960919	00219		1996	9	19	96ZZZX4590 	1	19950428	G	3320	BR6303102	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900220	19960919	00220		1996	9	19	96ZZZX4591 	1	19950504	G	3320	BR6303102	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900221	19960919	00221		1996	9	19	96ZZZX4592 	1	19950405	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900222	19960919	00222		1996	9	19	96ZZZX4593 	1	19950419	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	DEFECTIVE 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900223	19960919	00223		1996	9	19	96ZZZX4594 	1	19950418	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900224	19960919	00224		1996	9	19	96ZZZX4595 	1	19950418	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	CRACKED 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900225	19960919	00225		1996	9	19	96ZZZX4596 	1	19950512	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INTERMITTENT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900226	19960919	00226		1996	9	19	96ZZZX4597 	1	19950516	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900227	19960919	00227		1996	9	19	96ZZZX4598 	1	19950519	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BROKEN 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900228	19960919	00228		1996	9	19	96ZZZX4599 	1	19950525	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP.																			 
1996010500404	19960105	00404	CE 	1996	1	5	96ZZZX46 	1	19951216	G	3211	071349561	BRACKET 			CESSNA	170 	170B 	2072306	CE 										LT MLG	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	4600C					25544				UPON INSPECTION OF LANDING GEAR, LT SIDE DUE TO HARD LANDING, FOUND BRACKET CRACKED AND CORRODED BEYOND TREATMENT OR REP	AIR. DUE TO CORROSION, RT SIDE WAS ALSO CORRODED BEYOND TREATMENT OR REPAIR. REPLACED BOTH LT AND RT SIDES. SUBMITTER	 RECOMMENDS INSTALLING DRAIN HOLES TO PREVENT BULKHEAD FROM HOLDING MOISTURE AND FREQUENT INSPECTION.				1	H	7	1 	3O				A799 					 
1996091900229	19960919	00229		1996	9	19	96ZZZX4600 	1	19950525	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP.																			 
1996091900230	19960919	00230		1996	9	19	96ZZZX4601 	1	19950609	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900231	19960919	00231		1996	9	19	96ZZZX4602 	1	19950609	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900232	19960919	00232		1996	9	19	96ZZZX4603 	1	19950615	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900233	19960919	00233		1996	9	19	96ZZZX4604 	1	19950630	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	INOPERATIVE 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996091900234	19960919	00234		1996	9	19	96ZZZX4605 	1	19950525	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP.																			 
1996091900235	19960919	00235		1996	9	19	96ZZZX4606 	1	19950421	G	3320	BR63031021	LAMP HOLDER 	BRUCE 																CABIN LIGHTS	BURNT 	B	L		ZZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT.																			 
1996020200274	19960202	00274	SO 	1996	2	2	96ZZZX461 	1	19951226	G	5740	6862102	FITTING 			PIPER 	PA32 	PA32RT300T 	7103216	SO 										LT WING ATTACH	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	39602	2170 				32R7887117				DURING ANNUAL INSPECTION, FOUND LEFT REAR WING ATTACH FITTING CORRODED AND WATER STANDING IN FUSELAGE. REMOVED FITTING 	AND CLEANED CORROSION. LOWER .5 INCH WAS CORRODED APPROXIMATELY 20 PERCENT OF THICKNESS OF PART. REPLACED WITH NEW FIT	TING IAW PIPER SB 977. SUBMITTER RECOMMENDS THIS SB BECOME AN AD DUE TO FREQUENCY OF PIPER AIRCRAFT WITH THIS PROBLEM.				1	L	7	1 	3O				A3SO 					 
1996020200276	19960202	00276		1996	2	2	96ZZZX463 	1	19951227	G	2434	ALU8421LS	ALTERNATOR 	ELECTROSYS 							LYC 	O540 	TIO540J2BD 	41532	EA 					DRIVE SHAFT	PULLEY BACKWARDS	B			APCR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	01					5112140					ALTERNATOR PULLEY INSTALLED BACKWARDS ON SHAFT. THIS WAS A NEWLY OVERHAULED UNIT RECEIVED FROM OVERHAULER.											3	O			E14EA				 
1996020200277	19960202	00277	SO 	1996	2	2	96ZZZX464 	1	19951130	G	5313	7746002	LONGERON 			PIPER 	PA38 	PA38112 	7103812	SO 										PILOT STEP SIDE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	2503V	5110 				3882A0069				LONGERON LOCATED IN THE FUSELAGE, BOTTOM LEFT, CRACKS AROUND THE NUTPLATES DUE TO STRESS FROM THE STEP. PREVENTION MAY 	BE A DOUBLER SLID UNDER THE CHANNEL RIVETED TO THE SKIN. THIS WILL PREVENT THE FLEX AROUND THE NUTPLATES WHERE CRACKS O	CCUR.				1	L	7	1 	3O				A18SO 					 
1996020200278	19960202	00278	CE 	1996	2	2	96ZZZX465 	1	19951211	G	8010	S1577A1	CONTACTOR 			CESSNA	150 	152 	2071835	CE 										STARTER	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	66955					15281690				PILOT STARTED ENGINE FOR TAKEOFF. STARTER CONTACTOR WELDED IN THE 'ON' POSITION. WHEN PILOT RELEASED KEY, STARTER CONT	INUED TO RUN UNTIL BURNED UP. PILOT WAS NOT AWARE OF CONDITION. SUBMITTER STATED THIS IS A FAIRLY COMMON OCCURRENCE WI	TH 24V STARTERS ON CESSNAS WITH LYCOMING ENGINES. IT ALWAYS DESTROYS THE STARTER, AND SOMETIMES THE ALTERNATOR AND BATT	ERY. SUGGEST FUNCTION LIGHT BE INSTALLED IN CIRCUIT.			1	H	7	1 	3O			NT	3A19 					 
1996091900583	19960919	00583	SO 	1996	9	19	96ZZZX4695 	1	19950522	G	5751	4A251095	HINGE 			EMB 	110 	EMB110P1 	3260122	SO 										LT AILERON	CRACKED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	710NH					110250				DURING ROUTINE 150-HOUR INSPECTION, FOUND LEFT AILERON CENTER HINGE CRACKED AT PIVOT BOLTS. CRACKED FROM ONE SIDE THROU	GH THE OTHER.					1	L	7	2 	4T				A21SO 					 
1996010500405	19960105	00405	CE 	1996	1	5	96ZZZX47 	1	19951216	G	3211	071349562	BRACKET 			CESSNA	170 	170B 	2072306	CE 										RT MLG	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	4600C					25544				UPON INSPECTION OF LANDING GEAR, LT SIDE DUE TO HARD LANDING, FOUND BRACKET CRACKED AND CORRODED BEYOND TREATMENT OR REP	AIR. DUE TO CORROSION, RT SIDE WAS ALSO CORRODED BEYOND TREATMENT OR REPAIR. REPLACED BOTH LT AND RT SIDES. SUBMITTER	 RECOMMENDS INSTALLING DRAIN HOLES TO PREVENT BULKHEAD FROM HOLDING MOISTURE AND FREQUENT INSPECTION.				1	H	7	1 	3O				A799 					 
1996020200283	19960202	00283	SO 	1996	2	2	96ZZZX470 	1	19951203	G	2437	834095	AMMETER 	STWARNER 		PIPER 	PA32 	PA32300 	7103212	SO 										ALT AMPS	SHORTED 	D				A				UNSCHED LANDING 				B			SMOKE/FUMES/ODORS/SPARKS 			CL	CLIMB 	1			AL	05	8991N	4935 				3240874				FLT 702 - SHORTLY AFTER TAKEOFF FROM THE AIRPORT, THE AMMETER SHORTED CAUSING SMOKE TO FILL THE COCKPIT. THE PIC WAS AB	LE TO RETURN TO AIRPORT SAFELY.					1	L	7	1 	3O				A3SO 					 
1996020200284	19960202	00284	CE 	1996	2	2	96ZZZX471 	1	19951201	G	3232	R3582519117	ACTUATOR 			BEECH 	33 	F33A 	1151425	CE 										NLG DOOR	MISINSTALLED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	07	853KS					CE1765				DURING 100-HOUR ANNUAL INSPECTION, DAMAGE TO NOSE GEAR FORK ASSY AND LEFT NOSE GEAR DOOR ACTUATOR ROD DISCOVERED. FURTH	ER EXAMINATION REVEALED IMPROPER WASHER PLACEMENT WHERE THE UPPER BALL JOINT OF THE DOOR ACTUATOR ROD IS FASTENED TO THE	 NOSE GEAR DOOR ACTUATOR SHAFT ASSY. BEECHCRAFT ILLUSTRATED PARTS CATALOG DOES NOT LIST WASHER PLACEMENT. THIS AIRCRAF	T IS A 1993 MODEL WITH 105 HOURS TOTAL TIME. SUBMITTER STATED CONTINUED OPERATION WOULD HAVE CAUSED NOSE GEAR DOOR ACTU	ATOR ROD FAILURE AND POSSIBLE INTERFERENCE WITH NOSE GEAR OPERATION.		1	L	7	1 	3O				3A15 					 
1996091900609	19960919	00609	EA 	1996	9	19	96ZZZX4722 	2	19950509	G	8520	LW11750	CONNECT ROD 			PIPER 	PA23 	PA23250 	7102308	SO 	LYC 	O540 	IO540J4A5 	41532	EA 					CYLINDER NR 5	BROKEN 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			NM	03	6730Y	4744 	706 			274062	L647648			ROD BROKE AT CRANKSHAFT END OF ROD WHERE IT WIDENS FOR CRANKSHAFT. ROD SHOWS SIGNS OF FATIGUE. CYLINDER NR 5, ROD.						1	L	7	2 	3O	3	O		1A10 	1E4				 
1996091900611	19960919	00611	EU 	1996	9	19	96ZZZX4724 	1	19950207	G	2810	T67620001	TANK 			SLNSBY	T67 	T67M260 	8323006	EU 										RT WING	LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	17	3004H	402 				2126				DURING POST-FLIGHT INSPECTION, THE SEAL ON BELLY OF AIRCAFT BETWEEN AIRFRAME AND WING ON RT SIDE WAS BLUE IN COLOR. AFT	ER FURTHER INSPECTION AND SEAL REMOVED, FUEL WAS SEEPING FROM WING TANK. A PRESSURE TEST WAS PERFORMED AND A LEAK WAS N	OTED ON THE CORNER OF THE FUEL TANK. CAUSE WAS DETERMINED TO BE NOT ENOUGH SEALANT ON INTERIOR OF TANK.				1	L	7	1 	3O			NT	A73EU 					 
1996020200286	19960202	00286	CE 	1996	2	2	96ZZZX473 	1	19951205	G	2410	1100723	ALTERNATOR 			CESSNA	402 	402CESSNA 	207590K	CE 										DRIVE GEAR	BEARING FAILED 	D				A				UNSCHED LANDING 				J			WARNING INDICATION 			CL	CLIMB 	1			SW	07	4046Q		600 			4020146				SHORTLY AFTER TAKEOFF, THE RT ENGINE STARTED LOSING OIL PRESSURE. THE PILOT RETURNED TO THE DEPARTING AIRPORT. INSPECT	ION OF THE OIL FILTER REVEALED A LARGE QUANTITY OF METAL. ON ENGINE TEAR DOWN, THE ALTERNATOR DRIVE GEAR WAS FOUND BROK	EN. THE ALTERNATOR FRONT BEARING WAS DESTROYED. SUBMITTER SUGGESTED 500-HOUR SERVICE LIFE ON BEARING, 250-HOUR INSPECT	IONS.			1	L	7	2 	3O				A7CE 					 
1996091900619	19960919	00619	CE 	1996	9	19	96ZZZX4732 	1	19950115	G	8011	6462382	STARTER 			CESSNA	185 	A185F 	2072821	CE 										BRUSH	WIRE BROKEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	05	6JV	451 				18502397				SUBMITTER STATED THIS IS ABOUT THE 4TH STARTER THAT HAS FAILED IN THE LAST 2 YEARS OUT OF 3 AIRCRAFT. THE STARTER BRUSH	 WIRE ALWAYS BREAKS OFF NEXT TO WHERE IT IS WELDED. SUBMITTER RECOMMENDS DIFFERENT METHOD OF ATTACHING STARTER BRUSH WI	RES (SCREW MAYBE). SUSPECT WIRE HARDENS NEXT TO WELD AND INSTEAD OF FLEXING, IT WORKS BACK AND FORTH UNTIL IT BREAKS.				1	H	7	1 	3O				3A24 					 
1996091900926	19960919	00926	CE 	1996	9	19	96ZZZX4741 	1	19950117	G	3210	224110213	PIVOT 			CESSNA	182 	R182 	2072734	CE 										MLG	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	517MS	775 				R18200681				AIRCRAFT REPORTED COMPLETE LOSS OF RT BRAKE. DETERMINED PIVOT CRACKED PER SEB 90-1, REV 2. THIS WAS NEW STYLE PIVOT. W	HILE FITTING NEW PIVOT, DETERMINED LOAD OF AIRCRAFT WAS BEING CARRIED BY BUSHING 2241120-1 BECAUSE OF CLOSER FIT. THE M	AIN SUPPORT BUSHINGS WERE NOT WORN, BUT CLEARANCE GREATER THAN ENDS. END BUSHINGS ON BOTH PIVOTS REPLACED AFTER OUTSIDE	 DIAMETER CHANGED TO .989 INCH AND INSURED AIRCRAFT LOAD ON MAIN SUPPORTS.			1	H	7	1 	3O			RT	3A13 					 
1996091900928	19960919	00928	EA 	1996	9	19	96ZZZX4743 	2	19950328	G	8530	LW12988	CYLINDER 			PIPER 	PA46 	PA46350P 		SO 	LYC 	O540 	TIO540AE2A 	41532	EA 					NR 6 CYL HEAD	SEPARATED 	B			LF1R	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	TO	TAKEOFF 	1			EA	07	126SR	746 				4622036	L899261A			OPERATOR COMPLAINED OF ROUGHNESS ON TAKEOFF. AIRCRAFT RETURNED TO HANGAR WITH OIL LEAKING FROM COWLING. REMOVED TOP CO	WLING AND FOUND NR 6 CYLINDER SEPARATED 1 INCH TO 2 INCHES BELOW HEAD. COULD FIND NO EVIDENCE OF PRIOR DAMAGE. (NOTE: 	 CYLINDER WAS REPAIRED 454.0 HOURS PREVIOUSLY FOR OIL CONSUMPTION.) SUSPECT CAUSE COULD BE FATIGUE OR HIDDEN DEFECT. R	EPLACED CYLINDER AND PISTON ASSY.			1	L	7	1 	3O	3	O	RT	A25SO 	E14EA				 
1996091900929	19960919	00929		1996	9	19	96ZZZX4744 	4	19950302	G	3434	8857K44	SELECTOR 			BEECH 	58 	58P 	1152744	CE 										MLG SWITCH	JAMMED 	B			FC6R	O				OTHER 				O			OTHER 			AP	APPROACH 	1			NM	11	163Z					TJ247				LANDING GEAR SELECTOR (SWITCH) FROZE IN THE UP POSITION. LANDING GEAR CIRCUIT BREAKER PULLED AND GEAR WAS HAND CRANKED 	TO DOWN WITH NO FAULT.					1	L	7	2 	3O				A23CE 					 
1996091900931	19960919	00931	CE 	1996	9	19	96ZZZX4746 	1	19950307	G	5522	966100055	SKIN 			BEECH 	95 	95B55 	1152729	CE 										RT/LT ELEVATOR	CRACKED 	B		A	DEBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	18388	2900 				TC2081				DURING ANNUAL ISNEPCTION, FOUND ELEVATOR SKIN BOTH LEFT AND RIGHT CRACKED AND CORRODED. REPLACED SKINS WITH NEW, PAINTE	D AND BALANCED. SUBMITTER SUGGESTS CLOSER ATTENTION DURING ANNUAL INSPECTION. BELIEVE THIS OCCURRED LONG BEFORE THIS I	NSPECTION. OLDER ACFT WITH MAGNESIUM SKINS ARE CANDIDATES FOR CORROSION.				1	L	7	2 	3O			RT	3A16 					 
1996091900933	19960919	00933	CE 	1996	9	19	96ZZZX4748 	1	19950404	G	8011	539800	CLUTCH SPRING 		642087A 	BEECH 	58 	58P 	1152744	CE 										STARTER ADAPTER	DISLOCATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	13	1858G		264 		B3678	TJ383				DURING TROUBLESHOOTING, RIGHT ENGINE NOT TURNING OVER WHEN STARTER SWITCH ENGAGED. FOUND WHEN STARTER SWITCH ENGAGED, S	TARTER MOTOR WOULD RUN, BUT ENGINE WOULD NOT TURN OVER. REMOVED STARTER ADAPTER AND FOUND CLUTCH SPRING HAD WORKED OUT 	OF ITS HOUSING AND RUBBING STARTER SHAFT GEAR ASSY. APPEARS THIS HAS BEEN GOING ON FOR SOME TIME. GEAR ON STARTER SHAF	T GEAR ASSY HAS BEEN HOT. DISCOLORED THE GEAR. STARTER ADAPTER HAD BEEN OVERHAULED BY AN FAA CERTIFIED REPAIR STATION.			1	L	7	2 	3O				A23CE 					 
1996091900934	19960919	00934		1996	9	19	96ZZZX4749 	4	19950310	G	6113		SPINNER 			CESSNA	172 	172N 	2072434	CE 						SNSNCH	76E	76EM8 	EA 	BULKHEAD	MISFIT 	D	S			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	11	1928F	2930 				17273019		28715K		FOUND ABOVE NORMAL TENSION ON REAR SPINNER BULKHEAD WHEN INSTALLING SPINNER, THIS NEW PROPELLER MAY BE THICKER THAN ORIG	INAL PROPELLER WHICH USES THE ORIGINAL SPINNER AND BACKPLATES FROM THE 160HP ENGINE. 350 HOURS SINCE STC MOD NR SA 4428	SW.				1	H	7	1 	3O			NT	3A12 		5	N	P4EA	 
1996091900939	19960919	00939	CE 	1996	9	19	96ZZZX4754 	1	19950921	G	3213	51411022	STRUT ASSY 		51411012 	CESSNA	414 	414A 	2075907	CE 										RT MLG	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	36961	2741 				414A0494				AFTER A ROUTINE FLIGHT AND LANDING, FOUND RT MLG WAS FULLY EXTENDED ON THE GROUND. DISASSEMBLY FOUND THE LOWER STRUT AS	SY, UPPER BEARING RETAINER HAD COME LOOSE FROM ITS RETAINER GROOVE CAUSING STRUT TO EXTEND FARTHER THAN NORMAL CAUSING S	TRUT TO STICK IN FULL EXTENSION. REPLACEMENT OF LOWER STRUT ASSEMBLY AND UPPER BEARING AND RETAINER, AND RESEALING OF S	TRUT WERE REQUIRED TO REPAIR DEFECT. THIS IS NOT A NORMAL INSPECTION ITEM AND CAN EASILY BE PASSED OVER AND NOT SEEN DU	RING PRE-FLIGHT OR ANNUAL INSPECTION. FAILURE WAS INTERNAL TO STRUT.		1	L	7	2 	3O				A7CE 					 
1996020200289	19960202	00289		1996	2	2	96ZZZX476 	1	19951218	G	2434	6503LS	BEARING 	PRESTOLITE 	ALV9510 															ALT DRIVE END	FAILED 	B			NV2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07			600 		11000007					DRIVE END BEARING ON ALTERNATOR FAILED DUE TO MAIN RING GEAR FAILURE ON ENGINE.																			 
1996020200291	19960202	00291	EA 	1996	2	2	96ZZZX478 	2	19951130	G	8530	7380685	PUSH ROD 			PIPER 	PA38 	PA38112 	7103812	SO 	LYC 	O235 	O235L2C 	41505	EA 					NR 4 CYL INTAKE	DAMAGED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	9171A		590 			3882A0119	L1533115			THE PUSH ROD METAL INSERT ON THE VALVE END BECAME LOOSE. THIS ALLOWED THE INSERT TO POUND AGAINST THE METAL TUBE, CURLI	NG THE METAL OVER, UNDER THE INSERT TO THE OUTSIDE.					1	L	7	1 	3O	3	O		A18SO 	E223				 
1996092600121	19960926	00121		1996	9	26	96ZZZX4784 	4	19950301	G	3452	RT359A	TRANSPONDER 	ARC 		CESSNA	172 	R172K 	2072431	CE 										POWER SUPPLY	BURNED 	D				A				UNSCHED LANDING 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			EA	07	758LC				12362	R1723172				PILOT LANDED AIRCRAFT AFTER DETECTING BURNING SMELL. AFTER INVESTIGATING PROBLEM, TRANSPONDER WAS REPLACED BY RADIO SHO	P (POWER SUPPLY IN TRANSPONDER HAD BURNED CAUSING SMELL).					1	H	7	1 	3O				3A17 					 
1996092600123	19960926	00123	SO 	1996	9	26	96ZZZX4786 	2	19950313	G	8520	303821	CRANKCASE 			PIPER 	PA34 	PA34200T 	7103406	SO 	CONT 	O360 	TSIO360E 	17025	SO 					NR 3 BEARING	CRACKED 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	321GS					347770419	303821			DURING TROUBLESHOOTING TO DETERMINE ORIGIN OF AN OIL LEAK, FOUND CASE CRACKED ON BOTH VALVES AT NR 3 BEARING WEB. UPON 	TEAR DOWN, CASE HALVES WERE REJECTED DUE TO FAILING HARDNESS TEST. CRACKS WERE IN AREA OF A PREVIOUS REPAIR. CAUSE OF 	FAILURE UNKNOWN.				1	L	7	2 	3O	3	O		A7SO 	E9CE				 
1996092600125	19960926	00125	CE 	1996	9	26	96ZZZX4788 	1	19950328	G	7810	175400115	MUFFLER 			CESSNA	172 	172M 	2072418	CE 										ENGINE EXHAUST	DEFORMED 	B		A	LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	8882V					17264241				DURING ANNUAL INSPECTION, FOUND END OF MUFFLER CRACKED AND BODY OF MUFFLER BULGED UNDER HEAT SHIELD. THE DEFORMATION HA	D BEEN PRESENT FOR SOME TIME. PROBLEM MAY HAVE OCCURRED DUE TO EXCESSIVE LEANING OF MIXTURE. (NOTE: EGT INDICATOR WAS	 INOP ON INSPECTION RUN-UP.) THE HEAT SHIELD MUST BE REMOVED FOR INSPECTION AT EVERY ANNUAL. FAILURE WOULD CAUSE CARBO	N MONOXIDE POISONING AND HEAT DAMAGE TO ENGINE.			1	H	7	1 	3O			NT	3A12 					 
1996020200292	19960202	00292	SO 	1996	2	2	96ZZZX479 	1	19951201	G	7922	53E19980	VALVE 			PIPER 	PA31 	PA31P 	7103120	SO 										THERMO BYPASS	LOOSE CRIMP NUT 	B	L		YYKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	500MC				159	31P21				INSPECTION OF OIL TEMPERATURE BYPASS VALVE REVEALED LOOSE NUT. REF: LYC SB 518C, 5-2-95. THIS SB LISTS P/N 53E19980, 	S/N 159, AND HIGHER AS N/A. SUBMITTER SUGGESTS SB BE REVISED TO INCLUDE ALL PART NUMBERED AND SERIAL NUMBERED VALVES UN	TIL LATEST STYLE PART NUMBER IS INSTALLED. VALVE SENT TO LYC FACTORY FOR INSPECTION PER PART NUMBER AND SERIAL NUMBER.				1	L	7	2 	3O				A8EA 					 
1996092600131	19960926	00131	SO 	1996	9	26	96ZZZX4794 	1	19950313	G	2140	90D381	HEATER 	JANITROL 		PIPER 	PA34 	PA34200T 	7103406	SO 										BURNER CAN	FAILED CHECK 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	9670K		1376 			34760214				DURING 100-HOUR INSPECTION, HEATER FAILED DK CHECK. DURING FURTHER INSPECTION, FOUND 1 INCH CRACK IN END OF BURNER CAN.	 ALSO, HEATER APPEARED TO HAVE BEEN OVERTEMPED JUST PRIOR TO THIS INSPECTION.					1	L	7	2 	3O				A7SO 					 
1996010500406	19960105	00406	EA 	1996	1	5	96ZZZX48 	2	19951204	G	7322	46F10	VENTURI 	FACET 	MA4SPA 	CESSNA	172 	172K 	2072430	CE 	LYC 	O320 	O320E2C 	41508	EA 					CARBURETOR	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	7362G	100 				17259062				C/W AD 93-18-03 BY REMOVING TWO-PIECE VENTURI AND INSTALLING CONSOLIDATED FUEL SYSTEM'S ONE-PIECE VENTURI. THEREAFTER, 	PILOT REPORTED CRUISE FLIGHT FUEL BURN INCREASED FROM 7 GPH TO 9 GPH. INSPECTION OF CARBURETOR AND VENTURI DISCLOSED NO	 DISCREPANCIES, BUT AS A PRECAUTION, A NEW 46-F10 ONE-PIECE VENTURI WAS INSTALLED AND FUEL CONSUMPTION HAS SINCE RETURNE	D TO NORMAL.			1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1996020200293	19960202	00293	SO 	1996	2	2	96ZZZX480 	1	19951130	G	5313	7746002	LONGERON 			PIPER 	PA38 	PA38112 	7103812	SO 										PILOT STEP SLIDE	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	01	232OV	5377 				3882A0040				LONGERON LOCATED IN THE FUSELAGE, BOTTOM LEFT, CRACKS AROUND THE NUTPLATES DUE TO STRESS FROM THE STEP. SUBMITTER SUGGE	STS PREVENTION MAY BE A DOUBLER SLID UNDER THE CHANNEL RIVETED TO THE SKIN. THIS WILL PREVENT THE FLEX AROUND THE NUTPL	ATES WHERE CRACKS OCCUR.				1	L	7	1 	3O				A18SO 					 
1996020200294	19960202	00294	SO 	1996	2	2	96ZZZX481 	2	19951019	G	8530		ROCKER 			CESSNA	150 	150 	2071802	CE 	CONT 	O200 	O200A 	17020	SO 					NR 2 CYLINDER	BOSS FAILED 	G	P			A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			NM	01	3481J					15066181	00304			PILOT OWNER DEPARTED HOME AIRPORT FOR ROUTINE SCENIC FLIGHT. AFTER ABOUT 20 MINUTES INTO CROSS-COUNTRY FLIGHT, ENGINE S	TARTED RUNNING ROUGH, CARBURETOR HEAT HAD NO EFFECT. RETURN HOME WITH PARTIAL POWER. INSPECTION OF NR 2 CYLINDER ROCKE	R REVEALED ALL FOUR BOSSES BROKEN OFF REQUIRING REPLACEMENT OF CYLINDER. SUBMITTER SUGGESTS FATIGUE MOST LIKELY CAUSE O	F FAILURE. TOTAL TIME ON CYLINDER-ENGINE, 2,100 HOURS SMOH. RECOMMEND DYE PENETRANT CHECK EVERY 500 HOURS.			1	H	7	1 	3O	3	O	NT	3A19 	E252				 
1996092600215	19960926	00215	EU 	1996	9	26	96ZZZX4837 	1	19951005	G	2916	1054543001	BRACKET 			BOLKMS	105 	BO105S 	5626006	EU 										NR 1 HYD RESVR	CRACKED 	B			JSNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	204PC	439 				S895				DURING RETROFIT OF HYDRUALIC MODULE FRAME, LEFT OR FORWARD WALL, BRACKET WAS FOUND CRACKED. CRACKS WERE NOT DETECTABLE 	UNTIL BRACKET WAS COMPLETELY REMOVED. CRACKS APPEARED TO BE STARTING FROM CENTER EDGE OF RIVETED NUTPLATES. SUBMITTER 	STATED THIS BRACKET GENERIC TO ALL 105 HELICOPTERS, HAD SAME BRACKET CRACK ON CBS4 VARIANT, BUT AT A MUCH HIGHER TIME, 2	,200 HRS. EUROCOPTER IS SUPPOSED TO COME OUT WITH OPTIONAL BULLETIN TO ADDRESS CRACKING ON FORWARD WALL OF HYDRAULIC MO	DULE.		1	G	7	2 	3U				H3EU 					 
1996020200300	19960202	00300	WP 	1996	2	2	96ZZZX487 	2	19951207	G	7250	31038391	SEAL 								GARRTT	TPE331	TPE33112UAR 	01514	WP 					1ST STAGE TURB	CRACKED 	B		A	DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		10508			9233151457		P70018			DURING SCHEDULED HOT SECTION INSPECTION, FOUND SEAL CRACKED AT SEALING FLANGE. THIS IS A CRITICAL LIFE LIMITED COMPONEN	T. LIFE LIMIT IS 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE/CORRECT CAUSE OF CRACKING. NUM	EROUS MALFUNCTION/DEFECT REPORTS SUBMITTED ON THIS TOPIC BY THIS REPAIR STATION ALONE. CYCLES SINCE NEW, 10,865.									4	T			E4WE				 
1996020200301	19960202	00301	SO 	1996	2	2	96ZZZX488 	1	19951208	G	3246	13836	BEARING CUP 			PIPER 	PA28 	PA28181 	7102807	SO 										WHEELS	CORRODED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	05	3344Q	1533 				287790452				OWNER COMPLAINED OF A 'CLUNKING' NOISE COMING FROM ONE WHEEL AS THE PLANE WAS PULLED OUT FROM A HANGAR. INSPECTION SHOW	ED ALL THREE WHEELS TO HAVE CORRODED WHEEL BEARINGS. BEARINGS WERE REPLACED. THE AIRCRAFT RECEIVED AN ANNUAL INSPECTIO	N ON 11-17-94 AT 1,491 HOURS. THREE MONTHS LATER, 1,509 HOURS, THE AIRCRAFT WAS STRIPPED AND PAINTED. FIVE MONTHS AFTE	R PAINTING AT 1,533 HOURS, THE CORRODED WHEEL BEARINGS WERE FOUND. IT SEEMS THAT DURING THE STRIPPING PROCESS, WATER EN	TERED THE WHEELS AND CAUSED THE CORROSION.		1	L	7	1 	3O				2A13 					 
1996010500407	19960105	00407	EA 	1996	1	5	96ZZZX49 	2	19951107	G	8530		VALVE 			GULSTM	AA5 	AA5A 	3960106	SO 	LYC 	O320 	O320E2G 	41508	EA 					ENG INTAKE	LEAKING 	D				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			NE	01	97520		57 			AA5A0152	L4647827A			AIRCRAFT WAS TAKING OFF, NOT GENERATING FULL POWER. NOTICED SLIGHT VIBRATION. RETURNED TO AIRPORT. VIBRATION INCREASE	D AS AIRCRAFT EXECUTED EMERGENCY LANDING AT AIRPORT. PERFORMED COMPRESSION CHECK, FOUND TO BE 20/80. REMOVED CYLINDER.					1	L	7	1 	3O	3	O		A16EA 	E274				 
1996020200303	19960202	00303	CE 	1996	2	2	96ZZZX490 	1	19951221	G	2720	51152603	TORQUE TUBE 			CESSNA	402 	402B 	207590P	CE 										LT RUDDER PEDAL	CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	53SA	13008				402B0591				DURING A PRE-FLIGHT INSPECTION, THE PILOT NOTED WHEN THE LT RUDDER PEDAL WAS PUSHED, NO CONTROL SURFACE MOVEMENT WAS NOT	ED. INVESTIGATION REVEALED CONTROL CABLE HAD PULLED ITS ATTACH EAR OFF OF THE TORQUE TUBE. THE INTERIOR GUST LOCK WAS 	INSTALLED FREEZING THE RUDDER PEDALS. NO EXTERNAL GUST LOCK WAS INSTALLED WHICH ALLOWED ALL THE WIND FORCE TO BE TRANSM	ITTED TO THE TORQUE TUBE. SUBMITTER SUGGESTS TO USE EXTERNAL GUST LOCKS.			1	L	7	2 	3O				A7CE 					 
1996020200304	19960202	00304	CE 	1996	2	2	96ZZZX491 	1	19951218	G	3260	MS3126F10P	PLUG ASSY 	AIRIGHT 	11238002223 	BEECH 	1900 	1900C 	1154161	CE 										NLG ACTUATOR	CORRODED 	C		A		K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			GL	13	521M	9100 			64	UB68				NOSE GEAR UNSAFE INDICATION. FOUND PLUG ASSY CORRODED. SUBJECT PLUG IS PART OF ELECTRICAL HARNESS AND IS LOCATED IN TH	E UPPER LEFT SIDE OF NOSE WHEELWELL. IT IS EXPOSED TO THE ELEMENTS AND A GOOD DEAL OF HARNESS MOTION. SUBMITTER RECOMM	ENDS CLOSER INSPECTION DURING DETAIL INSPECTIONS WHICH ALREADY CALL FOR A CHECK FOR CONDITION. IF CONDITION IS AT ALL S	USPECT, DISCONNECT, INSPECT, CLEAN, REASSEMBLE, AND SEAL.			2	L	7	2 	4T			RT	A24CE 					 
1996020200306	19960202	00306	EU 	1996	2	2	96ZZZX493 	1	19951006	G	3260		SWITCH 			ISRAEL	1124 	1124 	4500102	EU 										GEAR WARNING	MISWIRED 	B			EBVR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	09	420JM					193				DURING C-CHECK INSPECTION, FOUND LANDING GEAR WARNING HORN COULD BE CANCELLED WITH FLAPS AT 40 DEGREES. FOUND A GEAR WA	RNING HORN SILENCE SWITCH HAD BEEN MOUNTED IN THE THROTTLE WITH FAA FIELD APPROVAL, BUT WAS NOT WIRED AS SUBSEQUENT MODE	LS AND AS SHOWN IN SL WW 2428.				2	M	7	2 	4F				A2SW 					 
1996020200307	19960202	00307	EU 	1996	2	2	96ZZZX494 	1	19951215	G	5751	SL443110	BEARING 			BRAERO	DH125 	BAE125800A 	1500285	EU 										LT AIL INB HINGE	CRACKED 	B			EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	410BT	1571 				258209				THE LEFT AILERON, INBOARD HINGE BEARING, CENTER RACE WAS FOUND COMPLETELY CRACKED FROM SIDE TO SIDE IN ONE LOCATION. RE	PLACED WITH NEW UNIT.					2	L	7	2 	4F			RT	A3EU 					 
1996020200308	19960202	00308	NE 	1996	2	2	96ZZZX495 	2	19950806	G	7260	9699M27P01	COVER PLATE 			BOEING	747 	7472D3B 	1384805	NM 	GE 	CF6 	CF650E2 	30018	NE 					NR 2 GEARBOX	SEAL LEAK 	B		A	CISY	E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			K			FLUID LOSS 			CL	CLIMB 	1			EA	31	505MC					21251				LUX - AIRCRAFT DEPARTED, DURING CLIMB THE NR 2 ENGINE'S OIL QUANTITY DROPPED AND WAS SHUT DOWN. AIRCRAFT RETURNED TO LU	X AND LANDED SAFELY. OIL SERVICED AND ENGINE MOTORED - NO LEAK, IDLE CHECK - NO LEAK, POWER LEVEL ADVANCED AND LEAK APP	EARED AT THE GEARBOX MANUAL CRANK PAD. FOUND WASHER INSTALLED BEHIND CRANK PAD. WASHER REMOVED AND SEAL REPLACED, ENGI	NE RUN AND LEAK CHECK ACCOMPLISHED. AIRCRAFT RETURNED TO SERVICE. NOTE: THE GEARBOX MANUAL CRANK PAD WAS REMOVED FOR 	MAINTENANCE, SEAL REPLACED, NO LEAKS NOTED BY MOTORING. BOEING MM 72-00, PAGES 201-203, NO LEAK CHECK INDICATED, ESPECI	ALLY ADVANCED.	2	L	7	4 	4F	4	F	RT	A20WE 	E23EA				 
1996100300446	19961003	00446	SO 	1996	10	3	96ZZZX4957 	1	19950915	G	2731	4173448	CONTROL CABLE 		51436 	PIPER 	PA31T 	PA31T 	7103124	SO 										ELEVATOR TRIM	FRAYED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	700LT	4005 				31T7920046				DURING C/W PIPER SB 897A, AFTER REMOVAL OF RT ELEVATOR, INSPECTED THE TRIM CABLE AND FOUND SEVERAL BROKEN STRANDS IN THE	 AREA WHERE THE CABLE RUNS AROUND THE ELEVATOR TRIM/AP SERVO, WHICH HAS 2 SMALL 1.25 INCH PULLEYS THAT THE CABLE RUNS AR	OUND. AREA IS HARD TO INSPECT WHEN INSTALLED AND WITH TENSION ON CABLES. CHECKED PRIOR TO DISASSMEBLY, FOUND NO PROBLE	MS.			1	L	7	2 	3T			 	A8EA 					 
1996020200309	19960202	00309	CE 	1996	2	2	96ZZZX496 	1	19951030	G	3610	45A563024011	DUCT 			BEECH 	MU300 	400BEECH 		CE 										EXPANSION JOINT	BLOWN 	B			RJ3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	8167Y				0399	RK67				EXPANSION JOINT RETAINING MESH HAS 'LET GO' AT EACH END ALLOWING THE EXPANSION BELLOWS TO KINK OUT OF ALIGNMENT. BELLOW	S HAS RUPTURED. SUBMITTER STATED CAUSE UNKNOWN.					2	H	7	2 	4F			RT	A16SW 					 
1996020200510	19960202	00510		1996	2	2	96ZZZX499 	4	19951023	G	2210	117884141	COMPUTER 			BOLKMS	117 	BK117B1 	5626012	EU 										YAW CSAS	INOPERATIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	10UM				0489112	7231				COMPUTER UNIT INOPERATIVE ON INSTALL. WILL NOT COME ON-LINE. REPLACED WITH NEW UNIT. CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1996010500283	19960105	00283	NE 	1996	1	5	96ZZZX5 	2	19951020	G	7250	3023683	SEAL 		3037312 						PWA 	PT6 	PT6A67D 		NE 					DISK 1ST STAGE	FAILED 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01		6527 			58A981		114091			WHEN DTS RECEIVED THE POWER SECTION FROM MOUNTAIN WEST, IT WOULD NOT ROTATE FREELY. AT THE TIME OF DISASSEMBLY, SEVERAL	 PIECES OF NON-FUROUS METAL FELL OUT OF THE EXHAUST DUCT. IT WAS NOTED AFTER THE METAL FELL OUT, THE POWER SECTION ROTA	TED FREELY.									4	T			E26NE				 
1996010500408	19960105	00408	GL 	1996	1	5	96ZZZX50 	3	19951130	G	6111	FC84598R	BLADE 													HARTZL	HCC2Y	BHCC2YF2 	GL 	SEAL AREA	DEFECTIVE 	B			JT2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	15					D85695			AN4596		DURING OVERHAUL OF PROPELLER BLADE IAW HARTZELL MANUAL 133B, DISCOVERED SEAL AREA MEASURED UNDER DIMENSIONS. (EGG-SHAPE	D.) MINIMUM ALLOWED 4.344 INCHES. MEASURED 4.343 INCHES.															5	C	P920	 
1996020200511	19960202	00511	NE 	1996	2	2	96ZZZX500 	2	19951212	G	7321	0164448330	FUEL CONTROL 			SNIAS 	350 	AS350B 	8680801	EU 	TMECA 	ARRIEL	ARRIEL1B 	6OO30	NE 					ENGINE	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	151AC	1372 	1 		434B	1173	4019			FUEL CONTROL FAILED TO MEET FLIGHT MANUAL AND MM NR RPM GUIDE LINES. AT FLAT PITCH AND DURING FLIGHT, RPM WAS TOO HIGH.	 REPLACED WITH REPAIRED UNIT, CORRECTED PROBLEM.					1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1996020200512	19960202	00512	EU 	1996	2	2	96ZZZX501 	1	19951117	G	6510	105315221	DRIVE SHAFT 			BOLKMS	105 	BO105LSA3 	5626020	EU 										T/R	BENT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	203LF	1409 				2015				DRIVE SHAFT BENT BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U				H3AU 					 
1996101000113	19961010	00113		1996	10	10	96ZZZX5014 	4	19951028	G	3442	ART2100	ART SENSOR 	BENDIX 		BEECH 	200 	B200 	1152922	CE 										RADAR ANT STAB	MALFUNCTION 	B			FR2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	38V				P1009	BB1412				NEW RADAR UPGRADE. ANTENNA STABILIZATION TOO SENSITIVE. RADAR PAINTS HEAVY LEFT/RIGHT. AUTOTILT DROPS ANTENNA. BENDI	X/KING OFFERED NEW SOFTWARE LEVEL.					1	L	7	2 	4T				A24CE 					 
1996101000117	19961010	00117	SO 	1996	10	10	96ZZZX5018 	2	19950207	G	8530	SA626540C	VALVE 			CESSNA	180 	180 	2072602	CE 	CONT 	O470 	O470L 	17026	SO 					NR 4 CYL EXH	FAILED 	B	P		YECR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	09	3880C	550 				31028	68832864			DURING INVESTIGATION OF LOW CYLINDER COMPRESSION, NOTED THE TIP OF THE NR 4 CYLINDER EXHAUST VALVE WAS MUSHROOMED. ROCK	ER ARM IS DRILLED TYPE, PN 640944. WITH ROTOCOIL AND SPRINGS REMOVED, VALVE TIP COULD NOT BE WITHDRAWN FROM GUIDE. AFT	ER GRINDING TIP OF VALVE WAS BLASTED TO REVEAL FAA-PMA PN 'SA62650-C'. HARDNESS TESTS ON TIP OF VALVE WERE ABOUT 35 PER	CENT LESS THAN ON SIMILAR PN SA643873. VALVE WAS RETURNED TO MFG FOR TESTS. OTHER CYLINDERS ARE BEING CHECKED FOR ANY 	SIMILAR VALVE CONDITION.		1	H	7	1 	3O	3	O	NC	5A6 	E273				 
1996020200513	19960202	00513	NE 	1996	2	2	96ZZZX502 	2	19950719	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	417BK	637 				7143	LE45509EF			SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,31	2.8.					1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996101000124	19961010	00124	SO 	1996	10	10	96ZZZX5025 	2	19950327	G	7314	643950	COVER ASSY 			CESSNA	210 	T210N 	2073456	CE 	CONT 	O520 	TSIO520R 	17040	SO 					ENG FUEL PUMP	MISINSTALLED 	B	L		YECR	O				OTHER 				R	J	W	PARTIAL RPM/PWR LOSS 	WARNING INDICATION 	INADEQUATE Q C 	CR	CRUISE 	1			NM	09	6439N	2045 	150 			21063015	517034			SHORTLY AFTER REINSTALLATION OF ENGINE, PILOT REPORTED FUEL PRESSURE COULD NOT BE MAINTAINED AS ACFT GAINED ALTITUDE. F	UEL PRESSURE BEGAN TO DROP ABOVE 3,500 FEET MSL, AND BOOST PUMP NEEDED TO MAINTAIN ADEQUATE FUEL FLOWS AS ACFT CLIMBED A	BOVE 7,000 FEET MLS. AT 100 HOURS SMOH, FUEL PUMP REMOVED AND SENT TO SHOP WHICH OVERHAULED PUMP. BENCH TESTS REVEALED	 FUEL PUMP PRESSURE WAS A BIT HIGH, AND THIS WAS READJUSTED TO SPECIFIED BENCH. REINSTALLATION OF PUMP BROUGHT NO CHANG	E IN THE INITIAL SYMPTOMS. FUEL PUMP REMOVED SECOND TIME AT 150 HRS SMOH, AND SENT TO DIFFERENT SHOP OF INVESTIGATION. 	 THE P/N 643950 RELIEF VALVE COVER ASSY REVEALED THE COVER HAD BEEN INSTALLED 180 DEGREES FROM ITS PROPER POSITION.	1	H	7	1 	3O	3	O		3A21 	E8CE				 
1996020200514	19960202	00514	NE 	1996	2	2	96ZZZX503 	2	19950719	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	417BK	637 			666	7143	LE45509EF			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,312.8.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996101000182	19961010	00182	EA 	1996	10	10	96ZZZX5031 	2	19950207	G	8520	75011	CRANKSHAFT 			BBAVIA	8 	8KCAB 	2110612	CE 	LYC 	O320 	AEIO320E2B 	41508	EA 					FRONT MAIN	CORRODED 	B	P		YECR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	7698S	1153 				26276	L546055A			DURING OVERHAUL INSPECTION OF CRACKSHAFT, SOME CORROSION PITTING WAS NOTED ON OUTSIDE DIAMETER OF SEVERAL BEARING JOURNA	LS. INSPECTION OF FRONT MAIN INSIDE DIAMETER REVEALED AN AREA OF APROXIMATELY 20 CORROSION PITS. PITS WERE APPROXIMATE	LY .010 INCH DEEP AND WERE LOCATED APPROXIMATELY 1.50 INCHES TO 1.69 INCHES AFT OF FLANGE PILOT. THIS CRANKSHAFT, PN 75	011 ASSY, SN 107450, HAS ALWAYS OPERATED WITH A CONSTANT SPEED PROP AND IS NOT COVERED BY SB 505A. SUBMITTER STATED UND	ER CERTAIN CONDITIONS IF MOISTURE IS PRESENT IN ENGINE OIL, EVEN CONSTANT SPEED MODELS MAY DEVELOP IN INTERNAL CORROSION	. SB 505A INSPECTION SHOULD BE EXTENDED TO ALL CONSTANT SPEED CRANKS BEYOND A CERTAIN AGE OR HOURS.	1	H	7	1 	3O	3	O		A21CE 	1E12				 
1996020200515	19960202	00515	NE 	1996	2	2	96ZZZX504 	2	19950719	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	417BK	637 			05920370	7143	LE45509EF			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,312.8.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996020200516	19960202	00516	NE 	1996	2	2	96ZZZX505 	2	19950312	G	7230	430124202	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					COMPRESSOR NR 1	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	424MB	814 			2951	7082	LE45313			BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 7,314.4						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996020200517	19960202	00517	NE 	1996	2	2	96ZZZX506 	2	19950312	G	7250	430144801	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	424MB	814 			1190731	7082	LE45313			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 7,314.4.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996101000370	19961010	00370		1996	10	10	96ZZZX5062 	4	19951006	G	3442	ART2100	SENSOR 	BENDIX 	07101550101 	BEECH 	200 	B200 	1152922	CE 										RADAR ANT STAB	FAILED 	B			FR2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	128V				P1003	BB1442				NEW RADAR UPGRADE FROM RDR2000 TO RDR2100. FACTORY NEW ART-2100, SN P1003, FAILED. ANTENNNA STABILIZATION FAULT. AUTO	TILT DROPS ANTENNA.					1	L	7	2 	4T				A24CE 					 
1996101000374	19961010	00374	CE 	1996	10	10	96ZZZX5066 	1	19951201	G	3242	ART2100	SENSOR 	BENDIX 	07101550101 	BEECH 	200 	B200 	1152922	CE 										RADAR ANT STAB	DEFECTIVE 	B			FR2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	128V				P1003	BB1442				FACTORY SERVICED RADAR STILL NOT WORKING. PAINTS FALSE TARGETS. PAINTS HEAVY ON RIGHT SIDE. AUTOTILT DROPS ANTENNA. A	UTOTILT WAS DISABLED BY BENDIX/KING FIELD SERVICE ENGINEER. ALSO, AWAITING NEW SOFTWARE LEVEL.					1	L	7	2 	4T				A24CE 					 
1996020200518	19960202	00518	NE 	1996	2	2	96ZZZX507 	2	19950818	G	7250	430124202	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					TURBINE NR 3	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	420MB	313 			41472	7077	LE45244E			BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 8,721.5.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996020200519	19960202	00519	NE 	1996	2	2	96ZZZX508 	2	19950818	G	7230	430124202	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					COMPRESSOR NR 1	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	420MB	313 			41503	7077	LE45244E			BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 8,721.5.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996020200520	19960202	00520	NE 	1996	2	2	96ZZZX509 	2	19950818	G	7240	410106701	SEAL RING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	420MB	313 				7077	LE45244E			SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 8,72	1.5.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996010500409	19960105	00409	GL 	1996	1	5	96ZZZX51 	3	19951130	G	6111	FC84598R	BLADE 													HARTZL	HCC2Y	BHCC2YF2 	GL 	SEAL AREA	DEFECTIVE 	B			JR2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15					D85786			AN4596		DURING OVERHAUL OF PROPELLER BLADE IAW HARTZELL SEAL AREA MEASURED UNDER DIMENSIONS. (EGG-SHAPED.) MINIMUM ALLOWED, 4.	344 INCHES. MEASURED, 4.342 INCHES.															5	C	P920	 
1996020200521	19960202	00521		1996	2	2	96ZZZX510 	4	19951103	G	3422	109290	GYRO 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT	STUCK 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	420MB	166 			0126	7077				GYRO STUCK. READS 3.42 VOLTS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1996101000474	19961010	00474	SO 	1996	10	10	96ZZZX5117 	1	19950915	G	5521	54755002	BUTT RIB 			PIPER 	PA31T 	PA31T 	7103124	SO 										LT/RT ELEVATOR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	700LT	694 				31T7920046				C/W PIPER SB 897A PART I DATED12-88. IN JULY '89 AT 3,311 ACFT HOURS, LT AND RT ELEVATOR BUTT RIBS WERE CRACKED AT THAT	 TIME AND REPLACED PER SB AT 4,005 ACFT HOURS. FOUND BUTT RIBS CRACKED AGAIN. C/W SB 897A PART I AND II DATED 1-90. S	UBMITTER STATED HAS NOT SEEN OR HEARD OF A PA31T THAT HAS BEEN INSPECTED THAT DID NOT HAVE CRACKS IN ELEVATOR BUTT RIBS 	AND/OR IN THE SPAR OR FALSE SPARS. NEEDS TO BE AD NOTE TO ENSURE COMPLIANCE.			1	L	7	2 	3T				A8EA 					 
1996020200522	19960202	00522	CE 	1996	2	2	96ZZZX512 	1	19951002	G	7931	99103101	TRANSDUCER 			CESSNA	441 	441 	2076020	CE 										ENGINE OIL	DEFECTIVE 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	441RC	48 			28094	4410076				PRESSURE INDICATOR FLUCTUATES AT LOW POWER SETTINGS. NORMAL INDICATION IS RECEIVED AT HIGHER POWER SETTINGS. REPLACED 	WITH NEW UNIT, CORRECTED PROBLEM.					1	L	7	2 	3T			RT	A28CE 					 
1996020200523	19960202	00523		1996	2	2	96ZZZX513 	4	19950922	G	6113	C25317P	SPINNER 			MTSBSI	MU2 	MU2B60 	5780460	CE 										PROPELLER	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	454MA	607 			S943	1535SA				SPINNER CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	H	7	2 	3T			RT	A10SW 					 
1996101000857	19961010	00857	EA 	1996	10	10	96ZZZX5137 	2	19951028	G	7414	4271	MAGNETO 	SLICK 		AMTR 	VANS 	RV6 	05608 	GL 	LYC 	O320 	O320D1A 	41508	EA 					ENGINE RT	COIL FAILED 	H	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	679CM	235 				20102	L15727			ON MAY 4, 1995, DUE TO HARD START PROBLEM, THE LEFT MAG COIL WAS FOUND DEFECTIVE. ON OCTOBER 28, 1995, THE RIGHT MAG FA	ILED IN-FLIGHT DUE TO A DEFECTIVE COIL.					1	L	7	1 	3O	3	O	NC	EXPA1L71	E274				 
1996101000858	19961010	00858	EA 	1996	10	10	96ZZZX5138 	2	19951028	G	7414	4270	MAGNETO 	SLICK 		AMTR 	VANS 	RV6 	05608 	GL 	LYC 	O320 	O320D1A 	41508	EA 					ENGINE LT	COIL FAILED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	679CM	274 				20102	L15727			ON MAY 4, 1995, DUE TO HARD START PROBLEM, THE LEFT MAG COIL WAS FOUND DEFECTIVE. ON OCTOBER 28, 1995, THE RIGHT MAG FA	ILED IN-FLIGHT DUE TO A DEFECTIVE COIL.					1	L	7	1 	3O	3	O	NC	EXPA1L71	E274				 
1996020200524	19960202	00524		1996	2	2	96ZZZX514 	4	19950820	G	6113	C25317P	SPINNER 			MTSBSI	MU2 	MU2B60 	5780460	CE 										PROPELLER	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	479MA	300 			S30	1553SA				SPINNER CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	H	7	2 	3T			RT	A10SW 					 
1996020200525	19960202	00525	NE 	1996	2	2	96ZZZX515 	2	19950829	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	5188B	708 			0492446	7163	LE45757E			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 5,938.0.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996101000878	19961010	00878	WP 	1996	10	10	96ZZZX5158 	1	19950926	G	6300	369F55101	SHAFT 			HUGHES	369 	369E 	4470707	WP 										M/R DRIVE	DEFECTIVE 	G				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	911RP	17 			0000380024	526E				FACTORY RECALL AFTER 17.1 HOURS OF OPERATION FOR COMPLETE REPLACEMENT OF M/R DRIVESHAFT. RETIREMENT TOTAL TIME 5,020 HO	URS.					1	G	7	1 	3U				H3WE 					 
1996020200526	19960202	00526	NE 	1996	2	2	96ZZZX516 	2	19950829	G	7230	430135702	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	5188B	708 			338	7163	LE45757E			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 5,938.0.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996020200527	19960202	00527	NE 	1996	2	2	96ZZZX517 	2	19950613	G	7250	430144801	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	527SF	490 				7111	LE45273E			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 6,224.8.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996020200528	19960202	00528	NE 	1996	2	2	96ZZZX518 	2	19950613	G	7230	430135703	SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	527SF	490 			148	7111	LE45273E			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996020200529	19960202	00529	NE 	1996	2	2	96ZZZX519 	2	19950613	G	7240	410106701	SEAL RING 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	527SF	490 				7111	LE45273E			SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 6,22	4.8.					1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996101700511	19961017	00511	NE 	1996	10	17	96ZZZX5192 	2	19951202	G	7230	536210	TABLOCK 			SKRSKY	S64 	S64F 		NE 	PWA 	JFTD12	JFTD12A5A 	52047	NE 					3RD STAGE DISK	MISSING 	B	L		JYDR	K				NONE 				O			OTHER 			TO	TAKEOFF 	1			NM	09	178AC	914 				64097	677761			ENGINE FAILED INTERNALLY AT FIRST LIFT-OFF OF THE DAY. TABLOCK FOUND MISSING 12-2-95. THE LAST OVERHAUL PERFORMED BY E	AC ON 1-6-94. WHEN INSPECTING COMPRESSOR THROUGH INLET, CONTACT OF 3RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NE	AR CENTERLINE OF ENGINE (ROOT END OF BLADE). THE BLADE MOVED AFT CONTACTING FRONT OF STATOR DUE TO TABLOCK FAILURE. TH	IS IS 3RD OCCURRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1994. ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACTUR	ER.		2	G	7	2 	4U	4	U		H6EA 	E15EA				 
1996101700512	19961017	00512	NE 	1996	10	17	96ZZZX5193 	2	19950822	G	7230	536210	TABLOCK 			SKRSKY	S64 	S64F 		NE 	PWA 	JFTD12	JFTD12A5A 	52047	NE 					3RD STAGE DISK	MISSING 	B	L		JYDR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	178AC	1035 				64097	677775			ENGINE REMOVED FOR HSI. TABLOCK FOUND MISSING AT HIDDEN DAMAGE INSPECTION CONDUCTED ON COMPRESSOR BEING INDUCTED IN REP	AIR STATION ON 8-22-95. THE LAST OVERHAUL PERFORMED BY EAC ON 10-7-94. WHEN INSPECTING COMPRESSOR THROUGH INLET, CONTA	CT OF 3RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF ENGINE (ROOT END OF BLADE). THE BLADE MOVED 	AFT CONTACTING FRONT OF STATOR DUE TO TABLOCK FAILURE. THIS IS 2ND OCCURRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINC	E 1994. ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACTURER.		2	G	7	2 	4U	4	U		H6EA 	E15EA				 
1996010500410	19960105	00410	CE 	1996	1	5	96ZZZX52 	1	19951106	G	2750		FLAPS 			CESSNA	172 	172P 	2072436	CE 										RETRACT SYSTEM	DEFECTIVE 	H				O				OTHER 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			SO	17	54807					17275055				WHILE PRACTICING LANDINGS WITH STUDENT, THE FLAPS FAILED TO RETRACT. AFTER RECYCLING THE FLAP HANDLE SEVERAL TIMES, THE	 FLAPS FINALLY DID RETRACT. (SECOND OCCURRENCE IN 3 DAYS.) THE CAUSE APPEARS TO BE A BAD ELECTRICAL CONTACT, SINCE IT 	IS INTERMITTENT.				1	H	7	1 	3O			NT	3A12 					 
1996020200530	19960202	00530	EU 	1996	2	2	96ZZZX520 	1	19951017	G	7714	6899145	PICKUP ASSY 			SNIAS 	350 	AS350D1 	8680804	EU 										N2 RPM	INOPERATIVE 	B			DYRR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	11	57731				A031	1434				PICKUP ASSY UNIT INOPERATIVE UPON INSTALLATION. REPLACED WITH NEW UNIT FROM ALLISON, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1996020200531	19960202	00531	NE 	1996	2	2	96ZZZX521 	2	19950923	G	7230	430135703	SEAL 			BOLKMS	117 	BK117A4 	5626017	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	586BH	97 			741	7129	LE45344E			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 7,698.4.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1996101700863	19961017	00863	SO 	1996	10	17	96ZZZX5210 	2	19950608	G	8530		CYLINDER 			CESSNA	175 	175 	2072502	CE 	CONT 	O300 	GO300A 	17022	SO 					INTAKE RKR SHAFT	FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	08	7227M		1200 			55527				INTAKE SIDE ROCKER SHAFT BOSS BROKE. SHAFT BUSHINGS HAD BEEN INSTALLED.						1	H	7	1 	3O	3	O	NT	3A17 	E298				 
1996020200532	19960202	00532	EU 	1996	2	2	96ZZZX522 	1	19951213	G	7130	350A3801100801	FIREWALL 			SNIAS 	350 	AS350B2 	8680813	EU 										ENGINE	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	6099P	428 				2818				FIREWALL CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1996101700874	19961017	00874	EA 	1996	10	17	96ZZZX5221 	2	19950223	G	8530	LW19001	VALVE 			PIPER 	PA28 	PA28151 	7102805	SO 	LYC 	O320 	O320E3D 	41508	EA 					NR 4 CYL EXH	BROKEN 	B			A5OR	A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CR	CRUISE 	1			SO	09	43125	1632 				287415430	L3796827A			DURING FLIGHT, PILOT EXPERIENCED A LOSS OF POWER AND SEVERE VIBRATION FROM ENGINE. PILOT MADE AN EMERGENCY LANDING WITH	OUT DAMAGE TO AIRCRAFT. FOUND NR 4 CYLINDER, PISTON AND SPARK PLUGS SEVERELY DAMAGED. REMOVED AND REPAIRED NR 4 CYLIND	ER AND PISTON. AIRCRAFT OPS CHECKED AND RETURNED TO SERVICE.				1	L	7	1 	3O	3	O		2A13 	E274				 
1996020200533	19960202	00533	NE 	1996	2	2	96ZZZX523 	2	19951220	G	7321	0164248800	FUEL CONTROL 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1D 		NE 					ENGINE	DEFECTIVE 	B			DYRR	K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			IN	INSP/MAINT 	1			NM	11	6099P	442 			B236B	2818	9365			OCCASIONAL SMOKE AND FUEL SMELL EMITTING FROM HEATER OUTLET. REPLACED WITH NEW FCU, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1996020200534	19960202	00534	EU 	1996	2	2	96ZZZX524 	1	19951009	G	6730	AC67246	SERVO 	DUNLOP 		SNIAS 	350 	AS350B2 	8680813	EU 										M/R	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	6099P	210 	94 		RC206	2818				SERVO LEAKING FROM PILOT VALVE. REPLACED WITH REPAIRED UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1996020200535	19960202	00535	NE 	1996	2	2	96ZZZX525 	2	19950717	G	7250	411101007	NOZZLE ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					GAS PRODUCER	CRACKED 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	7059N	1189 			D159	7154	LE45754EF			NOZZLE ASSY CRACKED AND BURNED BEYOND SERVICEABLE LIMITS. UNIT IS NOT REPAIRABLE. REPLACED WITH REPAIRED UNIT, CORRECT	ED PROBLEM. ENGINE TOTAL CYCLES, 3,790.3.					1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996020200536	19960202	00536	NE 	1996	2	2	96ZZZX526 	2	19950822	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	7060G	621 			0492489	7173	LE45552EF			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,063.2.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996102400022	19961024	00022	SO 	1996	10	24	96ZZZX5265 	2	19950505	G	8520	5389441050	BOLT 			CESSNA	188 	A188B 	2073005	CE 	CONT 	O520 	IO520D 	17032	SO 					CYL HOLD DOWN	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	8999G	1001 				18801344	281226R			DURING ATTEMPT TO REMOVE CYLINDERS FROM ENGINE CASE, FOUND HOLD DOWN NUTS HAD BEEN OVERTORQUED AND HAD TO BE DRILLED TO 	BE REMOVED. FOUND MAIN JOURNAL WEB CRACKS IN CYLINDERS NR 4 AND NR 6. SUBMITTER BELIEVES HOLD DOWN NUTS OVERTORQUE TO 	BE A FACTOR IN CASE CRACKS.				1	L	7	1 	3O	3	O		A9CE 	E5CE				 
1996102400023	19961024	00023	SO 	1996	10	24	96ZZZX5266 	2	19950505	G	8520	5390501075	BOLT 			CESSNA	188 	A188B 	2073005	CE 	CONT 	O520 	IO520D 	17032	SO 					CYL HOLD DOWN	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	8999G	1001 				18801344	281226R			DURING ATTEMPT TO REMOVE CYLINDERS FROM ENGINE CASE, FOUND HOLD DOWN NUTS HAD BEEN OVERTORQUED AND HAD TO BE DRILLED TO 	BE REMOVED. FOUND MAIN JOURNAL WEB CRACKS IN CYLINDERS NR 4 AND NR 6. SUBMITTER BELIEVES HOLD DOWN NUTS OVERTORQUE TO 	BE A FACTOR IN CASE CRACKS.				1	L	7	1 	3O	3	O		A9CE 	E5CE				 
1996020200537	19960202	00537	NE 	1996	2	2	96ZZZX527 	2	19950825	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	71703	794 			1190802	7227	LE45514EF			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,927.3.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996020200538	19960202	00538	NE 	1996	2	2	96ZZZX528 	2	19950825	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	71703	794 			479	7227	LE45514EF			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,927.3.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996020200539	19960202	00539	NE 	1996	2	2	96ZZZX529 	2	19950825	G	7250	411100719	SHROUD 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					GAS PRODUCER	BLADE TIP RUB 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	71703	794 				7227	LE45514EF			TURBINE ROTOR HAS EXCESSIVE GP BLADE TIP RUB. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,927.3.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996010500411	19960105	00411		1996	1	5	96ZZZX53 	4	19951102	G	2210	KAP150	AUTOPILOT 	KING 		SOCATA	TB20 	TB20TRINIDAD	8680695	EU 										PITCH CONTROL	MALFUNCTION 	D				K				NONE 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			SW	05		400 								GYRO LIGHT ILLUMINATED AND ZERO VACUUM INDICATED. WITHIN A MATTER OF SECONDS, AUTOPILOT COMMANDS FULL NOSE-UP TRIM AND 	FULL-UP ELEVATOR. AUTOPILOT STILL PASSES SELF-TEST. SUBMITTER STATED AUTOPILOT SHOULD HAVE A DISCONNECT IN RELATION TO	 GYROS LIGHT AND SHOULD CONTROL TRIM MUCH SLOWER AND WITH AN AUDIBLE WARNING.				1	L	7	1 	3O			RT	A51EU 					 
1996020200540	19960202	00540	NE 	1996	2	2	96ZZZX530 	2	19950825	G	7250	410106701	SEAL RING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					1ST TURB SHROUD	WORN 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	71703	794 				7227	LE45514EF			SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,927.3.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996020200541	19960202	00541	NE 	1996	2	2	96ZZZX531 	2	19950908	G	7250	430144801	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 3 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	911VU	976 			1190690	7141	LE45582EF			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,870.4.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996020200542	19960202	00542	NE 	1996	2	2	96ZZZX532 	2	19950908	G	7230	430135703	SEAL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					NR 2 BEARING	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	911VU	976 			446	7141	LE45582EF			SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ENGINE TOTAL CYCLES, 4,870.4.						1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1996020200543	19960202	00543		1996	2	2	96ZZZX533 	4	19951024	G	3457	4530506	SENSOR 			SNIAS 	350 	AS350B2 	8680813	EU 										GPS	INTERMITTENT 	B			DYRR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	11	92LG				0190114	2575				GPS UNIT RETURNED FOR CREDIT AGAINST REPLACEMENT INVOICE NOTED ABOVE. UNIT REMOVED DUE TO INTERMITTENT SIGNAL. REPLACE	D WITH GPS-505 AS RECOMMENDED BY ARNAV.					1	G	7	1 	3U				H9EU 					 
1996020200544	19960202	00544	EU 	1996	2	2	96ZZZX534 	1	19950914	G	6730	AC67246	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	96LG	232 			RX184	2817				SERVO LEAKING BEYOND SERVCEABLE LIMITS. REPLACED WITH REPAIRED UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U				H9EU 					 
1996010500412	19960105	00412	EU 	1996	1	5	96ZZZX54 	1	19951103	G	3230		EXTENSION SYSTEM			SOCATA	TB20 	TB20TRINIDAD	8680695	EU 										MLG	MALFUNCTION 	D				K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			SW	05										PULLING LANDING GEAR MOTOR CIRCUIT BREAKER AND ENERGIZING GEAR EXTENSION WITH GEAR SELECTOR IN UP POSITION YIELDS 2 GREE	N ON MLG AND NO NOSE GEAR LIGHT WITH RED UNSAFE LIGHT ON. SUBSEQUENTLY, MOVING SELECTOR TO DOWN POSITION DOES NOT HELP.					1	L	7	1 	3O			RT	A51EU 					 
1996110100373	19961101	00373	EA 	1996	11	1	96ZZZX5406 	2	19950810	G	8520	78290	PLUNGER ASSY 			PIPER 	PA28 	PA28180 	7102808	SO 	LYC 	O360 	O360A1A 	41514	EA 					CAM FOLLOWER	FAILED 	D				K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			NM	01	5204L					284495	L1189836A			ENGINE REPORTED AS RUNNING ROUGH AT FULL POWER. DURING RUN-UP TO CONFIRM SQUAWK, NR 2 EXHAUST VALVE WAS SUCKED INTO CYL	INDER AND PUSHED THROUGH CYLINDER HEAD. A VALVE SPRING AND RETAINER WAS PUSHED THROUGH ROCKER BOX COVER. DISASSEMBLY R	EVEALED PLUNGER ASSY PART NR 78290 HAD BROKEN AND CUP PORTION HAD DISINTEGRATED. CAM FOLLOWER ALSO HAD BROKEN EDGES. C	ATASTROPHIC FAILURE OF VALVE TRAIN IS BELIEVED TO HAVE BEEN PRECIPITATED BY FAILURE OF PLUNGER ASSY.			1	L	7	1 	3O	3	O		2A13 	E286				 
1996010500413	19960105	00413	NE 	1996	1	5	96ZZZX55 	2	19951026	G	7260	311196801	GEAR 								PWA 	118 	PW118 		NE 					TOWER SHAFT	SHEARED 	D				E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	05					45C307		PCE115298			ENGINE HAD AN IFSD. TEAR DOWN OF ENGINE REVEALED THE TOWER SHAFT GEAR WAS SHEARED NEAR THE TOP OF THE GEAR. INVESTIGAT	ION AS TO ROOT CAUSE OF FAILURE IS ON-GOING.										4	T			E20NE				 
1996020900017	19960209	00017	EU 	1996	2	9	96ZZZX552 	1	19951117	G	5511	453005507	SPAR SPLICE 			ISRAEL	1124 	1124 	4500102	EU 										HORIZ STAB RT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	37BE	5293 				396				RIGHT OUTBOARD HINGE LUG FOUND CRACKED WHEN INSPECTING IAW AD 89-12-08. SUSPECT CAUSE IS STABILIZER SHAKING WHEN USING 	REVERSE THRUSTS. REPLACED SPLICE ASSY WITH P/N 453005-509. LANDINGS, 4,615.					2	M	7	2 	4F				A2SW 					 
1996020900020	19960209	00020	CE 	1996	2	9	96ZZZX555 	1	19951220	G	2752	505211511	SHAFT 		505212233 	BEECH 	90 	C90A 	1152911	CE 										LT OTBD FLAP	CRACKED 	B			MZ4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	17	8156Z	471 			636A92	LJ1333				FLAP ACTUATOR SHAFT WAS FOUND CRACKED THE ENTIRE LENGTH OF THE SHAFT. CAUSE OF CRACK IS UNKNOWN. THE FLAP MOTOR AND GE	AR BOX ASSY WERE ALSO FOUND TO BE WORN AT THIS SAME TIME.					1	L	7	2 	3T			RT	3A20 					 
1996020900021	19960209	00021	CE 	1996	2	9	96ZZZX556 	1	19951219	G	5320	10143002115	PANEL 			BEECH 	200 	200BEECH 	1152920	CE 										FS 227.125	CRACK 	B		A	EBVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	09	33KM	6582 				BB432				DURING AN OPERATIONAL TEST OF THE CABIN PRESSURIZATION SYSTEM, FOUND MAXIMUM DIFFERENTIAL COULD NOT BE OBTAINED WITH THE	 TEST UNIT. INVESTIGATION FOUND A 3 INCH OPENED CRACK IN THE LOWER FLANGE, CENTER CLOSE-OUT PANEL FOR THE AFT SPAR. ST	A 227.125. EFFECTED REPAIR AND RETURNED TO SERVICE.				1	L	7	2 	4T				A24CE 					 
1996020900022	19960209	00022	CE 	1996	2	9	96ZZZX557 	1	19951222	G	3232	C4860821	PIN 	RONSON 	24170161 	LEAR 	35 	35A 	5170602	CE 										GEAR DOOR	BROKEN 	D				O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			SW	09	873LP	3236 			3272	659				WHEN GEAR SELECTED DOWN, GEAR DOORS OPENED, BUT GEAR DID NOT DEPLOY. GEAR LOWERED USING EMERGENCY AIR SYSTEM. FOUND PI	N BROKEN IN PISTON, P/N C48608-19. THIS PISTON MOVES SWITCH TO SIGNAL DOORS OPEN FOR GEAR DOWN.					2	L	7	2 	4F				A10CE 					 
1996020900024	19960209	00024	EU 	1996	2	9	96ZZZX559 	1	19951206	G	6220	704A33633109	THRUST BEARING 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R	BLISTERED 	B			KO1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	707WR	775 			320	7239				THE MAIN ROTOR SPHERICAL THRUST BEARINGS HAVE BEEN MONITORED IN SERVICE ON THIS AIRCRAFT DUE TO THE WEAR OF THE ELASTOME	R MATERIAL. THESE BEARINGS HAVE A HISTORY OF A SHORT LIFE IN RELATIONSHIP TO THEIR PUBLISHED LIFE LIMIT OF 6,400 HOURS.					1	G	7	2 	3U				H11EU 					 
1996010500414	19960105	00414	EA 	1996	1	5	96ZZZX56 	1	19951101	G	5711		SPAR 			MNCOUP	90 	90A 	5810104	EA 										WING	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	11747					676				ON INSPECTION, MAIN SPAR FOUND WITH LATERAL CRACKS 18 INCHES IN LENGTH. WING OPENED FOR RECOVER. WING HAD HIT 'POLE' I	N 1956 (?) WAS IN STORAGE.					1	H	7	1 	3R				A306 					 
1996020900025	19960209	00025	EU 	1996	2	9	96ZZZX560 	1	19951206	G	6220	704A33633109	THRUST BEARING 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R	BLISTERED 	B			KO1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	707WR	775 			321	7239				THE MAIN ROTOR SPHERICAL THRUST BEARINGS HAVE BEEN MONITORED IN SERVICE ON THIS AIRCRAFT DUE TO THE WEAR OF THE ELASTOME	R MATERIAL. THESE BEARINGS HAVE A HISTORY OF A SHORT LIFE IN RELATIONSHIP TO THEIR PUBLISHED LIFE LIMIT OF 6,400 HOURS.					1	G	7	2 	3U				H11EU 					 
1996020900026	19960209	00026	EU 	1996	2	9	96ZZZX561 	1	19951206	G	6220	704A33633109	THRUST BEARING 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R	BLISTERED 	B			KO1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	707WR	775 			336	7239				THE MAIN ROTOR SPHERICAL THRUST BEARINGS HAVE BEEN MONITORED IN SERVICE ON THIS AIRCRAFT DUE TO THE WEAR OF THE ELASTOME	R MATERIAL. THESE BEARINGS HAVE A HISTORY OF A SHORT LIFE IN RELATIONSHIP TO THEIR PUBLISHED LIFE LIMIT OF 6,400 HOURS.					1	G	7	2 	3U				H11EU 					 
1996010500415	19960105	00415	CE 	1996	1	5	96ZZZX57 	1	19951101	G	2720	505243263	PEDAL HORN 			BEECH 	35 	V35B 	1151548	CE 										RUDDER	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4163A	2361 				D9121				ON PEDAL HORN EAR THE .1875 HOLE HAS ELONGATED DUE TO NORMAL PEDAL MOVEMENT AND VIBRATION. SUBMITTER STATED THIS CAUSES	 A SLOPPY PEDAL CONDITION AND POSSIBLE EVENTUAL FAILURE OF PART RESULTING IN LOSS OF BRAKING AND POSSIBLE LOSS IN RUDDER	 CONTROL.				1	L	7	1 	3O				3A15 					 
1996020900284	19960209	00284	CE 	1996	2	9	96ZZZX574 	1	19950824	G	3244		TIRE 	GOODYEARAERO		LEAR 	25 	25 	5170506	CE 										RT MLG	BLOWN 	E				C				ABORTED TAKEOFF 				O			OTHER 			TO	TAKEOFF 	1			SW	09	345MC	102 				046				BLOW-OUT ON RIGHT MAINS (2 EACH). PILOT REPORTED SEEING OBJECT ON RUNWAY PRIOR TO V1 AND THEN VIBRATION. ABORTED TAKEO	FF AND THEN PULLED OFF ON TAXIWAY.					2	L	7	2 	4J				A10CE 					 
1996020900285	19960209	00285	CE 	1996	2	9	96ZZZX575 	1	19951221	G	2730	04341552	TORQUE TUBE 			CESSNA	150 	152 	2071835	CE 										RT ELEVATOR	CRACKED 	D	P	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	17	94111	6765 				15285599				FOUND AT 100-HOUR INSPECTION. CIRCUMFERENTIAL CRACK IN RIGHT ELEVATOR TORQUE TUBE. TSN - 6,851.8. CHECKED AIRCRAFT HI	STORY, NO UNUSUAL OCCURRENCES DOCUMENTED. USED PRIMARILY IN FLIGHT TRAINING.					1	H	7	1 	3O			NT	3A19 					 
1996020900286	19960209	00286	CE 	1996	2	9	96ZZZX576 	1	19951128	G	3240	215284	BRAKE ASSY 			CESSNA	500 	550 	2076604	CE 										LT MLG	ROTOR CRACKED 	D	S	A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	05	75ZA		502 			5500214				BRAKES REPLACED DUE TO WEAR INDICATOR 'BRAKES WORN TO LIMITS'. UPON DISASSEMBLY, FOUND ONE ROTOR CRACKED THROUGH ENTIRE	 LENGTH. FOUND TWO ROTORS WITH SAME DEFECT ON RIGHT BRAKE ASSEMBLY. THESE BRAKE ASSEMBLIES HAVE 502.3 HOURS SINCE OVER	HAUL AND 480 LANDINGS. THESE BRAKES INSTALLED ON CESSNA CITATION 550. SUBMITTER STATED THIS APPEARS TO BE A RECURRING 	PROBLEM.			1	L	7	2 	4F				A22CE 					 
1996010500416	19960105	00416	CE 	1996	1	5	96ZZZX58 	1	19951101	G	2720	505243264	PEDAL HORN 			BEECH 	35 	V35B 	1151548	CE 										RUDDER	WORN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	4163A	2361 				D9121				ON PEDAL HORN EAR THE .1875 HOLE HAS ELONGATED DUE TO NORMAL PEDAL MOVEMENT AND VIBRATION. SUBMITTER STATED THIS CAUSES	 A SLOPPY PEDAL CONDITION AND POSSIBLE EVENTUAL FAILURE OF PART RESULTING IN LOSS OF BRAKING AND POSSIBLE LOSS IN RUDDER	 CONTROL.				1	L	7	1 	3O				3A15 					 
1996020900295	19960209	00295	SO 	1996	2	9	96ZZZX585 	2	19951130	G	8530	653452	CYLINDER 			CESSNA	404 	404CESSNA 	2075901	CE 	CONT 	O520 	GTSIO520M 	17032	SO 					LT ENG NR 4 INT	CRACKED 	D				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	17	37167	100 				4040129	276434R			DURING 100-HOUR INSPECTION OF ENGINE, A FACTORY REMANUFACTURE WITH 100 HOURS ON IT, A CRACK OR CASTING FLAW WAS DISCOVER	ED NEAR THE INTAKE FLANGE AREA, APPROXIMATELY .75 INCH DOWN FROM THE INTAKE FLANGE TOWARDS THE FIN AREA WHERE THE FINS M	EET THE INTAKE PORT ON CYLINDER NR 4 OF LEFT ENGINE.				1	L	7	2 	3O	3	O		A25CE 	E7CE				 
1996020900299	19960209	00299	SO 	1996	2	9	96ZZZX589 	1	19951221	G	2140	488636	COMBUSTION TUBE 		940K12 	PIPER 	PA23 	PA23250 	7102308	SO 										HEATER	DETERIORATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	23	5693Y		480 		845	272813				DURING DIAGNOSTIC INSPECTION OF MALFUNCTIONING HEATER, DETERMINED REMOVAL OF THE ENTIRE HEATER FROM THE AIRCRAFT WAS WAR	RANTED. AFTER REMOVAL, SUBSEQUENT INSPECTION REVEALED ENTIRE END OF COMBUSTION TUBE WAS DETERIORATED AND LAYING IN THE 	BOTTOM OF THE TUBE (LOOSE). OWNER ADVISES AIRCRAFT WAS NOT FLOWN OFTEN IN MANY YEARS. SUBMITTER RECOMMENDS THESE TYPE 	HEATERS BE REMOVED AND INSPECTED BASED ON CALENDAR TIME, FREQUENCY OF USE, AND STORAGE CONDITIONS AS WELL AS HOURLY USAG	E.		1	L	7	2 	3O				1A10 					 
1996121200100	19961212	00100	CE 	1996	12	12	96ZZZX5905 	1	19951117	G	2810	0426512	STRAP 			CESSNA	150 	150G 	2071816	CE 										LT FUEL TANK	BROKEN 	H		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	16	2974S	2789 				15066874				WHILE REPLACING RUSTY LEFT FUEL TANK COVER SCREWS, FOUND REAR INBOARD TANK STRAP BROKEN AT BEND-WEAR MARKS ON TOPS OF TA	NK AND TANK COVER-INDICATIONS ARE TANK COVERS HAD NEVER BEEN REMOVED SINCE MANUFACTURE-FOUND SAME PROBLEM WITH RIGHT TAN	K STRAP 2-9-94 AT 2756.70 HRS.				1	H	7	1 	3O				3A19 					 
1996020900305	19960209	00305	CE 	1996	2	9	96ZZZX595 	1	19951128	G	2820	050010683	LINE 			CESSNA	172 	172M 	2072418	CE 										RT WING FUEL	LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	09	19992	7470 				17260917				FUEL DYE STAINS NOTICED ON UNDERSIDE OF RIGHT WING AT ROOT. CLEANED AREA AND CHECKED FOR LEAK. NO LEAK NOTED. AFTER P	LANE SAT FOR 6 TO 8 HOURS, MORE FUEL STAINS NOTED. FOUND SMALL PINHOLE, .75 INCH, FROM TANK CONNECTION ON THE SOLID LIN	E. UPON PROBING WITH PICK, THE HOLE ENLARGED TO .0625 INCH IN DIAMETER. THE OUTSIDE OF THE LINE HAD SURFACE CORROSION 	AT THIS POINT WHICH PROBABLY CONTRIBUTED TO THE FORMATION OF THE HOLE.			1	H	7	1 	3O			NT	3A12 					 
1996020900306	19960209	00306	CE 	1996	2	9	96ZZZX596 	1	19951201	G	2810	O5235228	STRAP ASSY 			CESSNA	172 	172M 	2072418	CE 										RT INBD TANK	BROKEN 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	09	19992	7470 				17260917				AFTER REPAIRING A DEFECTIVE FUEL LINE TO CORRECT A LEAK, FUEL WAS PUT INTO TANK. A LEAK WAS STILL NOTED. REMOVED TANK 	AND FOUND BOTH STRAPS BROKEN WHERE THEY ARE FASTENED TO THE OUTBOARD STRAPS. A CRACK WAS FOUND ON THE WELDED BOSS FOR T	HE FINGER STRAINER/OUTLET CONNECTION. SUBMITTER SUGGESTS PERIODICALLY CHECKING FUEL TANK STRAPS FOR SECURITY TO PREVENT	 TANK MOVEMENT.			1	H	7	1 	3O			NT	3A12 					 
1996010500418	19960105	00418	CE 	1996	1	5	96ZZZX60 	1	19950829	G	5553	04320049	BRACKET 			CESSNA	150 	152 	2071835	CE 										V-FIN ATTACH	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	24353	7650 				15280232				WHILE PERFORMING 100-HOUR INSPECTION AND AD 80-11-04 (VERTICAL FIN ATTACH NUTPLATE), FOUND ATTACH BRACKET CRACKED IN 5 P	LACES. NUTPLATES WERE IN GOOD CONDITION. BRACKET WAS REPLACED. SUBMITTER SUGGESTS THE AREA SHOULD BE CLEANED VERY WEL	L BEFORE INSPECTION IS MADE AS THESE CRACKS ARE VERY DIFFICULT TO SEE.				1	H	7	1 	3O			NT	3A19 					 
1996020900310	19960209	00310	CE 	1996	2	9	96ZZZX600 	1	19951201	G	2810	07260011	BLADDER 	USRUBBER 		CESSNA	182 	182C 	2072708	CE 										FUEL TANK LT	LEAK 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	01	8561T				3626	52461				BLADDER FUEL TANKS LEAKED FUEL WHEN FILLED ABOVE ONE-HALF FULL MARK. CAUSED BY ABRASION DURING COLLAPSING OF FUEL TANK.	 RECOMMEND REPLACEMENT WITH FIBERGLASS TANKS.					1	H	7	1 	3O			NT	3A13 					 
1996020900311	19960209	00311	CE 	1996	2	9	96ZZZX601 	1	19951201	G	2810	07260012	BLADDER 	USRUBBER 		CESSNA	182 	182C 	2072708	CE 										FUEL TANK RT	LEAK 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	01	8561T				3669	52461				BLADDER FUEL TANKS LEAKED FUEL WHEN FILLED ABOVE ONE-HALF FULL MARK. CAUSED BY ABRASION DURING COLLAPSING OF FUEL TANK.	 RECOMMEND REPLACEMENT WITH FIBERGLASS TANKS.					1	H	7	1 	3O			NT	3A13 					 
1996121900273	19961219	00273	NE 	1996	12	19	96ZZZX6073 	2	19951205	G	7260	3019539	SEAL 			CESSNA	500 	550 	2076604	CE 	PWA 	JT15 	JT15D4 	52112	NE 					N2 TACH DRV	FAILED 	H				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			J	K		WARNING INDICATION 	FLUID LOSS 		NR	NOT REPORTED 	1			SW	17	4614N	23 				5500659	PCE71637			22.5 HOURS AFTER INSTALLATION OF OVERHAULED ENGINE, OIL PRESSURE LIGHT ILLUMINATED ON MASTER CAUTION PANEL AND OIL PRESS	URE INDICATED 35 PSI. ENGINE WAS SHUT DOWN AND A PRECAUTIONARY LANDING WAS MADE AT NEAREST AIRPORT. DURING TROUBLESHOO	TING, OIL LEAK WAS FOUND AT N2 TACH GENERATOR DRIVE. REPLACED SEAL, OPS CHECKED OK. OVERHAUL FACILITY ADVISED OPERATOR	 OF A SIMILAR RECENT OCCURRENCE ON LIKE ACFT/ENGINE INSTALLATION AND THEY SUSPECT SEALS NEED TO BE IMPROVED TO HANDLE TH	E INCREASED OIL CAPACITY OF IMPROVED PUMPS.		1	L	7	2 	4F	4	F		A22CE 	E1NE				 
1996020900625	19960209	00625	EU 	1996	2	9	96ZZZX609 	1	19951122	G	2820		BREAK-AWAY TUBE 	AEROQUIP 		BOLKMS	117 	BK117A1 	5626010	EU 										FUEL CELLS	MISMANUFACTURED 	B	L	A	BAQR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	03	39257				0302	S7027				FOR REASONS UNKNOWN, ACFT'S BREAK-AWAY TUBE STARTED LEAKING FUEL. BREAK-AWAY TUBE INTERCONNECTS AFT FUEL CELL WITH FWD 	FUEL CELL & IS DESIGNED TO SEAL OFF TANKS IN THE EVENT OF A CRASH. PROBLEM WAS NOT OLD PART INSTALLED IN ACFT, WHICH HA	S ACCUMULATED OVER 6,000 HRS & 28,000 LANDINGS, IT HAD PROBABLY REACHED ITS AGE LIMIT. PROBLEM WAS NEW FACTORY PARTS RE	CEIVED. NEW PARTS WERE IN AN UNAIRWORTHY CONDITION UPON RECEIPT. BOTH ENDS OF THE TUBE HAVE SPRING LOADED POPPET VALVE	S IN CLOSED POSITION NOT ALLOWING FUEL TO TRANSFER. THIS CONDITION CAME RIGHT OUT OF 1988 PKG OLD (NEW) PARTS. DATA TA	GS DID NOT SHOW SHELF LIFE. A RECOMMENDED SHELF LIFE SHOULD BE ON PART DUE TO O-RING'S & SEALS INSTALLED IN THE TUBE.	1	G	7	2 	3U				H13EU 					 
1996010500419	19960105	00419	SO 	1996	1	5	96ZZZX61 	2	19951206	G	7414	105136539	MAGNETO 		S6LN21 	CESSNA	172 	172C 	2072408	CE 	CONT 	O300 	O300C 	17022	SO 					FRONT HOUSING	BEARING LOOSE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	1851Y	448 			I299206DR	17249451				TIME SINCE MAGNETO FACTORY REBUILT, 448.4 HOURS. DURING INSPECTION (500-HOURS), DISCOVERED FRONT BEARING RACE WAS LOOSE	 IN FRONT HOUSING. NOT APPARENT UNTIL WIPED GREASE OFF TO REPLACE WITH NEW GREASE. SUSPECT CAUSE: MAXIMUM TOLERANCE F	IT WHEN ASSEMBLED AT FACTORY REBUILD.				1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1996020900630	19960209	00630	NE 	1996	2	9	96ZZZX614 	2	19951213	G	7250	414129001	ROTOR 			BELL 	222 	222B 	1182124	SW 	LYC 	LTS101	LTS101750C1 	41560	NE 					PT ROTOR	BLADE SHIFT 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	911RA	40 				47150	LE47228			POWER TURBINE ROTOR INSPECTION, SB LT101-72-50-0153, COMPLIED WITH EARLY DUE TO ANNUAL INSPECTION FOUND UNSERVICEABLE. T	IME SINCE INSTALLATION 40.3 HOURS. CYCLES, 65.					1	G	7	2 	3U	3	U		H9SW 	E5NE				 
1996122600409	19961226	00409	CE 	1996	12	26	96ZZZX6158 	1	19951214	G	2730		CONTROL ROD 			BEECH 	18 	E18S 	1151006	CE 										ELEVATOR	DETACHED 	C		A		A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			TO	TAKEOFF 	1			WP	07	5609D					BA315				ELEVATOR CONTROL ROD AT ELEVATOR ATTACH POINT DISCONNECTED WHEN BOLT FELL OUT ON TAKEOFF. COTTER KEY AND CASTLE NUT WER	E MISSING. BOTH FELL OUT RESULTING IN ELEVATOR TRAILING IN-FLIGHT. BOLT AND WASHERS WERE FOUND IN TAIL CONE. CASTLE N	UT AND KEY WERE NOT FOUND.				1	L	7	2 	3R				A765 					 
1996020900632	19960209	00632	GL 	1996	2	9	96ZZZX616 	2	19950829	G	7321	252464429	FUEL CONTROL 			BELL 	206 	206B3 	1181506	SW 	ALLSN 	250C 	250C20B 	03013	GL 					DRIVE BEARING	FAILURE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	50054	2001 			334442	2537				FAILURE OF DRIVE BEARINGS AND DAMAGE TO INTERNAL FLYWEIGHTS AND HOUSING CAUSED HIGH END TURBINE RUNAWAY RESULTING IN ENG	INE OVERSPEED.					1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1996010500420	19960105	00420	SO 	1996	1	5	96ZZZX62 	2	19951204	G	7314	64621216	PUMP 			BEECH 	33 	F33A 	1151425	CE 	CONT 	O520 	IO520BB 	17032	SO 					ENGINE FUEL	SHAFT SHEARED 	D				O				OTHER 				Y			ENGINE STOPPAGE 			CL	CLIMB 	1			WP	07	5587K	2340 	620 		H139202BR	CE1392	285675R			ENGINE DRIVEN FUEL PUMP FAILED ON CLIMB AT 400 FEET AGL.						1	L	7	1 	3O	3	O		3A15 	E5CE				 
1996020900637	19960209	00637	GL 	1996	2	9	96ZZZX621 	1	19951227	G	2510		BELT 			AMTR 	CHLNGR	CHALLENGER2 	05676V6	GL 										SEAT	DEFECTIVE 	H	L			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	13	9213A					CH20395CW131				DURING AN AIRWORTHINESS CERTIFICATION INSPECTION OF A COMPLETED CHALLENGER2 AIRCRAFT KIT, DISCOVERED THE SEAT BELT ASSEM	BLIES SUPPLIED BY THE KIT MANUFACTURER, QUAD CITY AIRCRAFT CORPORATION, WERE DEFECTIVE. AS SUCH, THE BUCKLE MAY INADVER	TENTLY OPEN ON IMPACT, THEREBY NEGATING THE SAFETY VALUE OF THESE ASSEMBLIES.				1	H	7	1 	3I			NT	EXPA1H71					 
1996010500421	19960105	00421	EA 	1996	1	5	96ZZZX63 	2	19951121	G	8520		CRANKCASE 			PIPER 	PA31 	PA31350 	7103110	SO 	LYC 	O540 	TIO540J2BD 	41532	EA 					RT FORWARD	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	59919		6 			317552038				A CRACK DEVELOPED 6 HOURS AFTER MAJOR OVERHAUL FROM LYCOMING. THE CRACK WAS 2.5 INCHES TO 3 INCHES LONG. SUBMITTER BEL	IEVES THE CRACK MUST HAVE BEEN THERE WHEN IT LEFT THE FACTORY. THIS ENGINE WAS A FACTORY REMANUFACTURE.					1	L	7	2 	3O	3	O		A20SO 	E14EA				 
1996010500422	19960105	00422	GL 	1996	1	5	96ZZZX64 	1	19951111	G	7410		IGNITION SYSTEM 			AMTR 	SONERI	SONERAI2 		GL 	AMTRVW	VOLKS 	VW2200VOLKS 		GL 					ENGINE	FAILED 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			WP	17	912BS	184 				1189L				AT 1,500 MSL, BOTH IGNITION SOURCES FAILED TO PRODUCE HIGH VOLTAGE TO THE SPARK PLUGS RESULTING IN THE REDUCTION OF ENGI	NE POWER AND THE ENGINE STOPPED ROTATION. THE AIRCRAFT CRASHED IN AN OPEN FIELD WITH MINOR DAMAGE. BOTH COILS' NEGATIV	E TERMINALS EXHIBIT WIRES CONNECTED TOGETHER AT A SINGLE POLE SWITCH ATTACHED TO THE ELECTRONIC TACHOMETER THAT HAD AN I	NTERNAL GROUND FAULT THAT CAUSED THE COILS TO OVERHEAT, AND INTERNALLY FAIL TO PRODUCE HIGH VOLTAGE IGNITION TO THE SPAR	K PLUGS.		1	M	7	1 	3O	3	O		EXPA1M71	EXP3O				 
1996010500423	19960105	00423	GL 	1996	1	5	96ZZZX65 	1	19951111	G	7714		TACHOMETER 			AMTR 	SONERI	SONERAI2 		GL 	AMTRVW	VOLKS 	VW2200VOLKS 		GL 					ENGINE	SHORTED 	G				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			WP	17	912BS	184 				1189L				AT 1,500 MSL, BOTH IGNITION SOURCES FAILED TO PRODUCE HIGH VOLTAGE TO THE SPARK PLUGS RESULTING IN THE REDUCTION OF ENGI	NE POWER AND THE ENGINE STOPPED ROTATION. THE AIRCRAFT CRASHED IN AN OPEN FIELD WITH MINOR DAMAGE. BOTH COILS' NEGATIV	E TERMINALS EXHIBIT WIRES CONNECTED TOGETHER AT A SINGLE POLE SWITCH ATTACHED TO THE ELECTRONIC TACHOMETER THAT HAD AN I	NTERNAL GROUND FAULT THAT CAUSED THE COILS TO OVERHEAT, AND INTERNALLY FAIL TO PRODUCE HIGH VOLTAGE IGNITION TO THE SPAR	K PLUGS.		1	M	7	1 	3O	3	O		EXPA1M71	EXP3O				 
1996010500576	19960105	00576	SO 	1996	1	5	96ZZZX66 	1	19951212	G	7810	5327	MUFFLER 			MAULE 	MX7 	MXT7180 	5470206	SO 										RT SIDE FWD/AFT	WELD CRACKED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	9209Y	424 				140130				MUFFLER CRACKED ON BOTH ENDS AROUND THE WELDED AREA NEXT TO THE NR 1 RISER ON THE FORWARD SIDE AND THE TAIL PIPE ON THE 	AFT SIDE. SUBMITTER BELIEVES THE MUFFLER MAY HAVE TOO MUCH STRAIN ON THE INLET AND OUTLET PIPES.					1	H	7	1 	3O			NC	3A23 					 
1996010500577	19960105	00577	SO 	1996	1	5	96ZZZX67 	1	19951212	G	7120	8621202	MOUNT 			PIPER 	PA44 	PA44180 	7104402	SO 										ENGINE	BROKEN 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	270FN	3923 				447995110				MOUNT WAS FOUND BROKEN IN 2 PLACES; BOTH OUTBOARD AND BELOW THE UPPER LEFT MOUNTING FLANGE. A SMALL AMOUNT OF INTERNAL 	CORROSION WAS DETECTED, BUT IT DID NOT APPEAR TO BE A CONTRIBUTING FACTOR. THE BROKEN AREAS WERE NOT ON WELD JOINTS, IT	 APPEARS THAT THE SUPPORT TUBE ASSEMBLIES FAILED.				1	L	7	2 	3O				A19S0 					 
1996021600660	19960216	00660	EA 	1996	2	16	96ZZZX673 	1	19951226	G	5700		STRUT 			SCWZER	G164 	G164A 	3952704	EA 										LT 'N' STRUT	CORRODED 	D	L			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	84PG	4375 				1536				DURING ANNUAL INSPECTION, A RIVET HEAD FOUND MISSING FROM LOWER FITTING ON THE LT 'N' STRUT. DURING ATTEMPT TO REPAIR, 	STRUT WAS REMOVED AND SEVERE CORROSION WAS FOUND WHICH CAUSED REDUCTION OF WALL THICKNESS BY 40 PERCENT.					1	Q	7	1 	3R				1A16 					 
1996021600665	19960216	00665	CE 	1996	2	16	96ZZZX678 	1	19951211	G	5511	043200156	SPAR 			CESSNA	150 	150K 	2071822	CE 										HORIZ STAB	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	01	5852G	5010 				15071352				DURING REPLACEMENT OF NUTPLATES TO TERMINATE AD 80-11-04, NOTED AFT SPAR REINFORCEMENT WAS CRACKED (PN 0432001-15) AND T	HE AFT SPARS (PN 0432001-56) WERE ALSO CRACKED. SUGGEST THESE PARTS BE INSPECTED AT TERMINATIION OF AD 80-11-04. SUBMI	TTER NOTED EXCESSIVE 'CREAKING' NOISES WHEN MOVING HORIZONTAL UP/DOWN DURING SECURITY CHECK.				1	H	7	1 	3O				3A19 					 
1996010500578	19960105	00578	CE 	1996	1	5	96ZZZX68 	1	19951111	G	2140	99103053	BLOWER 	JANITROL 		CESSNA	414 	414A 	2075907	CE 										HEATER	INOP 	G		A		C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			A			FLAME/FIRE 			TO	TAKEOFF 	1			GL	03	414CA	4305 				414A0479				ON TAKEOFF ROLL, RIGHT SEAT OCCUPANT NOTICED FIRE ON RIGHT FRONT FUSELAGE. TAKOFF WAS ABORTED. THE MECHANIC TROUBLESHO	OTING THE PROBLEM DISCOVERED THE COMBUSTION HEATER AIR BLOWER WAS INOPERATIVE AND COMBUSTION AIR SWITCH WAS STUCK IN THE	 CLOSED POSITION. BOTH ITEMS WERE REMOVED AND REPLACED, AND AIRCRAFT OPS CHECKED GOOD.				1	L	7	2 	3O				A7CE 					 
1996021600667	19960216	00667	SO 	1996	2	16	96ZZZX680 	1	19951219	G	3710	442CW	PUMP 	AIRBORNE 		PIPER 	PA31 	PA31P350 	7103111	SO 										VACUUM SYSTEM	SEPARATED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	92444		87 		50666	31P8414014				VACUUM PUMP WAS REPORTED INOP. UNCOWLED ENGINE. FOUND PUMP LAYING IN ENGINE COMPARTMENT SEPARATED IN 2 PIECES. CASTIN	G FAILURE.					1	L	7	2 	3O			RT	A8EA 					 
1996021600669	19960216	00669	CE 	1996	2	16	96ZZZX682 	1	19951227	G	2810		CAP 			CESSNA	185 	185 	2072802	CE 										FUEL TANK	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	07	61341	2125 				18504151				FUEL STAINS WERE NOTICED STREAKING AFT FROM THE FILLER CAPS. SMALL AMOUNTS OF WATER WERE ALSO NOTICED WHILE SUMPING FUE	L TANKS. INSPECTION REVEALED THE SEALS ON THE CAPS WERE BADLY CRACKED AND ALLOWING BOTH WATER INTO THE FUEL SYSTEM AND 	FUEL TO SEEP OUT IN-FLIGHT. REPLACEMENT OF THE CAP/ADAPTER ASSYS CURED BOTH PROBLEMS.				1	H	7	1 	3O			NC	3A24 					 
1996021600670	19960216	00670	CE 	1996	2	16	96ZZZX683 	1	19951221	G	2730	12632382	ACTUATOR 			CESSNA	210 	P210N 	2073454	CE 										RT HORIZ STAB	CRACKED 	D				O				OTHER 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			GL	21	210BG	2260 				P21000025				ELEVATOR TRIM BECAME FROZEN IN-FLIGHT AND WAS NOT ABLE TO OPERATE TRIM WHEEL IN BELOW FREEZING TEMPERATURE. AFTER ENTER	ING SHOP, TRIM WHEEL WAS FREE, BUT STICKY. FOUND TRIM ACTUATOR CRACKED AND DIRTY. SUBMITTER STATED ACTUATOR MAY NOT HA	VE BEEN SERVICED PROPERLY AND MAY HAVE IMPROPER GREASE.				1	H	7	1 	3O				3A21 					 
1996021600671	19960216	00671	SO 	1996	2	16	96ZZZX684 	1	19951215	G	2410	646405	BRACKET 			PIPER 	PA46 	PA46310P 	7104605	SO 										NR 2 ALTERNATOR	CRACKED 	B			LF1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	07	9100Z	121 				4608014				DURING ANNUAL INSPECTION, FOUND NR 2 ALTERNATOR BRACKET CRACKED. PART TOTAL TIME 121.0 HRS. BELT TENSION WAS CORRECT. 	 WHEN REPLACING BRACKET, FOUND SHIMS NEEDED TO BE INSTALLED BETWEEN BRACKET AND ENGINE. SUBMITTER STATED OLD BRACKET WA	S APPARENTLY PRE-LOADED. CAREFUL ATTENTION MUST BE PAID TO ALIGNMENT AND FIT.				1	L	7	1 	3O				A25SO 					 
1996021600674	19960216	00674	CE 	1996	2	16	96ZZZX687 	1	19951207	G	6100		SAFETY WIRE 			CESSNA	150 	152 	2071835	CE 										MOUNT BOLTS	ERROR 	B			EHHR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17										PERTAINS TO AD 95-21-01 WHICH REFERS TO MCCAULEY SB 219 WHICH HAS A STEP-BY-STEP INSTRUCTION ON PERFORMING THIS AD TO TH	E PROPELLER. STEP 2F STATES THAT MOUNTING BOLTS ARE TO BE SAFETIED WITH .032 INCH SAFETY WIRE. AC 43:13 STATES THAT .0	41 INCH STAINLESS STEEL WIRE, MINIMUM, IS TO BE USED. CALLED MCCAULY ON THIS MATTER AND THEY WERE NOT AWARE OF THE MIST	AKE AT THAT TIME. THIS WAS ABOUT A MONTH AGO, AND STILL NO REVISION TO THE SB.			1	H	7	1 	3O			NT	3A19 					 
1996021600675	19960216	00675	SO 	1996	2	16	96ZZZX688 	1	19951204	G	3246	4046	WHEEL 	PARKERHANFIN		GULSTM	G44 	G44A 	3951508	SO 										MOUNT SURFACE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	07	44CH	649 				1454				WHEN INSTALLING NEW TIRES, NOTICED CRACKS AROUND BOLT HOLES ON LEFT OUTER WHEEL HALF. THREE OTHER HALVES WERE EDDY CURR	ENT CHECKED. RIGHT OUTER AND INNER WHEEL HALVES WERE FOUND CRACKED AROUND BOLT HOLES. USING A SURFACE TABLE AND HEIGHT	 GAUGE, CHECKED THE STEPS AT THE WHEEL MOUNTING SURFACES AND FOUND THE BOLT SURFACES COULD NOT COME IN CONTACT WITH EACH	 OTHER BECAUSE OF THE INTERFERENCE AT ALIGNMENT STEP.			1	H	7	2 	3I			O	A734 					 
1996021600676	19960216	00676	CE 	1996	2	16	96ZZZX689 	1	19951227	G	2820	20000104	VENT LINE 			CESSNA	177 	177B 	2073708	CE 										FUEL TANK	CORRODED 	B	P	A	FK8R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	07	34099	1859 				17701639				ALUMINUM VENT LINE FROM FUEL TANK PITTED TO FAILURE DUE TO CORROSION. NOTED WHEN TANKS WERE FILLED. FUEL LEAKED INSIDE	 CABIN REAR SIDE WINDOW. BARE TUBING IN CONTACT WITH VENT DUCTING. POINT OF CONTACT WAS SITE OF PIT. SUSPECT CAUSE DU	E TO DISSIMILAR MATERIALS IN THE PRESENCE OF MOISTURE. SUBMITTER RECOMMENDS SHEATHING ENTIRE LENGTH OF VENT LINE WITH N	ON-CONDUCTIVE MATERIAL TO PREVENT CONTACT BETWEEN FUEL TANK VENT LINE AND VENTILATION DUCTING.			1	H	7	1 	3O				A13CE 					 
1996010500579	19960105	00579	CE 	1996	1	5	96ZZZX69 	1	19951204	G	2750	07606127	PULLEY 			CESSNA	172 	172M 	2072418	CE 										LT FLAP CONTROL	BRACKET BENT 	G	L	A		L				ABORTED APPROACH 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			GL	23	13923					17263039				DURING FIRST TOUCH AND GO LANDING, WHEN FLAPS LOWERED, ABNORMAL CONTROL RESPONSE NOTED. LT FLAP HAS MORE EXTENSION THAN	 RT FLAP. ABORTED AND MADE NEW APPROACH TO A LANDING. FOUND FLAP CONTROL SYSTEM HAD A BENT PULLEY BRACKET WHERE ROD (A	LSO BENT) IS ATTACHED. THE BRACKET BENT UNTIL PULLEY WAS CONTACTED CAUSING FLAP PROBLEM.				1	H	7	1 	3O			NT	3A12 					 
1996021600678	19960216	00678	CE 	1996	2	16	96ZZZX691 	1	19950713	G	3230	08421022	IDLER BELLCRANK 			CESSNA	310 	310P 	2074238	CE 										NLG	CRACKED 	D		A		A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			WP	01	5872M	3780 				310P0172				NOSE LANDING GEAR FAILED TO RETRACT ON TAKEOFF. PILOT REPORTED LOUD BANG AS LANDING GEAR RETRACTED. AIRCRAFT MADE NOSE	-UP LANDING. NO ONE INJURED AND AIRCRAFT DAMAGE MINIMAL. SUSPECT RIGHT NOSE GEAR DOOR CLEVIS BOLT FAILURE CAUSED INCID	ENT TO OCCUR. FATIGUE LIFE OF IDLER BELLCRANK SUSPECT ALSO. SUBMITTER RECOMMENDS COMPLETE INSPECTION OF LANDING GEAR D	OOR ACTUATOR ROD ENDS AND IDLER BELLCRANK AT REGULAR INSPECTION INTERVALS.			1	L	7	2 	3O				3A10 					 
1996021600679	19960216	00679	CE 	1996	2	16	96ZZZX692 	1	19951129	G	7820	08506508	MUFFLER 			CESSNA	310 	310H 	2074220	CE 										WING NACELLE	FRACTURED 	D	P			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	02	1052Q					310H0052				MUFFLER HOUSING (SHELL) FRACTURED ALLOWING EXHAUST INTO AFT SECTION OF ENGINE NACELLE CAUSING CORROSION AND HOT SPOTS. S	UBMITTER STATED THIS DEFECT HAS THE POTENTIAL TO CAUSE A FIRE IN THE WING OR FAILURE DUE TO CORROSION ALSO. SUBMITTER S	TATED THERE IS NO REQUIREMENT IN CESSNA 310 SM NR P150C FOR REMOVAL OF THE MUFFLER FOR INSPECTION DURING A 100-HOUR OR A	NNUAL OR HOURLY INSPECTION. SUBMITTER RECOMMENDS AN INSPECTION OF A SCHEDULED HOURLY TYPE, INCORPORATING THE REMOVAL OF	 THE MUFFLER, TO ACCOMMODATE INSPECTION OF THE NACELLE AND MUFFLER INTEGRITY.		1	L	7	2 	3O				3A10 					 
1996021600681	19960216	00681	CE 	1996	2	16	96ZZZX694 	1	19951209	G	3213	08412011	STRUT 			CESSNA	310 	310D 	2074212	CE 										LT MLG	BROKEN 	D		A		K				NONE 				O			OTHER 			LD	LANDING 	1			SW	07	6925T	5529 				39225				AIRCRAFT MADE A NORMAL LANDING. AFTER TOUCH-DOWN, THE LT MAIN GEAR BROKE AT WELD ON LOWER STRUT ASSY. AIRCRAFT LEFT RU	NWAY CAUSING SUBSTANTIAL DAMAGE. AIRCRAFT RECORDS INDICATE REPAIRS HAD BEEN MADE TO LT GEAR DUE TO HARD LANDINGS ON 8-3	1-95 AT 5,265.0 AFTT. SUBMITTER RECOMMENDS NDT INSPECTION TO WELD AREA AFTER HARD LANDING AND EVERY 3,000 HOURS AIRCRAF	T TOTAL TIME.			1	L	7	2 	3O				3A10 					 
1996021600685	19960216	00685	WP 	1996	2	16	96ZZZX698 	2	19951227	G	7261	89476411	STRAINER 								GARRTT	TFE731	TFE731* 	01518	WP 					ENGINE OIL	MISLABELED 	B		A	IY2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15										C/W ALLIED SIGNAL SB TFE 731-79-3058, A 'NEW' OIL JET STRAINER P/N 894764-11 INSTALLED TO REPLACE DASH 9 STRAINER. CMPT	 CONTROLS OIL FLOW TO NR 4 & NR 5 BEARING CAVITY. TWO DASH 11 STRAINERS ORDERED FROM ALLIED SIGNAL. RECEIVING INSPECTI	ON, FOLLOWING NOTED: EXIT ORIFICE OF 2 STRAINERS WERE DIFFERENT SIZES. STRAINER WITH 'SMALL' ORIFICE STAMPED (PERFECTL	Y ROUND & NO BURRS). STRAINER WITH 'LARGE' ORIFICE DRILLED (HOLE NOT ROUND & BURRED EDGES). NEITHER STRAINER IDENTIFIE	D, NOR WAS PLASTIC BAG. PKG SLIP DID IDENTIFY BOTH PARTS AS 894764-11 STRAINERS. ENG MFG & BLUEPRINT REVIEWED, STRAINE	R WITH 'SMALL' ORIFICE IS ACTUALLY A 894764-9 PRINT, & CALLS OUT EACH STRAINER IS TO BE INDIVIDUALLY BAGGED & TAGGED.						4	F			E6WE				 
1996021600686	19960216	00686	WP 	1996	2	16	96ZZZX699 	2	19951227	G	7250	30724123	SUPPORT 								GARRTT	TFE731	TFE731* 	01518	WP 					HP TURBINE	MISIDENTIFIED 	B	L	A	IY2R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	15										C/W SB TFE 731-72-3471, A REWORKED SUPPORT AND SEAL ASSEMBLY MUST BE INSTALLED. THIS REWORKED SUPPORT INCORPORATES A HO	NEYCOMB SEAL AND IS IDENTIFIED AS P/N 3072412-3. BIZJET ORDERED AND RECEIVED FROM ALLIED SIGNAL (THE ENGINE MANUFACTURE	R), A SUPPORT AND FAA FORM 8130-3, BOTH IDENTIFIED AS P/N 3072412-3. HOWEVER, THE PART IS ACTUALLY A 3072412-1. THE DA	SH 1 SUPPORT INCORPORATES AN ABRADABLE SEAL.								4	F			E6WE				 
1996010500580	19960105	00580	CE 	1996	1	5	96ZZZX70 	1	19951204	G	2750	05235372	ROD 			CESSNA	172 	172M 	2072418	CE 										LT FLAP CONTROL	BENT 	G				L				ABORTED APPROACH 				F			FLT CONT AFFECTED 			AP	APPROACH 	1			GL	23	13923					17263039				DURING FIRST TOUCH AND GO LANDING, WHEN FLAPS LOWERED, ABNORMAL CONTROL RESPONSE NOTED. LT FLAP HAS MORE EXTENSION THAN	 RT FLAP. ABORTED AND MADE NEW APROACH TO A LANDING. FOUND FLAP CONTROL SYSTEM HAD A BENT PULLEY BRACKET WHERE ROD (AL	SO BENT) IS ATTACHED. THE BRACKET BENT UNTIL PULLEY WAS CONTACTED CAUSING FLAP PROBLEM.				1	H	7	1 	3O			NT	3A12 					 
1996021600689	19960216	00689	SO 	1996	2	16	96ZZZX702 	1	19951115	G	2437	550690	AMMETER 			PIPER 	PA31 	PA31350 	7103110	SO 										DC INDICATOR	DEFECTIVE 	B	L		APCR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	01										THREE DEFECTIVE AMMETERS RECEIVED. FIRST TWO HAD NEEDLE STUCK (JAMMED BY GAUGE FACE) AT 20 PERCENT LEFT DEFLECTION. TH	IRD UNIT HAD NEEDLE OUT-OF-CALIBRATION (NOT STUCK) 10 PERCENT TO THE RIGHT. ALL MADE BY (NON-PMA'S) AND SOLD THROUGH PI	PER FACTORY.				1	L	7	2 	3O				A20SO 					 
1996021600690	19960216	00690	CE 	1996	2	16	96ZZZX703 	1	19951130	G	3230	571304022	ATTTACH LUG 			CESSNA	421 	421C 	2076016	CE 										NLG ACTUATOR	BROKEN 	B	L		LN3R	A				UNSCHED LANDING 				J			WARNING INDICATION 			CL	CLIMB 	1			WP	07	888HT		3078 			421C0290				PILOT REPORTED 'GEAR UNLOCKED' LIGHT STAYED ON WHEN GEAR SELECTED UP AFTER TAKEOFF. AFTER A FLYBY, TOWER TOLD HIM NOSE 	GEAR WAS HANGING DOWN, IN TRAIL. PILOT SELECTED GEAR DOWN AND ALL 3 GREEN DOWN AND LOCKED LIGHTS CAME ON AS THE UNLOCKE	D LIGHT WENT OUT. A NORMAL LANDING WAS MADE AND ACFT TURNED OVER FOR REPAIR. INSPECTED LANDING GEAR RETRACTION SYSTEM 	AND FOUND BOTH NLG RETRACT ACTUATOR ATTACH LUGS (PN 5713040-22'S) HAD BROKEN WHERE THEY ATTACH TO BOSS OF ACTUATOR. SUS	PECT THIS HAPPENED WHEN GEAR WAS SELECTED UP AFTER TAKEOFF AND ALLOWED THE NOSE GEAR TO TRAIL IN THE SLIPSTREAM.		1	L	7	2 	3O				A7CE 					 
1996021600691	19960216	00691	CE 	1996	2	16	96ZZZX704 	1	19951101	G	2750		BRACKET 			CESSNA	185 	185 	2072802	CE 										FLAP FWD PULLEY	FAILED 	D				K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			GL	15	205NR					18503910				RIGHT FORWARD PULLEY BRACKET FAILED ON ROBERTSON EQUIPPED FLAP CABLE ASSEMBLY. RESULT - ASYMMETRICAL FLAP POSITION DURI	NG FLAP EXTENSION. AIRFRAME TT, 6,000 PLUS HOURS.					1	H	7	1 	3O			NC	3A24 					 
1996010500581	19960105	00581	SO 	1996	1	5	96ZZZX71 	2	19951201	G	8550		QUICK DRAIN 			CESSNA	150 	150M 	2071830	CE 	CONT 	O200 	O200A 	17020	SO 					ENGINE OIL	FAILED 	C				K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			WP	11	66172					15075893	252929			COMPONENTS FELL OUT OF THE OIL QUICK-DRAIN. SUBMITTER SUGGESTS RE-DESIGN SO IT CANNOT HAPPEN AGAIN.						1	H	7	1 	3O	3	O		3A19 	E252				 
1996022300004	19960223	00004	CE 	1996	2	23	96ZZZX711 	1	19951128	G	2410	73383	LOCK PLATE 		055521616 	CESSNA	172 	172M 	2072418	CE 										ALTERNATOR MOUNT	MISSING 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	02	9608H					17266261				INSTALLATION PARTS ARE NOT COMPATIBLE. CESSNA AIR BOX SUPPORT 0555216-16 ATTACHES TO FORWARD ALTERNATOR BRACKET BOLT. T	HIS PREVENTS INSTALLATION OF LYCOMING LOCK PLATE 73383. APPARENTLY, THERE IS NO SB THAT RESOLVES THIS ISSUE. THIS PROB	LEM RELATES TO REPORTS OF ALTERNATOR BRACKET FAILURES AND MAY CONTRIBUTE TO THIS PROBLEM. TYPICAL FIELD SOLUTION IS TO 	DRILL BOLTS FOR SAFETY WIRE INSTEAD OF USING LOCK PLATE. APPLIES TO ALL CESSNA 172 AIRCRAFT, SN 17263459 THROUGH 172675	84, F172, SN F17201235 THROUGH F17201514.		1	H	7	1 	3O			NT	3A12 					 
1996022300005	19960223	00005	SO 	1996	2	23	96ZZZX712 	1	19950801	G	7922	53E19600	VALVE 			GULSTM	AA5 	AA5A 	3960106	SO 										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	23	26122	1922 				AA5A0443				WHEN COMPLYNG WITH TEXTRON/LYCOMING SB 518A, NUT ON TOP OF VALVE LOOSE. HAVE PERFORMED THIS SB FOUR MORE TIMES, ALL VAL	VE NUTS WERE LOOSE, VARIOUS TIMES ON PARTS. RECOMMEND ALL VALVES BE REPLACED WITH NEW NUMBER PER SB518A.					1	L	7	1 	3O				A16EA 					 
1996022300006	19960223	00006	NM 	1996	2	23	96ZZZX713 	1	19950815	G	5711		SPAR CAP 			UNIVAR	415 	415D 	0420306	NM 										WING MAIN SPAR	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25										UPON REMOVAL OF METAL SKIN FOR INSPECTION BEFORE FABRIC RECOVER, FOUND BOTH WINGS HAD EXFOLIATION IN BOTTOM SPAR CAP (MA	IN SPARS). WINGS HAVE BEEN OFF OF AIRCRAFT AND STORED OUTSIDE FOR SEVERAL YEARS.					1	L	7	1 	3O				A787 					 
1996022300007	19960223	00007	NM 	1996	2	23	96ZZZX714 	1	19950815	G	5711		SPAR 			UNIVAR	415 	415C 	0420302	NM 										WING AUX SPAR	KINKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25										UPON INSPECTION PRIOR TO RECOVER, FOUND BOTH WINGS HAD KINK IN AUXILIARY SPAR APPROXIMATELY 8 INCHES OUTBOARD FROM WING 	ATTACH. WINGS WERE METAL COVERED AND STORED OUTSIDE FOR SEVERAL YEARS.					1	L	7	1 	3O				A718 					 
1996022300008	19960223	00008	EA 	1996	2	23	96ZZZX715 	2	19950725	G	7414	M3485	BEARING CAP 	SLICK 	4271 	GULSTM	AA5 	AA5B 	3960105	SO 	LYC 	O360 	O360A4K 	41514	EA 					MAG ROTOR	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	05	74608				91040066	AA5B0282	3295236A			PART NR M-3485 HAS A STEEL BEARING PRESSED INTO AN ALUMINUM BEARING CAP. IT PROVIDES SUPPORT TO THE ROTOR. DURING ROUT	INE 500-HOUR INSPECTION (500 TTSN), A BLACK POWDER-LIKE SUBSTANCE WAS SEEN THROUGHOUT THE MAG. FOUND STEEL BEARING WAS 	MOVING INSIDE THE BEARING CAP, ABRADING ALUMINUM PARTICLES AWAY TO CONTAMINATE THE MAG. SUSPECT EXCESSIVE CLEARANCE AT 	OPERATING TEMP. SUBMITTER RECOMMENDS: 1) TIGHTER PRESS FIT BETWEEN BEARING AND CAP, OR, 2) FLUSH SET SCREWS AROUND E	XTERIOR SIDES OF CAP TO HOLD BEARING IN PLACE, OR, 3) MAKE ALUMINUM CAP OF STEEL TO AVOID DIFFERENT EXPANSION RATES.		1	L	7	1 	3O	3	O		A16EA 	E286				 
1996022300009	19960223	00009	EA 	1996	2	23	96ZZZX716 	2	19950901	G	7414	10382585	BREAKER POINTS 	BENDIX 	1068291018 	PIPER 	PA31 	PA31P 	7103120	SO 	LYC 	O540 	TIO540V2AD 	41532	EA 					MAGNETO	NOT OPENING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	9237Y	32 			5630659	31P8414022				MAGNETO DEFECTIVE. BREAKERS NOT OPENING AT THE CORRECT GAP. ALSO, NOT LUBRICATED. NEED TO LUBRICATE BREAKERS AND SET 	CORRECT GAP. ALSO, FOUND BAD CAPACITOR.					1	L	7	2 	3O	3	O		A8EA 	E14EA				 
1996022300010	19960223	00010	SO 	1996	2	23	96ZZZX717 	2	19950905	G	8530	653426	CYLINDER 			CESSNA	175 	175A 	2072504	CE 	CONT 	O300 	GO300* 	17022	SO 					NR 1 CYLINDER	GUIDE WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	27	6821E	84 				56321				VALVE GUIDE WORN EXCESSIVELY AND WOULD NOT PASS COMPRESSION CHECK. OPERATOR STATED ENGINE NEVER WAS OVERTEMPED AND WAS 	NOT USING AUTO FUEL. VALVE GUIDE WAS REPLACED.					1	H	7	1 	3O	3	O		3A17 	E298				 
1996010500582	19960105	00582	SW 	1996	1	5	96ZZZX72 	1	19951211	G	7922	75944	VALVE 			MOONEY	M20 	M20E 	5870212	SW 										THERMO BYPASS	DEFECTIVE 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	15	7427V	931 			120471	1167				RED TAG IAW SB 518C ABOUT 85 PERCENT OF THESE VALVES INSPECTED HAVE FAILED IAW SB 518C. SUBMITTER RECOMMENDS SB BE MADE	 AN AD.					1	L	7	1 	3O				2A3 					 
1996022300016	19960223	00016	NE 	1996	2	23	96ZZZX723 	2	19951208	G	7210	310703301	BEARING 								PWA 	118 	PW118 		NE 					RGB NR 15	SPALLED 	B			R3AR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05		3023 			FC16572		121346			SPALLED INNER RACE ON RGB NR 15 BEARING.											4	T			E20NE				 
1996022300017	19960223	00017	NE 	1996	2	23	96ZZZX724 	2	19951210	G	7210	310703301	BEARING 								PWA 	118 	PW118 		NE 					RGB NR 15	SPALLED 	B			R3AR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05		5190 			FC8779		115066			INNER BEARING OUTER RACE SPALLED. ENGINE REMOVED FROM SERVICE FOR REMOTE GEARBOX MIO.											4	T			E20NE				 
1996022300018	19960223	00018	NE 	1996	2	23	96ZZZX725 	2	19951205	G	7210	310703301	BEARING 								PWA 	120 	PW120A 		NE 					RGB NR 15	SPALLED 	B			R3AR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05		6453 			68D271		121102			SPALLED OUTER RACE NR 15 BEARING OF RGB.											4	T			E20NE				 
1996022300020	19960223	00020	CE 	1996	2	23	96ZZZX727 	1	19951023	G	7603	98630543	CONTROL CABLE 			CESSNA	172 	172 	2072402	CE 										THROTTLE	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	55250	4800 				17275144				THROTTLE KNOB DISCONNECTED DUE TO CABLE BREAKING INSIDE LINKAGE ASSEMBLY. SUSPECTED FORCEFUL PUSHING IN OF THROTTLE KNO	B AGAINST FIREWALL, OVER TIME, CAUSED CABLE TO BULGE INSIDE PLASTIC SHEATH, EVENTUALLY CAUSING INDIVIDUAL CABLE STRANDS 	TO BREAK THROUGH. STRANDS THEN SEPARATED INDIVIDUALLY. POTENTIAL PROBLEM FOR HIGH TIME THROTTLE CABLES.				1	H	7	1 	3O			NT	3A12 					 
1996022300022	19960223	00022	SO 	1996	2	23	96ZZZX729 	1	19950922	G	5510	83464003	FITTING 			PIPER 	PA46 	PA46310P 	7104605	SO 										STAB RT	RUSTED 	D		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	19	6914T	2384 				468508074				INSPECTION FOUND STAB FITTING RUSTED. PIPER SB 962 DATED SEPTEMBER 29, 1993, DOES NOT COVER RE-INSPECTION OF AREA AFFEC	TED SOON ENOUGH. RUST CANNOT BE SEEN UNDER FITTING AND BETWEEN AIRCRAFT SKIN. DISSIMILAR CORROSION SETS UP CAUSING ADD	ITIONAL DAMAGE. SUBMITTER RECOMMENDS COMPLETE REMOVAL OF FITTINGS AND INSTALLATION OF NEW CADMIUM PLATED FITTINGS AS WE	LL AS TREATMENT OF AIRCRAFT SKIN WITH ZINC CHROMATE PAINT. DINETROL AV8 SHOULD BE RE-APPLIED AFTER INSTALLATION PER SB 	962 INSTRUCTIONS. RECOMMEND VISUAL INSPECTION EACH 500-HOURS OR 1 YEAR USING BORESCOPE AS AID.		1	L	7	1 	3O				A25SO 					 
1996010500583	19960105	00583	CE 	1996	1	5	96ZZZX73 	1	19951204	G	7430	103572001	SWITCH 			CESSNA	150 	150J 	2071820	CE 										IGNITION	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	17	50878					15069617				SWITCH INSTALLED NEW AT 4,000.4 HOURS ON MARCH 12, 1991. REMOVED AT 5,773.28 HOURS, NOVEMBER 30, 1995. TOTAL OPERATING	 TIME 1,772.9. INTERNAL WEAR BETWEEN TUMBLER AND HOUSING CAUSED CONTACTS TO WANDER AS ACTUATED, AND NO CONTACT. TO GRO	UND, ERRATIC, AND SWITCH COULD OCCASIONALLY BE HOT WITH KEY REMOVED.				1	H	7	1 	3O				3A19 					 
1996022300023	19960223	00023	EU 	1996	2	23	96ZZZX730 	1	19951211	G	3520	C3512000	MASK 		17511210 	BEECH 	DH125 	HAWKER800XP 		EU 										PASSENGER CABIN	SPLIT 	B	L	A	YK1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	817H					258279				RUBBER ON PASSENGER OXYGEN MASK SPLITTING AT BASE OF MASK. PROCEEDED TO INVESTIGATE AIRCRAFT IN FACILITY AND FOUND 2 OF	 6 AIRCRAFT WITH THE SAME PROBLEM. BOTH AIRCRAFT CONTAINED 13 PASSENGER OXYGEN MASKS AND EACH HAD TWO DEFECTIVE UNITS. 	 THESE OXYGEN MASKS AND THEIR CONTAINERS ARE BEING INSTALLED UNDER ARKANSAS AEROSPACE STC SA7944SW AND THE AFFECTED AIRC	RAFT ARE UNDERGOING INTERIOR COMPLETION MODIFICATION. THESE MASKS AND CONTAINERS ARE NEW AND HAVE ZERO TIME IN SERVICE.	 THEY HAVE, HOWEVER, BEEN DEPLOYED AND REPACKED AT LEAST 10 TIMES FOR FUNCTIONAL AND FLIGHT TEST.		2	L	7	2 	4F			RT	A3EU 					 
1996022300024	19960223	00024	EU 	1996	2	23	96ZZZX731 	1	19951211	G	3520	C3512000	MASK 			BEECH 	DH125 	HAWKER800XP 		EU 										PASSENGER CABIN	SPLIT 	B	L	A	YK1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	11	667H					258276				RUBBER ON PASSENGER OXYGEN MASK SPLITTING AT BASE OF MASK. PROCEEDED TO INVESTIGATE AIRCRAFT IN FACILITY AND FOUND 2 OF	 6 AIRCRAFT WITH THE SAME PROBLEM. BOTH AIRCRAFT CONTAINED 13 PASSENGER OXYGEN MASKS AND EACH HAD TWO DEFECTIVE UNITS. 	 THESE OXYGEN MASKS AND THEIR CONTAINERS ARE BEING INSTALLED UNDER ARKANSAS AEROSPACE STC SA7944SW AND THE AFFECTED AIRC	RAFT ARE UNDERGOING INTERIOR COMPLETION MODIFICATION. THESE MASKS AND CONTAINERS ARE NEW AND HAVE ZERO TIME IN SERVICE.	 THEY HAVE, HOWEVER, BEEN DEPLOYED AND REPACKED AT LEAST 10 TIMES FOR FUNCTIONAL AND FLIGHT TEST.		2	L	7	2 	4F			RT	A3EU 					 
1996022300120	19960223	00120	NE 	1996	2	23	96ZZZX736 	1	19951214	G	6220	7610708007103	WASHER 			SKRSKY	S76 	S76A 	8143006	NE 										BETWEEN WT/SUP	DEFECTIVE 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	708AL		847 			760277				INSPECTION OF LOWER BIFILAR FOUND 4 OF THE WASHERS WERE BREAKING DOWN. COMPONENT P/N 7610708100041.						1	G	7	2 	3U				H1NE 					 
1996022300122	19960223	00122	GL 	1996	2	23	96ZZZX738 	2	19951229	G	7210	23038182	GEARBOX HOUSING 		23035155 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					TACK GEN. PAD	UNBONDING 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1084Y	7348 	859 		HL23371	45433	CAE860485			UPON DISASSEMBLY AND INSPECTION OF THE GEARBOX PARTS, HOUSING INSPECTION FOUND BRONZE LIFTING FROM TACK GEN. PAD. POSSI	BLE CAUSE FOR BRONZE PLATING UNBONDING IS DUE TO SURFACE CORROSION ON HOUSING AND OIL ACCUMULATION UNDER BRONZE DEBONDS 	PLATING.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1996010500584	19960105	00584	EA 	1996	1	5	96ZZZX74 	2	19951212	G	8510	LW14021	SHAFT 			CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540J3C5 	41532	EA 					PROP IDLER GEAR	MISSING 	H				O				OTHER 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	07	9099C	3297 	1218 			R18200398	L2012540A			THE CESSNA R182 LANDED AND TAXIED ONTO THE PARKING RAMP. THE AIRCRAFT WAS COVERED WITH ENGINE OIL. VISUAL INSPECTION R	EVEALED A HOLE IN THE LOWER FRONT NOSE COWLING, A DAMAGED PROPELLER BLADE AND BENT CYLINDER FINS ON NR 1 CYLINDER. AFTE	R FURTHER INVESTIGATION, THE PROPELLER GOVERNOR IDLER GEAR SHAFT, PN LW-14021, AND PLUG, PN LW-13896, WERE DISCOVERED MI	SSING. THE PLUG THREADS WERE STRIPED AND IT APPEARED THE SET SCREW, PN AN565B1032H5, WAS NEVER ENGAGED IN THE PROP GOVE	RNOR SHAFT.		1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1996022300125	19960223	00125	NE 	1996	2	23	96ZZZX741 	1	19951219	G	6210	7615009100051A	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	DEBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1547N				A08601328	760088				DURING 500-HOUR INSPECTION, FOUND BLADE SKIN DEBONDED. LOWER SURFACE OVER SPAR AT BLADE TIP.						1	G	7	2 	3U				H1NE 					 
1996022300127	19960223	00127	GL 	1996	2	23	96ZZZX743 	2	19950929	G	7210	23035139	HOUSING 		23035139 	BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30 	03013	GL 					GEARBOX	UNBONDED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	346AL	3893 			HL36745	51378	CAE895538			UPON DISASSEMBLY OF THE ENGINE, FOUND BRONZE PLATING UNBONDING AT COMP. BORE. ALSO, FOUND T/M HELICOIL DAMAGED. THE CA	USE FOR BRONZE PLATING UNBONDING IS DUE TO THE SURFACE CORROSION ON HOUSING AND OIL ACCUMULATION. THE CAUSE FOR T/M HEL	ICOIL DAMAGE IS DUE TO METAL FATIGUE IN THE OIL PORTS.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1996022300129	19960223	00129	GL 	1996	2	23	96ZZZX745 	2	19951222	G	7313	47070	NOZZLE BODY 		6890917 	AEROSP	AS355 	AS355F 	8680806	EU 	ALLSN 	250C 	250C20 	03013	GL 					NOZZLE ASSY	CRACKED 	B			ALGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	378E	3922 				5214				DURING INSPECTION OF FUEL NOZZLE AND DISASSEMBLY, REMOVED CORROSION FROM THE BODY ASSY AND FOUND PITTING AND CRACKS ON T	HE NOZZLE BODY ASSY.					1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1996022300383	19960223	00383	CE 	1996	2	23	96ZZZX747 	4	19950121	G	2215		CHAIN 			MTSBSI	MU2 	MU2B40 		CE 										ROLL CONTROL	FOD BIND 	G	L			A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			CL	CLIMB 	1			EA	17	5LC					433SA				PILOT REPORTED INTERMITTENT ELECTRICAL OR AUTOPILOT SERVO PROBLEM ON TAKEOFF WHICH CREATED STIFF ROLL CNTRLS, RETN DEPAR	TURE AIRPORT, LANDED WITHOUT INCIDENT. MX EXTENSIVE INSP OF FLT CNTRL CABLING, CHAIN & SPROCKET & CNTRL WHEEL AREAS, CN	TRL RODS & TORQ TUBE INSP FOR FREEDOM OF MOVEMENT AND/OR CROSSED CABLES. REPAIRS TO AILERON LIMIT SW, RPLD CNTRL A/P SE	RVO BRACKET, MOTOR, NEW CNTRL CABLE. RETN ACFT TO SERVICE, GRD OPER CHKS OK. SUBSEQUENT FLT, SIMILAR BINDING AND/OR ST	IFFNESS & INSP FND (FOD) (A PAN HEAD SCREW, AN526,) FND LODGED BTWN SEGMENTS OF ROLL CNTRL CHAIN & CAUSED BINDING, STIFF	NESS WHEN IN CONTACT WITH ROLL CNTRL SPROCKET. SCREW (FOD) REMOVED, A/C RETN TO SERV, NO RECURRING PROBLEMS.	1	H	7	2 	3T				A10SW 					 
1996010500585	19960105	00585	EA 	1996	1	5	96ZZZX75 	2	19951212	G	8510	LW13896	PLUG 			CESSNA	182 	R182 	2072734	CE 	LYC 	O540 	O540J3C5 	41532	EA 					PROP GOV DRV	MISSING 	H				O				OTHER 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	07	9099C	3297 	1218 			R18200398	L2012540A			THE CESSNA R182 LANDED AND TAXIED ONTO THE PARKING RAMP. THE AIRCRAFT WAS COVERED WITH ENGINE OIL. VISUAL INSPECTION R	EVEALED A HOLE IN THE LOWER FRONT NOSE COWLING, A DAMAGED PROPELLER BLADE AND BENT CYLINDER FINS ON NR 1 CYLINDER. AFTE	R FURTHER INVESTIGATION, THE PROPELLER GOVERNOR IDLER GEAR SHAFT, PN LW-14021, AND PLUG, PN LW-13896, WERE DISCOVERED MI	SSING. THE PLUG THREADS WERE STRIPED AND IT APPEARED THE SET SCREW, PN AN565B1032H5, WAS NEVER ENGAGED IN THE PROP GOVE	RNOR SHAFT.		1	H	7	1 	3O	3	O	RT	3A13 	E295				 
1996022300386	19960223	00386	NE 	1996	2	23	96ZZZX750 	2	19951214	G	7250	569551	VANE 			RKWELL	NA265 	NA26540 	6402608	CE 	PWA 	JT12 	JT12* 	52042	NE 					1ST STAGE TURB	DEBONDING 	B	S		JV2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	306NT	917 				28230	P638155			UNDER NORMAL OPERATING CONDITIONS, THE PROTECTIVE COATING IS DEBONDING FROM THE SURFACE (LEADING EDGE) OF NEW VANES. DE	FECT WAS FOUND BY BORESCOPING THE ENGINE.					2	L	7	2 	4J	4	J		A2WE 	1E9				 
1996022300387	19960223	00387	CE 	1996	2	23	96ZZZX751 	1	19951227	G	2720		ACTUATOR 			CESSNA	650 	650 	2076802	CE 										RUDDER BIAS	WATER CONTAM 	B	L		KL1R	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			F			FLT CONT AFFECTED 			TO	TAKEOFF 	1			GL	25	175J					6500168				ACFT FLEW 3 LEGS, NO PROBLEMS. ON 4TH TAKEOFF, AT 100 KNOTS, RUDDERS LOCKED. T/O ABORTED. DURING TAXI BACK, RUDDER & 	NOSE STEERING WORKING NORMALLY. RUDDER BIAS TESTED NORMAL. CNTRL LOCK RELEASED. T/O ATTEMPED & AT 100-105 KNOTS, RUDD	ER CNTRLS LOCKED AGAIN. T/O ABORTED & ACFT RETND. VISUAL INSP MADE, NO PROBLEM FND. A 3RD T/O WITH RUDDER BIAS OFF WA	S ORDINARY WITH EVERYTHING WORKING NORMALLY. ACFT FLOWN HOME WITH NO FURTHER PROBLEMS. RUDDER BIAS ACT DISASSEMBLED AN	D INSP. APPROX 1 TEASPOON OF WATER REMOVED. ACT INSP IAW CESCARD NR A272202 & B272202. RUDDER BIAS SYS INSP IAW CESCA	RD NR 272002. RUDDER BIAS THERMOSTAT TESTED OK. LINES TO RUDDER BIAS ACT PURGED. ACT REINSTALLED, T/O & LDNG OK.	2	L	7	2 	4F				A9NM 					 
1996022300388	19960223	00388	CE 	1996	2	23	96ZZZX752 	1	19950705	G	7810	MS20500428	NUT 			BEECH 	300 	300BEECH 	1152930	CE 										EXH STACK ATTACH	DEFECTIVE 	D	L			K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CE	03	7202Y	2586 				FA12				UPON A ROUTINE ENGINE COWLING REMOVAL, RT ENG, AN EXHAUST STACK ATTACH NUT, WASHER AND BOLT WERE FND LOOSE IN COWLING. F	URTHER INSP SHOWED 50 PERCENT OF ALL INBD AND OTBD EXHAUST STACK ATTACHMENT NUTS FREE RUNNING AND A TOTAL OF 90 PERCENT 	HAD UNSATISFACTORY SELF-LOCKING FRICTION. EXH STACKS HAD BEEN REMOVED/RE-INSTALLED 7 TIMES SINCE FACTORY NEW AND NUTS W	ERE ORIGINAL. SUSPECT CAUSE COULD BE THERMAL CYCLING TO AFFECT NUT LOCKING FEATURE. RECOMMEND BACKING OFF NUTS TO CHEC	K LOCKING FEATURE AND TORQUING TO SPECIFICATION. ALSO, CONSIDER REPLACING NUT ANY TIME ONE IS REMOVED.		2	L	7	2 	4T				A24CE 					 
1996022300389	19960223	00389	SO 	1996	2	23	96ZZZX753 	1	19951220	G	3230	25720000	TRANSMISSION 			PIPER 	PA24 	PA24 	7102402	SO 										MLG	CRACKED 	B		A	OMKR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	03	7249P	2552 				242425				THE ALUMINUM CASTING OF THE MLG TRANSMISSION (PN 25720-002) WAS CRACKED IN 4 PLACES AND VERY CLOSE TO COMPLETE FAILURE. 	 FAILURE OF THE HOUSING WOULD POSSIBLY CAUSE THE LANDING GEAR TO LOCK IN ANY POSITION. THE CRACKS WERE DISCOVERED DURIN	G A GEAR RETRACTION TEST AFTER REPLACEMENT OF SEVERELY WORN GEAR DOOR HINGES. SUSPECT CAUSE OF TRANSMISSION CASTING TO 	FAIL DUE TO INCORRECT RIGGING OF GEAR SYSTEM CREATING OVERTORQUE.			1	L	7	1 	3O				1A15 					 
1996022300393	19960223	00393	EA 	1996	2	23	96ZZZX757 	1	19951203	G	7830		THRUST REVERSER 			CNDAIR	CL600 	CL6002B19 		EA 										BARREL SKIN	CRACKED 	B			EZ1R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	11	5100X				009	7008				WHILE PERFORMING A BLOCKER DOOR REPAIR, NOTICED THE INNER BARREL AT THE 6 O'CLOCK POSITION HAD A 6-INCH LONG CRACK IN TH	E SHAPE OF THE LETTER 'L'. CONSIDERING THE PRELOADING PROBLEM ON THE BLOCKER DOOR AND APPARENT MISALIGNMENT OF THE BLOC	KER DOOR MOUNTS AT PRODUCTION, SUBMITTER STATED THIS COULD BE THE ROOT CAUSE OF THE CRACK. REPLACED T/R WITH RENTAL UNI	T. FUNCTIONALLY CHECKED THRUST REVERSER AND RETURNED AIRCRAFT TO SERVICE.			2	L	7	2 	4F			RT	A21EA 					 
1996022300395	19960223	00395	CE 	1996	2	23	96ZZZX759 	1	19950918	G	2133	45AS63019007	REGULATOR VALVE 			BEECH 	MU300 	400BEECH 		CE 										RT CABIN PRESS	FAILED 	B			OG5R	O				OTHER 				J			WARNING INDICATION 			TO	TAKEOFF 	1			GL	21	3196N	3 			0632A	RK96				DURING TAKEOFF ROLL, VALVE PRESSURIZATION SYSTEM WENT INTO EMERGENCY PRESSURIZATION. VALVE HAD BEEN REPLACED 2.7 HOURS 	EARLIER FOR SAME PROBLEM. REPLACED BOTH LEFT AND RIGHT VALVES PER BEECH. AIRCRAFT TOTAL TIME 652.2 HOURS. OTHER AIRCR	AFT IN FLEET HAS TOTAL TIME OF 840.2 HOURS TO DATE WITH NO SIMILAR PROBLEMS.				2	H	7	2 	4F			RT	A16SW 					 
1996010500586	19960105	00586	SO 	1996	1	5	96ZZZX76 	2	19951128	G	8520	24878	BOLTS 			CESSNA	414 	414A 	2075907	CE 	CONT 	O520 	TSIO520NB 	17040	SO 					CASE HALF	DETACHED 	B			ESER	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SO	11	747JB	215 				414A1006	L800588			UPON REMOVAL OF THE OIL SUMP TO REPLACE A LEAKING GASKET, FOUND 2 CASE HALF BOLTS AND ASSOCIATED HARDWARE (NUTS AND WASH	ERS) HAD COME OUT AND WERE LAYING IN THE SUMP. INSPECTION OF THE CASE HALF BOLT HOLES SHOWED NO SIGN OF FORGING ON THES	E 2 BOLTS. IT IS THEORIZED THEY WERE INSTALLED BY HAND DURING ENGINE ASSEMBLY, BUT FAILED TO BE TORQUED. THUS, THEY LO	OSENED AND FELL INTO THE SUMP.			1	L	7	2 	3O	3	O		A7CE 	E8CE				 
1996022300399	19960223	00399	NE 	1996	2	23	96ZZZX763 	2	19951214	G	7250	569551	VANE 			RKWELL	NA265 	NA26540 	6402608	CE 	PWA 	JT12 	JT12* 	52042	NE 					1ST STG TURBINE	DEBONDED 	B			JV2R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	309NT	397 				28261	P637109			UNDER NORMAL OPERATING CONDITIONS, THE PROTECTIVE COATING IS DEBONDING FROM THE SURFACE OF NEW VANES. DEFECT WAS FOUND 	BY BORESCOPING THE ENGINE.					2	L	7	2 	4J	4	J		A2WE 	1E9				 
1996010500587	19960105	00587		1996	1	5	96ZZZX77 	4	19951214	G	2562	BP1026	BATTERY 	COMMUNCOMP 	CIR112 	PIPER 	PA28 	PA28161 	7102803	SO 										ELT	LEAKING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	38581				19724	287716270				WHITE CORROSION LEAKAGE WAS FOUND ON BATTERY CASE WHILE CHANGING BATTERY. ELT WAS NOT DAMAGED. MERL BATTERY, EXP DATE 	12-95, PN BP-1026, 2.5 POUNDS.					1	L	7	1 	3O				2A13 					 
1996022300683	19960223	00683	CE 	1996	2	23	96ZZZX777 	1	19951212	G	3230	12802311	SPRING 			CESSNA	210 	T210N 	2073456	CE 										NLG DOWNLOCK	BENT 	D		A		K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	07	656MC	30 				21063111				NLG DOWNLOCK PARTS A NEW SPRING, GUIDE, PN 9882024-1, SHIELD, PN 1280207, WERE PURCHASED NEW FROM CESSNA. AFTER ONLY 30	 HRS OF OPERATION, A VISUAL INSPECTION OF SPRING SHOWED SPRING AND SPRING GUIDE WERE COLLAPSED AND BENT ABOUT 30 DEGREES	. REPORTED THE VENDOR HAD SOLD SPRINGS THAT WERE .50 INCH TOO LONG. ADVISED TO CHECK COIL OUTSIDE DIAMETER TO .080 INC	H. THIS DIMENSION WAS OK EVEN ON WRONG PART. NEW SPRING, SAME PART NUMBER, WAS REORDERED. IT WAS .50 INCH SHORTER THA	N BENT SPRING. THIS COULD HAVE LET THE NOSE GEAR COLLAPSE. SUBMITTER STATED NEED SB ON SPRING.		1	H	7	1 	3O				3A21 					 
1996010500588	19960105	00588		1996	1	5	96ZZZX78 	4	19951214	G	2562	BP1040	BATTERY 	MARTECH 	EB2BCD 	BEECH 	23 	19A 	1151214	CE 										ELT	LEAKING 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	01	6982Q				3699	MB405				BATTERY LEAKAGE HAD CORRODED ELT INTERNALLY. BOTH WERE SENT TO MERL FOR WARRANTY EVALUATION.						1	L	7	1 	3O				A1CE 					 
1996022300687	19960223	00687	CE 	1996	2	23	96ZZZX781 	1	19951228	G	5553	04320049	BRACKET 			CESSNA	150 	152 	2071835	CE 										V-FIN	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	49276					15281217				BRACKET FOUND CRACKED DURING REPAIRS TO HORIZONTAL STABILIZER FOLLOWING GROUND COLLISION. CRACKS IN WELDED AREA EXISTED	 BEFORE COLLISION. DISSIMILAR METAL CORROSION ALSO EXISTED BETWEEN STEEL BRACKET AND ALUMINUM SKINS.					1	H	7	1 	3O			NT	3A19 					 
1996022300688	19960223	00688	SO 	1996	2	23	96ZZZX782 	1	19951116	G	5210	46624003	U-CHANNEL 			PIPER 	PA31T 	PA31T 	7103124	SO 										CABIN DOOR	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	926LD	2800 				31T7820047				PILOT REPORTED THE CABIN DOOR WOULD NOT LATCH. INSPECTION OF THE DOOR FOUND THE CABIN DOOR STRUCTURE U-CHANNEL NEAR THE	 HINGE WAS CRACKED. REPLACED THE U-CHANNEL, Z-CHANNEL, AND HINGE. DOOR MAY HAVE BEEN OVERSTRESSED BY MORE THAN ONE PER	SON ON DOOR AT A TIME. SUBMITTER SUGGESTS PLACARD DOOR FOR ENTRANCE BY ONE PERSON ON STEP AT A TIME, AND USING A SUPPOR	T FOR THE DOOR WHEN POSSIBLE, ESPECIALLY WHEN IN FOR MAINTENANCE.			1	L	7	2 	3T				A8EA 					 
1996022300690	19960223	00690	SO 	1996	2	23	96ZZZX784 	1	19950918	G	3231	86263005	BRACKET 			PIPER 	PA44 	PA44180 	7104402	SO 										NLG RT DOOR	CRACKED 	B			OG5R	O				OTHER 				J			WARNING INDICATION 			AP	APPROACH 	1			GL	21	855ND	3235 				4495009				NOSE GEAR FAILED TO EXTEND FOR LANDING. GEAR CYCLED AND GEAR INDICATED DOWN. FOUND ROD END BRACKET ON RIGHT NOSE GEAR 	DOOR BROKEN OFF AT ROD END ATTACH POINT/HOLE. INSTALLED NEW BRACKET. SUBMITTER STATED THIS IS SECOND OCCURRENCE IN FLE	ET OF 9 AIRCRAFT. OTHER FAILURE AIRCRAFT HAD TT OF 3,640.4 HOURS.				1	L	7	2 	3O				A19S0 					 
1996010500589	19960105	00589	CE 	1996	1	5	96ZZZX79 	1	19951107	G	5711	052302012	ANGLE 			CESSNA	172 	172N 	2072434	CE 										RT SPAR CAP	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	7598D					1727928				SPAR CAP ANGLE EXHIBITED SEVERE INNER CORROSION IN 2 LOCATIONS AND MODERATE INTERGRANULAR CORROSION IN SEVEREAL OTHER LO	CATIONS. CORROSION AFFECTED THE DOUBLER PLATE WHERE THE POINT OF CORROSION CONTACTED.					1	H	7	1 	3O			NT	3A12 					 
1996022300696	19960223	00696	SO 	1996	2	23	96ZZZX790 	1	19950921	G	5720		STIFFENER 			PIPER 	PA28 	PA28161 	7102803	SO 										WING 1ST-2ND RIB	CRACKED 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	124ND	5663 				2841137				DURING INSPECTION, STIFFENERS BETWEEN 1ST AND 2ND RIBS IN BOTH WINGS WERE FOUND CRACKED ACROSS 2 END RIVETS ON INBOARD A	ND OUTBOARD ENDS OF STRINGERS. SUBMITTER STATED VARIOUS STIFFENERS HAVE BEEN FOUND ON 5 AIRCRAFT TO-DATE. TOTAL STIFFE	NERS REPLACED IS 11. AIRCRAFT TOTAL TIMES RANGE FROM 3,503 HOURS TO 6,196 HOURS. INSPECTION OF STRINGERS MUST BE DONE 	BY FUEL TANK REMOVAL TO GET BEST INSPECTION RESULTS. REPORTED STIFFENER P/N'S 62086-, AND 62087-.			1	L	7	1 	3O				2A13 					 
1996022300697	19960223	00697	SO 	1996	2	23	96ZZZX791 	1	19950919	G	2710	62701127	CONTROL CABLE 			PIPER 	PA34 	PA34220 	 	SO 										AIL FWD WS 70.5	WORN 	B			ECPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	9218N	3324 				3448014				LEFT AND RIGHT FORWARD AILERON CABLES ARE BEING WORN BY THE PULLEY AT WS 70.5. THE PULLEY AT THIS STATION CARRIES NO LO	AD FROM THE CABLE TENSION. IT APPEARS THAT IN-FLIGHT VIBRATION IS CUTTING THE CABLE IN HALF. NO PULLEYS HAVE BEEN FOUN	D FROZEN OR DAMAGED. OPERATOR HAS FLEET OF 5 AND PROBLEM IS APPARENT IN ALL.				1	L	7	2 	3O			 	A7SO 					 
1996022300698	19960223	00698	SO 	1996	2	23	96ZZZX792 	1	19951013	G	5730	6206101	SKIN 			PIPER 	PA28 	PA28161 	7102803	SO 										RT WING AFT	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	4295N	5580 				288316051				THE SKIN RIVETED TO THE UNDERSIDE OF THE WING WALK PANELS FOR RE-ENFORCEMENT WERE FOUND CRACKED. THE CRACKS RAN FORE AN	D AFT. THE CRACKS WERE DISCOVERED AT 100-HOUR INSPECTION AFTER NOTING WEAKNESS IN THE WING WALK AREA WITH WEIGHT ON THI	S AREA. THE AIRCRAFT IS USED FOR FLIGHT TRAINING. SUSPECT CAUSE WAS AGE, TOTAL TIME ON PART, AND ENVIRONMENT WHICH AIR	CRAFT IS USED. SUBMITTER RECOMMENDS A VERY THOROUGH INSPECTION ANNUALLY OR VERY 100 HOURS FOR AIRCRAFT USED IN FLIGHT T	RAINING.		1	L	7	1 	3O				2A13 					 
1996022300699	19960223	00699	SO 	1996	2	23	96ZZZX793 	1	19951013	G	5730	6206102	SKIN 			PIPER 	PA28 	PA28161 	7102803	SO 										RT WING FWD	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99	4295N	5580 				288316051				THE SKIN RIVETED TO THE UNDERSIDE OF THE WING WALK PANELS FOR RE-ENFORCEMENT WERE FOUND CRACKED. THE CRACKS RAN FORE AN	D AFT. THE CRACKS WERE DISCOVERED AT 100-HOUR INSPECTION AFTER NOTING WEAKNESS IN THE WING WALK AREA WITH WEIGHT ON THI	S AREA. THE AIRCRAFT IS USED FOR FLIGHT TRAINING. SUSPECT CAUSE WAS AGE, TOTAL TIME ON PART, AND ENVIRONMENT WHICH AIR	CRAFT IS USED. SUBMITTER RECOMMENDS A VERY THOROUGH INSPECTION ANNUALLY OR VERY 100 HOURS FOR AIRCRAFT USED IN FLIGHT T	RAINING.		1	L	7	1 	3O				2A13 					 
1996022300700	19960223	00700	SO 	1996	2	23	96ZZZX794 	1	19950919	G	2710	62701127	CONTROL CABLE 			PIPER 	PA34 	PA34220 	 	SO 										AIL FWD WS 70.5	WORN 	B			ECPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	9217F	3393 				3448013				LEFT AND RIGHT FORWARD AILERON CABLES ARE BEING WORN BY THE PULLEY AT WS 70.5. THE PULLEY AT THIS STATION CARRIES NO LO	AD FROM THE CABLE TENSION. IT APPEARS THAT IN-FLIGHT VIBRATION IS CUTTING THE CABLE IN HALF. NO PULLEYS HAVE BEEN FOUN	D FROZEN OR DAMAGED. OPERATOR HAS FLEET OF 5 AND PROBLEM IS APPARENT IN ALL.				1	L	7	2 	3O			 	A7SO 					 
1996022300701	19960223	00701	SO 	1996	2	23	96ZZZX795 	1	19950919	G	2710	62701127	CONTROL CABLE 			PIPER 	PA34 	PA34220 	 	SO 										AIL FWD WS 70.5	WORN 	B			ECPR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15	9215N	3224 				3448011				LEFT AND RIGHT FORWARD AILERON CABLES ARE BEING WORN BY THE PULLEY AT WS 70.5. THE PULLEY AT THIS STATION CARRIES NO LO	AD FROM THE CABLE TENSION. IT APPEARS THAT IN-FLIGHT VIBRATION IS CUTTING THE CABLE IN HALF. NO PULLEYS HAVE BEEN FOUN	D FROZEN OR DAMAGED. OPERATOR HAS FLEET OF 5 AND PROBLEM IS APPARENT IN ALL.				1	L	7	2 	3O			 	A7SO 					 
1996022300702	19960223	00702	EA 	1996	2	23	96ZZZX796 	2	19951212	G	8520	SL75060	BOLT 			PIPER 	PA28 	PA28R200 	7102811	SO 	LYC 	O360 	IO360C1C 	41514	EA 					NR 3 CYL CON ROD	FAILED 	D				O				OTHER 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		NR	NOT REPORTED 	1			SW	05	16460	472 				28R7335151	L1057151A			DURING THROTTLE MOVEMENT FORWARD TO FULL POWER, ENGINE ABRUPTYLY BEGAN TO RUN EXTREMELY ROUGH. NO COMPRESSION ON ONE CY	LINDER. FOUND NR 3 CYLINDER CONNECTING ROD BROKEN NEAR CRANKSHAFT JOURNAL AREA. ONE CONNECTING ROD BOLT INTACT, THE OT	HER BROKEN. EXTENSIVE DAMAGE TO LOWER CRANKCASE ABOVE OIL SUMP FROM CONTACT WITH CONNECTING ROD.				1	L	7	1 	3O	3	O		2A13 	1E10				 
1996010500590	19960105	00590	CE 	1996	1	5	96ZZZX80 	1	19951107	G	5711	052302012	ANGLE 			CESSNA	172 	172N 	2072434	CE 										RT SPAR CAP	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	6390J					17273856				SPAR CAP ANGLE EXHIBITED INTERGRANULAR CORROSION IN SEVERAL LOCATIONS ALONG ITS LENGTH AND AFFECTED THE DOUBLER PLATE AT	 THE POINTS WHERE THE CORROSION CONTACTED. SUBMITTER STATED THIS INTERGRANULAR CORROSION IS DISPLAYING SIGNS OF PRESENC	E IN THE LT SPAR CAP AS WELL.				1	H	7	1 	3O			NT	3A12 					 
1996022300707	19960223	00707	GL 	1996	2	23	96ZZZX801 	3	19950810	G	6114	D4883C55	HUB 													MCAULY	2AF34C	2AF34C55 	GL 	NR 1 BLD SOCKET	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								703398		DURING PROP INSPECTION, HUB FOUND CRACKED IN BLADE SOCKET NR 1. HUB HAS BEEN SCRAPPED.																5	C	P5EA	 
1996022300708	19960223	00708	NE 	1996	2	23	96ZZZX802 	3	19951030	G	6114	D5170	PISTON ROD 													MCAULY	4HFR34	4HFR34C652 	NE 	PROP	HEAD LOOSE 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								881168		UPON PROP INSPECTION, HEAD FOUND BROKEN LOOSE FROM PISTON ROD ASSY. PISTON ROD ASSY HAS BEEN SCRAPPED.																6	C	3PNE	 
1996010500591	19960105	00591	CE 	1996	1	5	96ZZZX81 	1	19951107	G	5711	05233151	PLATE 			CESSNA	172 	172N 	2072434	CE 										RT SPAR DOUBLER	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	21	6390J					17273856				SPAR CAP ANGLE EXHIBITED INTERGRANULAR CORROSION IN SEVERAL LOCATIONS ALONG ITS LENGTH AND AFFECTED THE DOUBLER PLATE AT	 THE POINTS WHERE THE CORROSION CONTACTED. SUBMITTER STATED THIS INTERGRANULAR CORROSION IS DISPLAYING SIGNS OF PRESENC	E IN THE LT SPAR CAP AS WELL.				1	H	7	1 	3O			NT	3A12 					 
1996022300716	19960223	00716	CE 	1996	2	23	96ZZZX810 	1	19951221	G	3246	40289	WHEEL 	PARKERHANFIN		BEECH 	200 	200BEECH 	1152920	CE 										MLG	HEAVY 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	03	500GC					BB735				AIRCRAFT IS EQUPPED WITH PARKER HANIFAN MAIN WHEEL AND BRAKE CONVERSION STC SA646GL. PARKER HANIFAN HAS SUPERSEDED ORIG	INAL WHEEL, PN 40-172, TO PN 40-289. NEW WHEEL WEIGHS 3 POUNDS MORE THAN ORIGINAL. PARKER HANIFAN SHOULD MAKE OPERATOR	S AWARE OF THIS.				1	L	7	2 	4T				A24CE 					 
1996022300717	19960223	00717	CE 	1996	2	23	96ZZZX811 	1	19951212	G	3250	57423081	BELLCRANK 			CESSNA	441 	441 	2076020	CE 										NLG STEERING	TWISTED 	D				K				NONE 				O			OTHER 			TX	TAXI/GRND HDL 	1			SW	03	2628M	1881 				4410151				CREW REPORTED LACK OF STEERING AUTHORITY TO THE LEFT. INSPECTION SHOWED STEERING BELLCRANK BENT AND TWISTED. STEERING 	LIMIT 'TATTLE TALE' FITTING WAS INTACT. PILOT REPORTED IT GOT WORSE OVER A PERIOD OF TIME. FINALLY, COULD NOT HOLD A H	EADING ON THE TAXIWAY.				1	L	7	2 	3T			RT	A28CE 					 
1996022300720	19960223	00720	WP 	1996	2	23	96ZZZX814 	2	19951207	G	7250	31038391	ROTATING SEAL 		31033152 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					1ST STAGE TURB	FLANGE CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		9710 			9233151419		P70029			DURING SCHEDULED HOT SECTION INSPECTION, FOUND PART CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE	-LIMIT = 20,000 CYCLES. THIS IS THE 23RD MALFUNCTION/DEFECT REPORT SUBMITTED BY THIS REPAIR STATION ON THIS TOPIC.										4	T			E4WE				 
1996022300721	19960223	00721		1996	2	23	96ZZZX815 	4	19950922	G	2210	600591993	ACCLEROMETER 	GULTON 		CNDAIR	CL600 	CL6001A11 	1900302	EA 										AUTOFLIGHT	FAILED 	B			SH5R	K				NONE 				W			INADEQUATE Q C 			NR	NOT REPORTED 	1			NE	03	1045X				18402	1038				UNIT STICKS AT 6.0 VDC RIGHT OUT OF STOCK. C/W CANADAIR SB 600-0440 TO INSTALL THE DASH 3, MORE RELIABLE ACCELEROMETER,	 AND STILL IT FAILS RIGHT AFTER INSTALLATION.					2	L	7	2 	4F			RT	A21EA 					 
1996022300722	19960223	00722		1996	2	23	96ZZZX816 	4	19950922	G	2210	600591997	ACCELEROMETER 	GULTON 		CNDAIR	CL600 	CL6001A11 	1900302	EA 										AUTOFLIGHT	STICKS 	B			SH5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NE	03	1045X				1348	1038				UNIT STICKS WHEN POWERED ON AND OFF. THIS WAS THE SAME CONDITION ON THE LAST OVERHAUL OF THIS UNIT. THE UNIT FAILED OU	T OF STOCK.					2	L	7	2 	4F			RT	A21EA 					 
1996022300723	19960223	00723	CE 	1996	2	23	96ZZZX817 	1	19951218	G	3260	MS3126F1210P	CONNECTOR 		11238002233 	BEECH 	1900 	1900C 	1154161	CE 										NLG ACTUATOR	CORRODED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	13	521M	9100 			64	UB68				CONNECTOR PLUG IS LOCATED UPPER LEFT SIDE OF NOSE WHEELWELL AND IS EXPOSED TO THE ELEMENTS AND A GOOD DEAL OF HARNESS MO	TION. PINS WERE CORRODED AND WORN CAUSING INTERMITTENT NOSE GEAR UNSAFE INDICATIONS. SUBMITTER RECOMMENDS CLOSER INSPE	CTION DURING BEECH DETAIL INSPECTIONS WHICH ALREADY DIRECT TO CHECK CONNECTORS FOR SECURITY AND CONDITION AND WHEN CONDI	TION IS QUESTIONABLE THEN DISCONNECT, INSPECT AND CLEAN. ENSURE BACKSHELL IS SEALED WELL.			2	L	7	2 	4T			RT	A24CE 					 
1996010500592	19960105	00592	CE 	1996	1	5	96ZZZX82 	1	19951211	G	7810	265401842	EXHAUST DUCT 			CESSNA	208 	208B 	2073701	CE 										OUTBOARD SEAM	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			AL	01	1040N	180 				208B0336				CRACK ALONG OUTBOARD SEAM OF EXHAUST DUCT DISCOVERED DURING PRE-FLIGHT. PART REMOVED AND REPLACED BY LOANER WHILE BEING	 WELDED AND REPAIRED.					1	H	7	1 	3T				A37CE 					 
1996030100221	19960301	00221	SO 	1996	3	1	96ZZZX822 	2	19951201	G	7314	634053	VAPOR SEPARATOR 		64621216 	BEECH 	33 	F33A 	1151425	CE 	CONT 	O520 	IO520BB 	17032	SO 					FUEL PUMP	FOD JAMMED PUMP 	B	L		WTXR	A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			NM	11	5587K	1720 	620 		H139202BR	CE1392	285675R			CUSTOMER REPORTED ENG DRIVEN FUEL PUMP FAILED AT 600 FEET AGL AFTER T/O. PILOT ACTIVATED ELEC PUMP AND SAFELY LANDED AI	RPLANE. PUMP SENT TO THIS FACILITY FOR DISASSEMBLY AND INSP. WHEN PUMP DISASSEMBLED, 2 SMALL FLAKES OF ALUM FOUND JAMM	ED IN VANES OF PUMP. THIS CAUSED PUMP TO SEIZE AND DRIVE COUPLING TO SHEAR. VAPOR SEPARATOR OF PUMP FND TO BE SOURCE O	F ALUM. A SHARP MACHINED EDGE INSIDE HOUSING OF SEPARATOR HAD LOST MATERIAL INTO VANES OF PUMP. CASTING OF VAPOR SEPAR	ATOR MAY HAVE BEEN POOR QUALITY THAT ALLOWED THIS TO HAPPEN. A POSSIBLE MEASURE TO PREVENT THIS SITUATION FROM OCCURRIN	G WOULD BE TO ROUND THE SHARP EDGE IN VAPOR SEPARATOR DURING OVERHAUL.	1	L	7	1 	3O	3	O		3A15 	E5CE				 
1996030100222	19960301	00222	GL 	1996	3	1	96ZZZX823 	3	19950815	G	6114	C6608C205	HUB 			CESSNA	188 	188CESSNA 	2073002	CE 						MCAULY	2A34C	B2A34C205 	GL 	PILOT HOLE	CRACKED 	B			ME4D	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	15								890657		UPON PROPELLER INSPECTION, HUB FOUND CRACKED IN PILOT HOLE. HUB HAS BEEN SCRAPPED.						1	L	7	1 	3O				A9CE 		5	C	P3EA	 
1996010500593	19960105	00593	CE 	1996	1	5	96ZZZX83 	1	19950618	G	2916	105931S	RESERVOIR 			CESSNA	177 	177RG 	2073709	CE 										HYD SYSTEM	LOW FLUID 	G				A				UNSCHED LANDING 				J			WARNING INDICATION 			AP	APPROACH 	1			GL	03	7637V	4445 				177RG0898				ON APPROACH INTO AIRCRAFT, WAS UNABLE TO EXTEND OR RETRACT LANDING GEAR. AIRCRAFT MADE EMERGENCY LANDING CAUSING GEAR T	O COLLAPSE. FURTHER INVESTIGATION OF THE INCIDENT SHOWED THERE HAD BEEN MAINTENANCE PERFORMED ON LANDING GEAR SYSTEM BY	 PERSONS UNKNOWN. DURING INVESTIGATION, HYDRAULIC RESERVOIRS WERE FOUND LOW AND NOT SERVICED CORRECTLY CAUSING LANDING 	GEAR TO MALFUNCTION			1	H	7	1 	3O				A20CE 					 
1996030100479	19960301	00479	CE 	1996	3	1	96ZZZX838 	1	19951027	G	2434	30B10719A	GENERATOR 	BENDIX 		LEAR 	55 	55LEAR 	5170702	CE 										DC SYS	FAILED 	B			DINR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	127GT		13 		2632	067				REMOVED, S/N 2632, GENERATOR ON 10-17-95 DUE TO FAILURE (SHORTED BETWEEN 'D' AND 'E' POSTS). IT HAD ONLY 13.1 HOURS SIN	CE OVERHAUL. INSTALLED ANOTHER OVERHAULED GENERATOR, S/N 1333.					2	L	7	2 	4F				A10CE 					 
1996030100480	19960301	00480	NE 	1996	3	1	96ZZZX839 	2	19951123	G	7250	3037313	PT DISK 			BEECH 	1900 	1900D 	1154162	CE 	PWA 	PT6 	PT6A67D 		NE 					2ND STAGE	BLADE FAILURE 	B			MASR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	65YV	5484 			69A494	UE65	114165			THE POWER SECTION WAS HARD TO ROTATE WHEN BROUGHT INTO TEAR-DOWN INVESTIGATION AREA. PRE-INSPECTION REVEALED THE NR 2 S	TAGE 4 PT BLADES HAD FRACTURED AT THE ROOT, 6 ARE FRACTURED FROM .200 INCH TO .500 INCH IN FROM THE ROOT, THE REMAINING 	BLADES ARE FRACTURED AT THE BLADE SHROUD AREA. THE 2ND STAGE DISK AND BLADES WERE SENT TO PCW FOR INVESTIGATION AND ARE	 THE PRIMARY SUSPECT FOR THE FAILURE.			2	L	7	2 	4T	4	T	RT	A24CE 	E26NE				 
1996010500594	19960105	00594	CE 	1996	1	5	96ZZZX84 	1	19951204	G	2436	C6110040101	REGULATOR 			CESSNA	172 	172N 	2072434	CE 										DC SYSTEM	WIRE DETACHED 	D				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			WP	07	737LD	4793 			00411344	17270620				FIELD WIRE SEPARATED FROM CONNECTOR PLUG ON THE ALTERNATOR CONTROL UNIT. SUSPECT CAUSE - VIBRATION AND FATIGUE ON WIRE.						1	H	7	1 	3O			NT	3A12 					 
1996030100485	19960301	00485	CE 	1996	3	1	96ZZZX844 	1	19951027	G	2434	30B10719A	GENERATOR 			LEAR 	55 	55LEAR 	5170702	CE 										DC SYSTEM	FAILED 	B	L		DINR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	127GT		593 			067				REMOVED GENERATOR, S/N 1187, DUE TO WHINE HEARD OVER SPEAKERS ON 9-27-95. IT HAD 593.3 HOURS SINCE OVERHAUL. INSTALLED	 GENERATOR, S/N 2632, 9-27-95 WITH ZERO HOURS SINCE OVERHAUL.					2	L	7	2 	4F				A10CE 					 
1996010500595	19960105	00595	SO 	1996	1	5	96ZZZX85 	2	19951123	G	8520	632941F	CONNECTING ROD 			CESSNA	185 	A185E 	2072818	CE 	CONT 	O520 	IO520D 	17032	SO 					NR 6 PISTON	BROKE 	G				K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SO	17	8H					1851172	17406870D12			ENGINE'S NR 6 ROD BROKE. PISTON PIN BOSS WAS GONE.						1	H	7	1 	3O	3	O		3A24 	E5CE				 
1996030100500	19960301	00500	SO 	1996	3	1	96ZZZX859 	1	19951025	G	3213	78738003	STRUT STUB AXLE 			PIPER 	PA28 	PA28161 	7102803	SO 										RT MLG	EAR CRACKED 	B		A	OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	110ND	6116 				2841134				DURING PHASE 3 INSPECTION, FOUND RT GEAR STUB AXLE TORQUE LINK ATTACH OUTBOARD EAR CRACKED ON INNER RADIUS APPROXIMATELY	 ONE-HALF LENGTH OF EAR FROM TOP OF EAR. (THIS IS LOWER ATTACH POINT FOR TORQUE LINKS.) SUBMITTER STATED THIS IS THIRD	 OCCURRENCE OF LOWER EAR CRACKING. THIS OPERATOR HAS CHANGED APPROXIMATELY 30 STRUT HOUSINGS FOR UPPER ATTACH EAR CRACK	S. (FLEET OF 33 AIRCRAFT.)			1	L	7	1 	3O				2A13 					 
1996010500596	19960105	00596	CE 	1996	1	5	96ZZZX86 	1	19950904	G	7921	6526601	COOLER 			CESSNA	206 	U206G 	2073356	CE 										ENGINE OIL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	4672U	144 				U20605046				OIL COOLER CORE WAS FOUND LEAKING.						1	H	7	1 	3O				A4CE 					 
1996030100506	19960301	00506	NE 	1996	3	1	96ZZZX865 	2	19951221	G	8530	27056	PISTON 		399353 	BEECH 	18 	E18S 	1151006	CE 	PWA 	R985 	R985* 	52008	NE 					NR 2 CYL	DEFECTIVE 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	5611D	621 				BA316	8486			IN C/W AD 78-08-07 INSPECTION FOR POSSIBLE SEPARATION OF CYLINDER HEAD AND BARREL, SIGNS OF BLOW-BY WERE NOTED. CYLINDE	R ASSY REMOVED AND RETURNED TO OVERHAUL FACILITY.					1	L	7	2 	3R	3	R		A765 	5E1				 
1996030100507	19960301	00507	NE 	1996	3	1	96ZZZX866 	2	19951220	G	8530	27056	PISTON 		399353 	BEECH 	18 	E18S 	1151006	CE 	PWA 	R985 	R985* 	52008	NE 					NR 9 CYL	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	5611D	1100 				BA316	22664			THE CYLINDER SHOWED LOW COMPRESSION AND EMITTED BLACK OILY EXHAUST. CYLINDER ASSY REMOVED. FOUND CRACKED PISTON. CRAC	K EXTENDED FROM PISTON PIN HOLE TO TOP OF PISTON. NO OTHER DAMAGE. CAUSE UNKNOWN.					1	L	7	2 	3R	3	R		A765 	5E1				 
1996030100509	19960301	00509	CE 	1996	3	1	96ZZZX868 	1	19950316	G	2810		TIP TANK 			BEECH 	35 	E35 	1151512	CE 										CARB SCREEN	MAKING FOD 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09										TIP TANK FILLER INSTALLED IN EARLY MODEL TIP TANKS. HAS SMALL PIECES OF METAL AND FIBERGLASS MIGRATING AND CLOGGING FUE	L LINES AND FILLING CARBURETOR SCREWS ON EARLY 'E' SERIES ENGINES. SUBMITTER STATED IF INSTALLED ON FUEL INJECTOR ENGIN	ES, COULD POSSIBLY CAUSE SAME PROBLEM. FUEL STARVATION WAS PROBLEM. RECOMMEND PART 39 ACTION. AIRCRAFT WAS USING AUTO	GAS.			1	L	7	1 	3O				A777 					 
1996010500597	19960105	00597	CE 	1996	1	5	96ZZZX87 	1	19951004	G	7921	6526601	COOLER 			CESSNA	206 	U206G 	2073356	CE 										ENGINE OIL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	4975U	395 				U20605179				OIL COOLER CORE WAS FOUND LEAKING.						1	H	7	1 	3O				A4CE 					 
1996030100512	19960301	00512	EA 	1996	3	1	96ZZZX871 	2	19951025	G	7314	LW15473	PUMP 			PIPER 	PA28 	PA28R201 	7102816	SO 	LYC 	O360 	IO360C1C 	41514	EA 					ENGINE FUEL	WASHER BROKEN 	B			OG5R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	21	171ND	1190 				2837006				DURING PHASE INSPECTION, FOUND WASHER PARTS IN SUCTION SCREEN. BROKEN WASHER WAS FROM ENGINE DRIVEN FUEL PUMP. WASHER 	IS LOCATED JUST BELOW LEVER SLOT OF PUMP WHERE IT SLIDES OVER PUMP VERTICAL PLUNGER SHAFT.					1	L	7	1 	3O	3	O		2A13 	1E10				 
1996030100513	19960301	00513	SO 	1996	3	1	96ZZZX872 	2	19950419	G	8550	CH48108	FILTER 	CHAMPION 		CESSNA	340 	340CESSNA 	2076404	CE 	CONT 	O520 	TSIO520N 	17040	SO 					ENGINE OIL	GASKET FAILED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	01	44SV	50 				3400032	20840173			ON A ROUTINE OIL CHANGE, FILTER WAS REMOVED AND CUT OPEN. SOMETHING RATTLING INSIDE WAS FOUND. RUBBER GASKET HAS PIECE	S MISSING ALONG WITH METAL SLIVERS. PARTS WERE PUMPED INTO ENGINE. ENGINE REMOVED, TORN DOWN. FOUND RUBBER PIECES IN 	2 LIFTERS. ENGINE FLUSHED, REASSEMBLED, AND INSTALLED. FILTER DATE CODE - F10E05-1.				1	L	7	2 	3O	3	O		3A25 	E8CE				 
1996010500598	19960105	00598	CE 	1996	1	5	96ZZZX88 	1	19951127	G	7921	6526601	COOLER 			CESSNA	206 	U206G 	2073356	CE 										ENGINE OIL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	4975U	107 				U20605179				OIL COOLER CORE WAS FOUND LEAKING AFTER RETURNING FROM A FLIGHT. THIS IS THE SECOND COOLER FOUND LEAKING ON THIS ENGINE	. FIRST LEAK OF COOLER WAS AT 395.0 HOURS TOTAL TIME. TOTAL TIME ON ENGINE NOW IS 502.0 HOURS.					1	H	7	1 	3O				A4CE 					 
1996030100530	19960301	00530	GL 	1996	3	1	96ZZZX889 	3	19951107	G	6110		PROPELLER 			CESSNA	182 	182R 	2072731	CE 	CONT 	O470 	O470U 	17026	SO 	MCAULY	2A34C	C2A34C204 	GL 	STC PROP	VIBRATION 	D				K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			NM	01	6374N					18267832	286965R	940528		REMOVED 2-BLADED PROPELLER. INSTALLED 3-BLADED HARTZELL PROPELLER UNDER STC SA090015. SPENT HUNDREDS OF MAN HOURS TROU	BLESHOOTING EXTREME VIBRATION IN AIRFRAME. INSTALLED SAME 3-BLADED PROP ON DIFFERENT AIRCRAFT SAME VIBRATION (BAD). REM	OVED PROP, RETURNED TO STC HOLDER. SUBMITTER RECOMMENDED REMOVING THE O470U ENGINE FROM THIS STC.				1	L	7	1 	3O	3	O	NT	3A13 	E273	5	C	P3EA	 
1996010500599	19960105	00599	CE 	1996	1	5	96ZZZX89 	1	19951012	G	7921	6526601	COOLER 			CESSNA	206 	U206G 	2073356	CE 										ENGINE OIL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	244PL	196 				U20604371				OIL COOLER FOUND LEAKING. THIS IS THE SECOND OIL COOLER ON THIS ENGINE. THE FIRST STARTED LEAKING AT 353.0 HOURS TOTAL	 TIME. THE SECOND AT 549.5 HOURS TOTAL TIME.					1	H	7	1 	3O				A4CE 					 
1996010500600	19960105	00600	CE 	1996	1	5	96ZZZX90 	1	19950810	G	7921	6526601	COOLER 			CESSNA	206 	U206G 	2073356	CE 										ENGINE OIL	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			AL	03	244PL	354 				U20604371				OI COOLER CORE WAS FOUND LEAKING.						1	H	7	1 	3O				A4CE 					 
1996010500601	19960105	00601		1996	1	5	96ZZZX91 	4	19950327	G	2562	EB2BCD	ELT 	MARTECH 		PIPER 	PA34 	PA34200T 	7103406	SO 										BATTERY	CASE LEAK 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	08	821GS				31357	347770419				DURING BATTERY REPLACEMENT, FOUND BATTERY HAD CRACKED AND LEAKED CAUSING INTERIOR OF ELT TO BECOME SEVERELY CORRODED. E	LT WAS STILL FUNCTIONAL ON FUNCTION TEST.					1	L	7	2 	3O				A7SO 					 
1996030800547	19960308	00547	SO 	1996	3	8	96ZZZX936 	2	19950925	G	8530	631996	RETAINER 			PIPER 	PA28 	PA28R201T 	7102813	SO 	CONT 	O360 	TSIO360FB 	17025	SO 					ROCKER SHAFT	CRACKED 	D	S			K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	123HD		39 			28R7803069	299531R			DURING C/W CONTINENTAL SB CSB95-4, FOUND 2 ROCKER SHAFT RETAINERS CRACKED THROUGH THE BOLT HOLE.						1	L	7	1 	3O	3	O		2A13 	E9CE				 
1996030800550	19960308	00550		1996	3	8	96ZZZX939 	1	19951026	G	2421	M832481251	PACKING 	LUCAS 	31708001A 															ALT DRV END	LEAKING 	B			OL3R	K				NONE 				K	W		FLUID LOSS 	INADEQUATE Q C 		IN	INSP/MAINT 	1			WP	27			664 		1056					MASSIVE LEAKAGE OUT OF PARTING SURFACES (A.D.E.). UPON VISUAL INSPECTION, FOUND A.D.E. END BELL INSTALLED INCORRECTLY. 	 MATING SURFACES NOT SEATED PROPERLY DUE TO INTERFERENCE FROM EXTRUDING PACKING RESULTING IN SEVERE OIL LEAKAGE. PACKIN	G VISIBLE WITH EXTERNAL INSPECTION, AIR GAP OF ABOUT .0625 INCH. ON DISASSEMBLY, FOUND 6 SECURING SCREWS LOOSE, FOUND P	ACKING SEPARATED IN 3 PIECES. FOUND GLASS BEADS THROUGHOUT GENERATOR. FOUND MAIN FIELD LEAD T2 NUT SECURED. SERVICE T	AG INDICATES NIACC TECHNOLOGY, INC., SERVICED UNIT. (CRS-DC3R444L).															 
1996010500605	19960105	00605	CE 	1996	1	5	96ZZZX95 	1	19951218	G	8120	4066109005	TURBOCHARGER 	AIRESRCH 		CESSNA	206 	TU206F 	2073353	CE 	CONT 	O520 	TSIO520C 	17040	SO 					ENGINE	BEARING FAILED 	B			LJQR	O				OTHER 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			EA	09	8647Q		1 		YJ026773	U20603463				TURBOCHARGER REPLACED FOR LOW BOOST. MFG OVERHAULED TURBOCHARGER, INSTALLED AND GROUND RUN ACCOMPLISHED. GROUND PERFOR	MANCE SATISFACTORY. DURING FLIGHT, LOW BOOST CONDITION NOTED. INSPECTION OF TURBOCHARGING SYSTEM REVEALED TURBINE WHEE	L TIP RUB AND EXCESSIVE SHAFT PLAY. OVERHAULED TURBO HAD ACHIEVED 20-25 MINUTES OPERATION PRIOR TO FAILURE. TURBINE SH	AFT BEARINGS FAILED. UNIT RETURNED TO MFG 10-29-95. ACFT TOTAL: 2,721.6 HOURS.			1	H	7	1 	3O	3	O		A4CE 	E8CE				 
1996030800561	19960308	00561	SO 	1996	3	8	96ZZZX950 	2	19951227	G	8540	EQ6642	ADAPTER KIT 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520N 	17032	SO 					STARTER	EXCESS WEAR 	B			CWNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	09	369NM	40 				421C1032	277113R			ON 12-27-95, A 50-HOUR INSPECTION WAS PERFORMED. METAL CONTAMINATION NOTED IN RT ENG OIL FILTER. FURTHER INVESTIGATION	 REVEALED TORSIONAL DAMPER AND STARTER SHAFT GEAR ASSY WERE LOOSE IN THE STARTER ADAPTER HOUSING. ADAPTER ASSY REMOVED 	AND FND NEEDLE BEARING MOUNTED IN REAR CENTER OF RT CRANKCASE HAD COMPLETELY COME APART. STARTER ADAPTER SHAFT GEAR WAS	 THEN ALLOWED TO ELONGATE THE HOLE. BEARING IS MOUNTED IN AND RENDER THE CRANKCASE UNSERVICEABLE AT THIS TIME. CSB94-4	A C/W ON 11-15-95 BY INSTALLATION OF A REBUILT EQ6642 STARTER ADAPTER KIT. A NEW BEARING, PN 537721, INSTALLED AT THE S	AME TIME BECAUSE FRONT FACE OF OLD BEARING CAGE WAS WORN PAPER THIN.	1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1996030800562	19960308	00562	CE 	1996	3	8	96ZZZX951 	1	19951215	G	3242	16416	BRAKE DISC 	PARKERHANFIN	4083B 	BEECH 	36 	A36 	1151604	CE 										MLG	HOLES BROKEN 	B			VT3R	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			WP	09	9675R	1210 				E2503				DURING ROUTINE INSPECTION, FOUND BRAKE DISC LOOSE ON WHEEL. FOUND ALL 3 BRAKE DISC BOLT HOLES BROKEN OUT. WHEEL HALF B	OLTS PROPERLY TORQUED. LOOSE BRAKE DISC CAUSED DAMAGE TO LOWER TORQUE LINK AND TO BRAKE CARRIER. SUBMITTER RECOMMENDS 	CLOSE INSPECTION DURING PRE-FLIGHT AND INSPECTIONS AND MAINTENANCE.				1	L	7	1 	3O				3A15 					 
1996030800567	19960308	00567	CE 	1996	3	8	96ZZZX956 	1	19951218	G	3230	55423022	LINK ASSY 			CESSNA	500 	S550 	2076607	CE 										NLG	WORN 	B			CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	151QS	6646 				S5500151				DURING INSPECTION, FOUND LOWER TORQUE LINK ASSY WORN TO LIMITS AT THE CENTER CONNECTION. THE BUSHING IN THE UPPER TORQU	E LINK ASSY CAUSES THE WEAR. SUBMITTER SUGGESTS THE LOWER TORQUE LINK ASSY NEEDS TO HAVE BUSHINGS INSTALLED IN THE CENT	ER CONNECTION.				1	L	7	2 	4F			RT	A22CE 					 
1996010500606	19960105	00606	WP 	1996	1	5	96ZZZX96 	2	19951111	G	7250	31038393	SEAL 		31033155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		7114 			1233152001		P70109			DURING CAM INSPECTION, FOUND SEAL CRACKED AT SEAL FLANGE IN 7 PLACES. THIS IS A CRITICAL MAIN ROTATING GROUP LIFE-LIMIT	ED COMPONENT. CURRENT LIFE LIMIT IS 20,000 CYCLES. TOTAL CYCLES 7,894.										4	T			E4WE				 
1996030800571	19960308	00571	CE 	1996	3	8	96ZZZX960 	1	19950518	G	5541	3363000017	SPAR 			BEECH 	33 	35C33 	1151408	CE 										RUDDER	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	27	6142V	4696 				CD874				PERFORMING AD 93-24-03 FOUND CRACKED RUDDER SPAR UNDER UPPER HINGE BRACKET.						1	L	7	1 	3O				3A15 					 
1996030800573	19960308	00573	CE 	1996	3	8	96ZZZX962 	1	19951224	G	2720	6565007195	CONTROL CABLE 			CESSNA	500 	S550 	2076607	CE 										RUDDER	FRAYED 	B			CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	111QS	9269 				S5500111				DURING INSPECTION, FOUND LEFT RUDDER CABLE WITH BROKEN WIRE STRANDS. THE CABLE WAS DAMAGED AT THE FAIRLEAD BRACKET FORW	ARD OF FS 400.50. THE TEFLON FAIRLEAD, PN S338-3, CAUSES DAMAGE TO CABLE WHERE EVER INSTALLED IN THE AIRCRAFT. SUBMITT	ER STATED A NEW MATERIAL FOR THE FAIRLEAD SHOULD BE LOOKED AT.				1	L	7	2 	4F			RT	A22CE 					 
1996010500607	19960105	00607	WP 	1996	1	5	96ZZZX97 	2	19951127	G	7250	31033155	SEAL 		31033155 						GARRTT	TPE331	TPE33112UAR 	01514	WP 					TURB 1ST STAGE	CRACKED 	B			DSCR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	25		7517 			1233151982		P70086C			DURING SCHEDULED CAM INSPECTION, FOUND PART CRACKED AT FLANGE. THIS IS A MAIN ROTATING GROUP, CRITICAL LIFE-LIMITED COM	PONENT. LIFE-LIMIT IS 20,000 CYCLES. SUGGEST ALLIED SIGNAL ENGINEERING DETERMINE AND CORRECT THE CAUSE OF THIS PROBLEM	. THIS IS THE 21ST MALFUNCTION/DEFECT REPORT FILED BY THIS REPAIR STATION ON THIS TOPIC. TOTAL CYCLES, 9,199.									4	T			E4WE				 
1996030800581	19960308	00581	CE 	1996	3	8	96ZZZX970 	1	19951028	G	7170	1019300133	TUBE 			BEECH 	200 	200BEECH 	1152920	CE 										ENG OIL DRAIN	CRACKED 	H				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	21	87BP					BB34				FOUND ENGINE OIL STAINLESS STEEL DRAIN TUBE CRACKED IN RADIUS OF 90 DEGREES BEND JUST BELOW B-NUT AT ENGINE SUPPLY TANK.	 NOTED PUDDLE OF OIL BELOW NACELLE ON GROUND AND OIL ON LOWER COWL. OPENING COWL FOUND OIL ON TOP OF OIL COOLER AND AT	 LOWER END OF DRAIN TUBE. WIPED DOWN DRAIN TUBE AND APPLIED SLIGHT PRESSURE TO TUBE. OIL BEGAN LEAKING AT 90 DEGREE BEND	 BELOW TOP B-NUT. REPLACED TUBE.			1	L	7	2 	4T				A24CE 					 
1996031500080	19960315	00080	EU 	1996	3	15	96ZZZX977 	1	19950906	G	7712	10590952	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										OUT OF TOLERANCE	FAULTY 	B			JSNR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	204PC	429 				S895				NR 2 ENGINE FAILED POWER ASSURANCE CHECK WHEN PERFORMED IAW AIRCRAFT FLIGHT MANUAL. ENGINE CHECKED FOR BLEED AIR LEAKS 	AND BLEED VALVE WAS SWAPPED. BURNER CAN, NR 1 NOZZLE AND WHEEL WERE VISUALLY INSPECTED WITH A BORESCOPE. FOUND OK. TO	RQUE GAUGE CHECKED AND FOUND OUT OF TOLERANCE (MINUS 5 PERCENT) WITH INFORMATION PROVIDED BY A.E.C. THIS INFORMATION IS	 NOT FOUND IN MM. COMPRESSOR WAS WASHED. SUBSEQUENT POWER CHECK SHOWED REASONABLE POWER MARGIN FOR ENGINE.			1	G	7	2 	3U				H3EU 					 
1996031500081	19960315	00081	SW 	1996	3	15	96ZZZX978 	1	19951129	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										START/GEN	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	704H		156 		87D0340	28108				VOLTAGE DROPPING TO LOW VOLT DURING START, CAUSED STARTER TO STOP CRANKING.						2	G	7	2 	4U				H10SW 					 
1996031500082	19960315	00082	GL 	1996	3	15	96ZZZX979 	2	19951016	G	7313	6899001	NOZZLE 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					FUEL	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	732H		88 		0956	51607				FUEL NOZZLE 'ERRATIC SPRAY PATTERN'.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1996010500608	19960105	00608	EU 	1996	1	5	96ZZZX98 	1	19951201	G	6730	AC67246	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	LEAKING 	B			DYRR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	11	6099P				RC206	2818				SERVO HAD BEEN REMOVED FOR LEAKAGE. FOLLOWING INSPECTION BY REPAIR AGENCY (NO DEFECTS FOUND), UNIT WAS REINSTALLED. AF	TER 10 HOURS IN SERVICE, SERVO STARTED TO LEAK.					1	G	7	1 	3U				H9EU 					 
1996031500083	19960315	00083	NE 	1996	3	15	96ZZZX980 	2	19951221	G	7321	324473512	FUEL CONTROL 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					ENGINE	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	735H		31 		B41152	35046	35046			ENGINE EXTREMELY SLOW TO DECELERATE FROM 80 PERCENT N1 TO 61 PERCENT N1. (TAKES ABOUT 10 SECONDS.)						1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1996031500084	19960315	00084	SW 	1996	3	15	96ZZZX981 	1	19951011	G	7722	212075067109	GAUGE 			BELL 	212 	212 	1181420	SW 										COCKPIT ITT	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	736H	29 			262	35048				STICKS ON START AND FLUCTUATES DURING CRUISE - INTERMITTENT.						1	G	7	1 	4U				H4SW 					 
1996031500085	19960315	00085	SW 	1996	3	15	96ZZZX982 	1	19950824	G	6730	212076005105	SERVO 			BELL 	212 	212 	1181420	SW 										M/R	LEAKING 	C				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EU	01	754H		479 		HR7936	35034				SERVO LEAKING EXCESSIVELY FROM UPPER CYLINDER. ALSO, PRO-SEAL FROM UPPER CLEVIS HAD DOWN INSIDE UPPER CYLINDER.						1	G	7	1 	4U				H4SW 					 
1996031500086	19960315	00086	SW 	1996	3	15	96ZZZX983 	1	19951011	G	3210	214031839101	STRAP ASSY 			BELL 	214 	214ST 	1182106	SW 										MLG	DEBONDED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H	152 			950330	28197				STRAP ASSY HAS DEBONDED RUBBER PAD.						2	G	7	2 	4U				H10SW 					 
1996031500087	19960315	00087	SW 	1996	3	15	96ZZZX984 	1	19950819	G	6322	ES731701	BLOWER 			BELL 	214 	214ST 	1182106	SW 										COOL SYSTEM	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	745H	124 			7	28197				BLOWER ASSY 'WILL NOT COME ON'.						2	G	7	2 	4U				H10SW 					 
1996031500088	19960315	00088	SW 	1996	3	15	96ZZZX985 	1	19950920	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENGINE	FAILED 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	746H		4 		84L0166	28200				STARTER WILL NOT DISENGAGE.						2	G	7	2 	4U				H10SW 					 
1996031500089	19960315	00089	SW 	1996	3	15	96ZZZX986 	1	19950902	G	2434	214175150105	GENERATOR 			BELL 	214 	214ST 	1182106	SW 										NR 2	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	746H		307 		429	28200				NR 2 GENERATOR WILL NOT COME ON LINE.						2	G	7	2 	4U				H10SW 					 
1996031500090	19960315	00090	SW 	1996	3	15	96ZZZX987 	1	19950929	G	2434	214175150105	GENERATOR 			BELL 	214 	214ST 	1182106	SW 										DC SYSTEM	DEFECTIVE 	C				K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			EU	01	746H		73 		219	28200				GENERATOR DISENGAGES, LIGHT ON, NO AMP INDICATION.						2	G	7	2 	4U				H10SW 					 
1996031500091	19960315	00091	SW 	1996	3	15	96ZZZX988 	1	19950919	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										START/GEN	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	746H		283 		82M0061	28200				STARTER SLOW DURING START, HIGH AMPS, LOW VOLTAGE.						2	G	7	2 	4U				H10SW 					 
1996031500092	19960315	00092	SW 	1996	3	15	96ZZZX989 	1	19950924	G	8010	214060056001	STARTER SWTICH 			BELL 	214 	214ST 	1182106	SW 										ENGINE	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	746H		3 		81L0018M	28200				STARTER SWITCH CUT OFF AT 15 PERCENT N1.						2	G	7	2 	4U				H10SW 					 
1996010500609	19960105	00609	GL 	1996	1	5	96ZZZX99 	2	19950915	G	7323	56075042	CONTROL CABLE 			BELL 	47 	47G5 	1181032	SW 	ALLSN 	250C 	250C18B 	03011	GL 					N2 GOVERNOR	FAILED 	B			EOOR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03	2251W					7965	CAE800447B			N2 GOVERNOR CONTROL CABLE END FAILED WHILE BEING INSTALLED ON HELICOPTER. THREADED END BROKE OFF DURING INITIAL ADJUSTM	ENT ON GROUND. THIS CABLE END IS A 1/4-28 THREADED FITTING THAT IS SWAGED ONTO A .1875 INCH CABLE SHANK. THE THREADS H	AD BEEN CUT TOO FAR DOWN UNTIL THEY MET THE END OF THE BORE THAT IS SWAGED ONTO CABLE SHANK LEAVING VERY LITTLE MATERIAL	. SUBMITTER STATED PROPERLY MANUFACTURED THREADED ENDS HAVE APPROXIMATELY .125 INCH BETWEEN END OF THREADS AND END OF S	WAGE BORE.		1	G	7	1 	3O	3	U		2H3 	E4CE				 
1996031500093	19960315	00093	SW 	1996	3	15	96ZZZX990 	1	19950820	G	6710	214001160129	STICK ASSY 			BELL 	214 	214ST 	1182106	SW 										COLLECTIVE	LOOSE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	746H		84 		27253	28200				AXIAL PLAY (END CHUCK) IN NR 1 THROTTLE GRIP. COLLECTIVE HEAD RIVETS LOOSE.						2	G	7	2 	4U				H10SW 					 
1996031500094	19960315	00094	SW 	1996	3	15	96ZZZX991 	1	19950828	G	7714	212075037105	INDICATOR 			BELL 	212 	212 	1181420	SW 										RPM	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	749H		106 		0565	35061				RPM INDICATOR STICKING AT 65 PERCENT. WITH TAP ON GAUGE, NEEDLE CAME DOWN TO 61.5 PERCENT, NR 1.						1	G	7	1 	4U				H4SW 					 
1996031500095	19960315	00095	SW 	1996	3	15	96ZZZX992 	1	19950410	G	7712	206075739103	INDICATOR 			BELL 	206 	206L3 	1182108	SW 										COCKPIT TORQUE	FLUCTUATES 	C				K				NONE 				O			OTHER 			CR	CRUISE 	1			EU	01	727H		298 		468	51550				INDICATOR FLUCTUATES AT CRUISE.						1	G	7	1 	3U				H2SW 					 
1996031500096	19960315	00096	SW 	1996	3	15	96ZZZX993 	1	19950620	G	6520	206040402003	GEARBOX 			BELL 	206 	206L3 	1182108	SW 										T/R	DEFECTIVE 	C				K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			EU	01	727H		109 		AFS2895	51550				HIGH FREQUENCY VIBRATION AND UNABLE TO BALANCE T/R ASSY WHEN INSTALLED ON GEARBOX.						1	G	7	1 	3U				H2SW 					 
1996031500099	19960315	00099	NE 	1996	3	15	96ZZZX996 	2	19950421	G	7321	32447066	CONTROL UNIT 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					ENGINE	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	703H				A65636	31101				TORQUE, N1 AND ITT FLUCTUATION ON BOTH POWER SECTIONS.						1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1996031500100	19960315	00100	SW 	1996	3	15	96ZZZX997 	1	19950808	G	2436	51509002R	REGULATOR 			BELL 	212 	212 	1181420	SW 										DC SYSTEM	FAULTY 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	703H				6761AB	31101				GENERATOR POWER WILL NOT COME ON LINE, FAULTY REGULATOR.						1	G	7	1 	4U				H4SW 					 
1996031500101	19960315	00101	SW 	1996	3	15	96ZZZX998 	1	19950807	G	2436	51509002R	REGULATOR 			BELL 	212 	212 	1181420	SW 										DC SYSTEM	DEFECTIVE 	C				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EU	01	703H		38 		5235	31101				GENERATOR WILL NOT COME ON LINE.						1	G	7	1 	4U				H4SW 					 
1997032700069	19970327	00069	SO 	1997	3	27	97ZZZX1151 	2	19950606	G	8530	40762	COVER 			CESSNA	172 	172H 	2072424	CE 	CONT 	O300 	O300D 	17022	SO 					NR 2 CYL VALVE	HOLED 	H				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	08	2600L	1073 				17255800	35313D6D			A HOLE WAS FOUND IN THE VALVE COVER. THE SHAFT OF THE VALVE ROCKER ROTATED AND WORE THROUGH THE SIDE OF THE VALVE COVER	. SUBMITTER STATED HAVE SEEN SIGNS OF THIS KIND OF WEAR, BUT NOT TO THIS DEGREE,3 OF THE REMAINING 6 CYLS SHOWED SOME SI	GNS AND WERE REPLACED. A NYLON PLUG IN ENDS OF (21153) SHAFT-VALVE ROCKER WOULD STOP THIS ACTION.				1	H	7	1 	3O	3	O	NT	3A12 	E253				 
1997010900105	19970109	00105	EA 	1997	1	9	97ZZZX12 	2	19951026	G	8530		VALVE GUIDE 			PIPER 	PA28 	PA28181 	7102807	SO 	LYC 	O360 	O360A4M 	41514	EA 					NR 3 CYL EXH	EXCESS WEAR 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	99	8235S	837 				288090359	L2841736A			NR 3 CYLINDER HAD POOR COMPRESSION. IN THE PROCESS OF REMOVING CYLINDER IT WAS NOTED THE ROCKER ARMS WERE INCORRECTLY IN	STALLED. THE INTAKES WERE ON THE EXHAUST AND THE EXHAUST WAS ON THE INTAKE. IN CHECKING THE OTHER CYLINDERS, ALL THE R	EMAINING ROCKER ARMS WERE INCORRECTLY INSTALLED. ENGINE WAS OVERHAULED BY FIREWALL FORWARD INC.				1	L	7	1 	3O	3	O		2A13 	E286				 
1997041700207	19970417	00207	SO 	1997	4	17	97ZZZX1613 	1	19951020	G	3030	464357	ELEMENT 			PIPER 	PA34 	PA34200T 	7103406	SO 										REAR PITOT HEAT	OPEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	81070					348070013				LOSS OF AIRSPEED - TRACED TO OPEN PITOT HEAT ELEMENT.						1	L	7	2 	3O				A7SO 					 
1997041700208	19970417	00208	SO 	1997	4	17	97ZZZX1614 	1	19951020	G	3030	464356	ELEMENT 			PIPER 	PA34 	PA34200T 	7103406	SO 										FWD PITOT HEAT	OPEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	81070					348070013				LOSS OF AIRSPEED - TRACED TO OPEN PITOT HEAT ELEMENT.						1	L	7	2 	3O				A7SO 					 
1997041700209	19970417	00209	SO 	1997	4	17	97ZZZX1615 	1	19950302	G	3030	464357	ELEMENT 			PIPER 	PA34 	PA34200T 	7103406	SO 										REAR PITOT HEAT	OPEN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	05	81070					348070013				LOSS OF AIRSPEED - TRACED TO OPEN PITOT HEAT ELEMENT. REPLACED REAR ELEMENT 3-2-95.						1	L	7	2 	3O				A7SO 					 
1997072400096	19970724	00096	GL 	1997	7	24	97ZZZX3213 	2	19950905	G	7230	6896024	EJECTOR NOZZLE 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					COMPRESSOR ASSY	CRACKED 	D	L	A		A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			WP	01	5753D					45529	CAE860704			DURING FLIGHT, PILOT HEARD A LOUD BANG FOLLOWED BY A WHINE. PILOT LANDED THE AIRCRAFT WITH NO FURTHER PROBLEMS. INSPEC	TED AND FOUND EJECTOR NOZZLE ASSY MISSING ONE NOZZLE, FOUND THE BROKEN NOZZLE HAD BEEN SUCKED IN BY THE COMPRESSOR, AND 	FOUND THE REMAINS OF THE NOZZLE TRAPPED BETWEEN OUTER COMBUSTION CASE.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1997073100039	19970731	00039	EA 	1997	7	31	97ZZZX3328 	2	19951211	G	7414	D4RN2021	MAGNETO 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					DISTRIBUTOR GEAR	TEETH STRIPPED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	5855E		986 		5626462	17271946	RL555876T			TEETH ON DISTRIBUTOR GEAR WERE SHEARED CAUSING A VERY SEVERE MAG DROP ON RIGHT MAGNETO SIDE. A MAGNETO LOCKING TOOL WAS	 NOT USED DURING INSTALLATIONS AFTER AD CHECKS. THIS IS A SINGLE POINT DUAL MAGNETO.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1997073100044	19970731	00044	EA 	1997	7	31	97ZZZX3333 	2	19951211	G	7414	D4RN2021	MAGNETO 	BENDIX 		CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					DISTRIBUTOR GEAR	TEETH SHEARED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	01	733SW		639 		5032425R	17268521	L245976T			TEETH ON DISTRIBUTOR GEAR WERE SHEARED CAUSING A SEVERE MAG DROP ON LEFT MAGNETO SIDE. CAUSE UNKNOWN. A MAGNETO LOCKIN	G TOOL WAS NOT USED DURING INSTALLATIONS AFTER AD COMPLIANCES. THIS IS A SINGLE POINT DUAL MAGNETO.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1997091800246	19970918	00246	GL 	1997	9	18	97ZZZX3991 	1	19950601	G	3240	30133	BRAKE 			AMTR 	VIPER 	VIPER 	05625AS	GL 										LT MLG	LOCKED UP 	D				O				OTHER 				O			OTHER 			LD	LANDING 	1			WP	07	18VX	2 			199152	001				BRAKE LOCKED UP INSTANTANEOUSLY ON RUNWAY AT 53 MPH, CAUSE, AIRPLANE SPIN-OUT.						1	L	7	1 	3V			NC	EXPA1L71					 
1997100200069	19971002	00069	WP 	1997	10	2	97ZZZX4197 	1	19951019	G	3250	49206301	STEERING PISTON 		5920605503 	DOUG 	DC9 	DC932 	3022066	WP 										NLG	PIN SHEARED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	09	43537					47112				ONE EACH OF TWO STEERING PISTON PINS THAT GO THROUGH COLLAR, PN 5920605-503, WAS SHEARED INSIDE THE COLLAR. THE BREAK W	AS IN THE BOTTOM THIRD OF THE SHANK. THERE WAS A HEAVY COATING OF RUST ACROSS THE SHEARED SURFACE. THIS DEFECT WAS DIS	COVERED DURING THE PERFORMANCE OF AN A-CHECK.				2	L	7	2 	4F				A6WE 					 
1997022000478	19970220	00478	CE 	1997	2	20	97ZZZX791 	1	19951229	G	3240	075302782	TORQUE PLATE 			CESSNA	185 	A185F 	2072821	CE 										RT BRAKE	CRACKED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	25	24FG	7097 				18504207				INSP FOUND PLATE CRACKED AT TOP CALIPER BUSHING. THIS AREA IS THE WEAKEST OF THE ENTIRE PLATE, YET TAKES A HIGH PERCENT	AGE OF THE TORQUE.					1	H	7	1 	3O				3A24 					 
1997010900101	19970109	00101	EA 	1997	1	9	97ZZZX8 	2	19950303	G	8530	SL13441	PISTON PIN 			CESSNA	172 	172N 	2072434	CE 	LYC 	O320 	O320H2AD 	41508	EA 					NR 3 CYL	BROKEN 	B			MX3R	A				UNSCHED LANDING 				Y	E	K	ENGINE STOPPAGE 	VIBRATION/BUFFET 	FLUID LOSS 	CR	CRUISE 	1			WP	11	4773E	265 				17271638	L437476			ENGINE FAILED IN CRUISE FLIGHT DUE TO BROKEN PISTON PIN IN NR 3 CYLINDER. ENGINE DESTROYED, CASES BROKEN, RODS BENT, PI	STONS CRACKED. AIRCRAFT SUCCESSFULLY LANDED ON COUNTRY ROAD NEAR AIRPORT. SUPERIOR AIR PARTS WARRANTED ENGINE.					1	H	7	1 	3O	3	O	NT	3A12 	E274				 
1997030600293	19970306	00293	GL 	1997	3	6	97ZZZX889 	3	19950526	G	6111		BLADE 			SLNSBY	T67 	T67M260 	8323006	EU 						HOFMAN	HOV123	HOV123KV 	GL 	BASE	DELAMINATED 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	17	30367	570 				2133		B711		INSPECTION FOUND DELAMINATION AT BASE OF BLADE. SUBMITTER STATED CAUSE UNKNOWN. AWAITING INFORMATION FROM MANUFACTURER	.					1	L	7	1 	3O			NT	A73EU 		5	C	P5EU2	 
1998121100025	19981211	00025	SO 	1998	12	11	98ZZZX4468 	2	19950927	G	8530	646283	INTAKE VALVE 			CESSNA	182 	182Q 	2072732	CE 	CONT 	O470 	O470U 	17026	SO 					ENGINE	MISMANUFACTURED 	B			MK5R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	23	954CC	100 				18265290	286937R			DURING A ROUTINE COMPRESSION CHECK, THE INTAKE VALVE WAS FOUND LEAKING ON THE NR 4 CYLINDER. THE CYLINDER WAS REMOVED A	ND THE INTAKE VALVE AND SEAT WERE REGROUND TO FIT EACH OTHER. SUBMITTER SUGGESTED POSSIBLE CAUSE AS IMPROPER ASSEMBLY P	ROCESS AT THE FACTORY.				1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1998121100131	19981211	00131	SO 	1998	12	11	98ZZZX4521 	2	19951206	G	8530	646286	VALVE 			CESSNA	182 	182P 	2075816	CE 	CONT 	O470 	O470S 	17026	SO 					ENGINE	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	953CC	700 				18264109	269314R			DURING A ROUTINE COMPRESSION CHECK, THE EXHAUST VALVE WAS FOUND LEAKING ON THE NR 1 CYLINDER. THE REMOVED CYLINDER HAD 	A WORN OUT EXHAUST VALVE AND GUIDE. SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS OR ASSY PROCESS AT THE FACTOR	Y.				1	H	7	1 	3O	3	O	NT	TA13 	E273				 
1998121100132	19981211	00132	SO 	1998	12	11	98ZZZX4522 	2	19951206	G	8530	648014	GUIDE 			CESSNA	182 	182P 	2075816	CE 	CONT 	O470 	O470S 	17026	SO 					ENGINE	WORN 	D				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	953CC	700 				18264109	269314R			DURING A ROUTINE COMPRESSION CHECK, THE EXHAUST VALVE WAS FOUND LEAKING ON THE NR 1 CYLINDER. THE REMOVED CYLINDER HAD 	A WORN OUT EXHAUST VALVE AND GUIDE. SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS OR ASSY PROCESS AT THE FACTOR	Y.				1	H	7	1 	3O	3	O	NT	TA13 	E273				 
1999012200110	19990122	00110	EA 	1999	1	22	99ZZZX309 	2	19951224	G	8520	60734	SEAL 			PIPER 	PA28 	PA28180 	7102808	SO 	LYC 	O360 	O360A4A 	41514	EA 					CRANKCASE	FAILED 	D				O				OTHER 				K			FLUID LOSS 			NR	NOT REPORTED 	1			CE	01	5116L					284399	L1169236A			APPROXIMATELY 1 INCH OF CRANKSHAFT SEAL PROTRUDED OUT OF CRANKCASE, OIL EXITED ENGINE. PILOT LANDED AIRPLANE IN BEAN FI	ELD. AIRPLANE GROUND LOOPED, PROP STRUCK GROUND, AND BENT NOSE WHEEL FORK.					1	L	7	1 	3O	3	O		2A13 	E286				 
1995111700651	19951117	00651	EU 	1995	11	17	A6WR95002 	1	19951005	G	5741		BOLT 			BAG 	BAE146	BAE146200A 	1500266	EU 										LT FR 29 LT WING	LOOSE 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND LT WING TO FUSELAGE BOTTOM ATTACH BOLT AT FRAME 29 SHOWING SIGNS OF SPINNING. REMOV	ED SEALANT, INSPECTED BOLT AND FOUND SECURE, RESEALED BOLT. UNDER INVESTIGATION BY AVRO ENGINEERING. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700652	19951117	00652	EU 	1995	11	17	A6WR95003 	1	19951005	G	5741		BOLTS 			BAG 	BAE146	BAE146200A 	1500266	EU 										LT FR 26	LOOSE 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND LT WING TO FUSELAGE TOP AND BOTTOM ATTACH BOLTS AT FRAME 26 SHOWING EVIDENCE OF SPIN	NING. REMOVED SEALANT, INSPECTED BOLT, AND FOUND SECURE. RESEALED BOLT. UNDER INVESTIGATION BY AVRO ENGINEERING. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700653	19951117	00653	EU 	1995	11	17	A6WR95004 	1	19951005	G	5755		BOLT 			BAG 	BAE146	BAE146200A 	1500266	EU 										LT ROLL SPOILER	MISINSTALLED 	B			A6WR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING SCHEDULED INSPECTION, FOUND LT ROLL SPOILER CENTER AND OUTBOARD HINGE BOLTS INSTALLED BACKWARDS. RE-INSTALLED BO	LTS IAW A.M.M. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700654	19951117	00654	EU 	1995	11	17	A6WR95005 	1	19951005	G	5711		BOLT 			BAG 	BAE146	BAE146200A 	1500266	EU 										RT WING AFT SPAR	WRONG NUT 	B			A6WR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND RIGHT WING REAR SPAR ROOT JOINT ATTACH FITTING BOLT 'B' HAD INCORRECT NUT INSTALLED.	 REPLACED WITH PROPER NUT. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700655	19951117	00655	EU 	1995	11	17	A6WR95006 	1	19951005	G	5320		STIFFENER 			BAG 	BAE146	BAE146200A 	1500266	EU 										FR 29 FS 25.94	CRACKED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND FRAME 29 STIFFENER AT 25.94 CRACKED AT BOLT HOLE. REPAIRED STIFFENER IAW BAE DRAWIN	G HC536H9165. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700656	19951117	00656	EU 	1995	11	17	A6WR95007 	1	19951012	G	5711		BOLT 			BAG 	BAE146	BAE146200A 	1500266	EU 										RT WING SPAR	REQUIRED RESEAL 	B			A6WR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND RT WING REAR SPAR ROOT JOINT ATTACH FITTING LEAKING AT BOLT 'A'. REMOVED AND INSPEC	TED BOLT. RESEALED AND INSTALLED BOLT. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700657	19951117	00657	EU 	1995	11	17	A6WR95008 	1	19951012	G	5712		RIB 			BAG 	BAE146	BAE146200A 	1500266	EU 										RT WING	CHAFED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND FALSE SPAR RIB ON RT WING TO HAVE EVIDENCE OF CHAFING. REPAIRED RIB IAW BAE SB24-44	. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700658	19951117	00658	EU 	1995	11	17	A6WR95009 	1	19951012	G	5330		SKIN 			BAG 	BAE146	BAE146200A 	1500266	EU 										FWD DOOR SCUFF	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND 2 SPOTS OF CORROSION AROUND RIVET HEADS IN FUSELAGE SKIN UNDER FORWARD SERVICE DOOR 	SCUFF PLATE. REMOVED CORROSION AND RETREATED AREA IAW BAE FAX GB/RJ0958-95. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700659	19951117	00659	EU 	1995	11	17	A6WR95010 	1	19951012	G	5320	HC537H0650002	INTERCOSTAL 			BAG 	BAE146	BAE146200A 	1500266	EU 										FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND 2ND INTERCOSTAL INBOARD FROM AIRSTAIR RAIL IN FORWARD VESTIBULE CORRODED BEYOND LIMI	TS. REPLACED INTERCOSTAL IAW BAE SRM. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700660	19951117	00660	EU 	1995	11	17	A6WR95011 	1	19951012	G	5320	HC537H0655002	GUSSET 			BAG 	BAE146	BAE146200A 	1500266	EU 										FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND 2 GUSSET PLATES IN FORWARD VESTIBULE/LAVATORY AREA CORRODED. REPLACED GUSSET PLATES	 IAW BAE SRM. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700661	19951117	00661	EU 	1995	11	17	A6WR95012 	1	19951012	G	5712		BOLTS 			BAG 	BAE146	BAE146200A 	1500266	EU 										RIB NR 2 LT-RT	LOOSE 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND 13 LOOSE JO-BOLTS IN CENTER FUEL TANK AT RIBS 2, LEFT AND RIGHT. INSPECTION OF JO-B	OLTS REVEALED NO CORROSION PRESENT. RESEALED JO-BOLTS IAW BAE FAX GCB/RJ0955-95. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700662	19951117	00662	EU 	1995	11	17	A6WR95013 	1	19951012	G	2820		FEED PIPE 			BAG 	BAE146	BAE146200A 	1500266	EU 										NR 4 PYLON	LEAKING 	B			A6WR	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING SCHEDULED INSPECTION FOUND FUEL LEAKING FROM NR 4 PYLON FORWARD AND CENTER FUEL LINE COVER DRAINS. INVESTIGATION	 REVEALED THAT A SECTION OF THE NR 4 FUEL FEED PIPE THROUGH THE PYLON SHOULDER COWL WAS GROOVED INTERNALLY AT THE O-RING	 UPPER CONTACT AREA. REPLACED FUEL PIPE. (X)				2	H	7	4 	4F			RT	A49EU 					 
1995111700663	19951117	00663	EU 	1995	11	17	A6WR95014 	1	19951012	G	5400		RIB 			BAG 	BAE146	BAE146200A 	1500266	EU 										NR 2 PYLON	FLANGE CRACKED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	881DV					E2074				DURING STRUCTURAL INSPECTION, FOUND ON NR 2 PYLON CENTER BOX, 3 RIVET HEADS POPPED OFF ON FLOOR AND THE BOTTOM OUTBOARD 	FLANGE ON RIB NR 4 CRACKED. INSTITUTED 1,000 CYCLE RE-INSPECTION IAW BAE RILHC546H9018. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700664	19951117	00664		1995	11	17	A6WR95015 	4	19951013	G	2565	D31005	SLIDE 			BAG 	BAE146	BAE146200A 	1500266	EU 										PASSENGER DOOR	LIGHT DEFECTIVE 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV				0198	E2062				UPON SCHEUDLED SLIDE DEPLOYMENT TEST EMERGENCY LIGHTS ON SLIDE FAILED TO ILLUMINATE. BATTERY VOLTAGE CHECKED OK. FOUND	 ONE LIGHT ASSEMBLY DAMAGED AND WIRES SHORTED. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700665	19951117	00665	EU 	1995	11	17	A6WR95016 	1	19951013	G	5520	HC551B0087000	BOLT 			BAG 	BAE146	BAE146200A 	1500266	EU 										LT ELEV A-FRAME	CRACKED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, DETAILED VISUAL INSPECTION OF LT ELEVATOR, LOWER A-FRAME BOLT REVEALED CRACK IN THE THREAD	 RUN-OUT AREA. REPLACED BOLT. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700666	19951117	00666	EU 	1995	11	17	A6WR95017 	1	19951013	G	5520	HC551B0087000	BOLT 			BAG 	BAE146	BAE146200A 	1500266	EU 										RT ELEV A-FRAME	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND RT ELEVATOR A-FRAME, NR 2 UPPER BOLT CORRODED AND CRACKED AT THREAD RUN-OUT AREA. R	EPLACED BOLT. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700667	19951117	00667	EU 	1995	11	17	A6WR95018 	1	19951013	G	5400		PYLON 			BAG 	BAE146	BAE146200A 	1500266	EU 										NR 1	RIVETS POPPED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND THE HEADS POPPED OFF OF 2 RIVETS ON THE ANGLE BETWEEN RIBS 3 AND 4 ON THE CENTER BOX	 OF NR 1 PYLON. REPLACED THE RIVETS. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700668	19951117	00668	EU 	1995	11	17	A6WR95019 	1	19951013	G	5400		PYLON 			BAG 	BAE146	BAE146200A 	1500266	EU 										NR 2	RIVETS POPPED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND THE HEADS POPPED OFF OF THE FIRST 3 RIVETS ON THE ANGLE BETWEEN RIBS 3 AND 4 ON THE 	CENTER BOX OF NR 2 PYLON. REPLACED THE RIVETS. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700669	19951117	00669	EU 	1995	11	17	A6WR95020 	1	19951013	G	5400		PYLON 			BAG 	BAE146	BAE146200A 	1500266	EU 										NR 3	RIVETS POPPED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND THE HEADS POPPED OFF OF 2 RIVETS IN THE CENTER BOX FLOOR OF NR 3 PYLON. REPLACED TH	E RIVETS. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700670	19951117	00670	EU 	1995	11	17	A6WR95021 	1	19951013	G	5400		PYLON 			BAG 	BAE146	BAE146200A 	1500266	EU 										NR 4	RIVETS POPPED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND THE HEADS POPPED OFF OF 3 RIVETS ON THE ANGLE BETWEEN RIBS 3 AND 4 ON THE CENTER BOX	 OF NR 4 PYLON. REPLACED THE RIVETS. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700671	19951117	00671	EU 	1995	11	17	A6WR95022 	1	19951013	G	5710		BOLTS 			BAG 	BAE146	BAE146200A 	1500266	EU 										WING RIB 0-2	LOOSE 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND 47 LOOSE JO-BOLTS IN WING AND CENTER FUEL TANK AT RIB ZERO AND RIB 2, LEFT AND RIGHT	. TORQUE CHECKED BOLTS OK. INSPECTED BOLTS AND FOUND NO EVIDENCE OF CORROSION. OK TO CONTINUE IN SERVICE WITH REINSPE	CT AT 16,000 CYCLES IN SERVICE PER AVRO FAX JM/RJ0989-95. (X)				2	H	7	4 	4F			RT	A49EU 					 
1995111700672	19951117	00672	EU 	1995	11	17	A6WR95023 	1	19951013	G	5320	HC537H0655502	GUSSET 			BAG 	BAE146	BAE146200A 	1500266	EU 										FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND GUSSET PLATE ON LT FORWARD VESTIBULE FLOOR STRUCTURE CORRODED. REPLACED GUSSET PLAT	E.					2	H	7	4 	4F			RT	A49EU 					 
1995111700673	19951117	00673	EU 	1995	11	17	A6WR95024 	1	19951016	G	5320	HC537H0650002	INTERCOSTAL 			BAG 	BAE146	BAE146200A 	1500266	EU 										LT FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND 2ND INTECOSTAL FROM OUTBOARD IN LT FORWARD VESTIBULE BETWEEN FRAMES 15 AND 18 CORROD	ED. ALSO, FOUND SUPPORT MEMBER ATTACHED TO INTERCOSTAL CORRODED. REPLACED INTERCOSTAL AND SUPPORT MEMBER. REFERENCE O	PERATOR CONTROL NR 95ZZZX6249. (X)				2	H	7	4 	4F			RT	A49EU 					 
1995111700674	19951117	00674	EU 	1995	11	17	A6WR95025 	1	19951016	G	5320	HC537H0480000	CHANNEL 			BAG 	BAE146	BAE146200A 	1500266	EU 										FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND Z-CHANNEL, FRAME 15, IN FORWARD VESTIBULE UNDER GALLEY FLOOR CORRODED. REPLACED Z-C	HANNEL. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700675	19951117	00675	EU 	1995	11	17	A6WR95026 	1	19951016	G	5320	HC537H0650006A	INTERCOSTAL 			BAG 	BAE146	BAE146200A 	1500266	EU 										RT FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND 2ND INTERCOSTAL FROM OUTBOARD IN RT FORWARD VESTIBULE, BETWEEN FRAMES 15 AND 18, COR	RODED. REPLACED INTERCOSTAL. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700676	19951117	00676	EU 	1995	11	17	A6WR95027 	1	19951016	G	5320	HC537H0651004	MEMBER 			BAG 	BAE146	BAE146200A 	1500266	EU 										RT FWD VESTIBULE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING STRUCTURAL INSPECTION, FOUND SUPPORT MEMBER FOR 2ND INTERCOSTAL FROM OUTBOARD IN RT FORWARD VESTIBULE, BETWEEN FR	AMES 15 AND 18, CORRODED. REPLACED SUPPORT MEMBER. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700677	19951117	00677	EU 	1995	11	17	A6WR95028 	1	19951016	G	5315		BEAM 			BAG 	BAE146	BAE146200A 	1500266	EU 										FLOOR SUPPORT	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	800DV					E2062				DURING STRUCTURAL INSPECTION, FOUND FRAME 15 FLOOR SUPPORT BEAMS (3 EACH) CORRODED. REPAIRED IAW AVRO REPAIR DRAWING HC	537H9257 AND FAX GCB/RJ1037-95. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700678	19951117	00678	EU 	1995	11	17	A6WR95029 	1	19951016	G	5330		SKIN 			BAG 	BAE146	BAE146200A 	1500266	EU 										FRAME 9-11	DAMAGED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				STRUCTURAL INSPECTION FOUND SKIN ON LT SIDE OF FUSELAGE PUSHED IN ON EITHER SIDE OF FRAMES, FROM FRAME 9 TO FRAME 11. D	AMAGE IS BETWEEN 6 INCHES AND 15 INCHES BELOW SKIN LAP JOINT BELOW COCKPIT WINDOWS. DRESSED OUT DENTS IAW AVRO FAX GCB/	RJ1172-95. INITIATED REPEAT DETAILED VISUAL INSPECTION OF AREA AT 2,000 CYCLE INTERVALS. (X)				2	H	7	4 	4F			RT	A49EU 					 
1995111700679	19951117	00679	EU 	1995	11	17	A6WR95030 	1	19951017	G	2820	WX1500	BARRIER 			BAG 	BAE146	BAE146100A 	1500260	EU 										CENTER TANK	SEAM OPEN 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR				FVB5093	E1068				DURING C-CHECK, FOUND CENTER FUEL TANK VAPOR BARRIER FORWARD RT SEAM DETERIORATED OPEN. REPLACED VAPOR BARRIER. (X)						2	H	7	4 	4F			RT	A49EU 					 
1995111700680	19951117	00680	EU 	1995	11	17	A6WR95031 	1	19951017	G	2711	HC270H0134018	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										LT AIL TRIM	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND LT AILERON TRIM CABLE CIRCUIT CABLES CORRODED. REPLACED CABLES. (X)						2	H	7	4 	4F			RT	A49EU 					 
1995111700681	19951117	00681	EU 	1995	11	17	A6WR95032 	1	19951017	G	7600	HC760H0003090	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										NR 2 ENG THRUST	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 2 ENGINE THRUST CONTROL CABLE CORRODED NEAR PULLEY AT WING LEADING EDGE. REPLACED CABLE. (X)						2	H	7	4 	4F			RT	A49EU 					 
1995111700682	19951117	00682	EU 	1995	11	17	A6WR95033 	1	19951017	G	2711	HC270H0134008	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										RT AIL TRIM	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND RT AILERON TRIM CABLES CORRODED AT CENTER WING ROOT AREA. REPLACED CABLES. REFERENCE CONTROL NR 	95ZZZX6262. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700683	19951117	00683	EU 	1995	11	17	A6WR95034 	1	19951017	G	2721	HC70H0042038	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										RUDDER TRIM	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND RUDDER TRIM CABLES AT CENTER WING ROOT AREA CORRODED. REPLACED CABLES. REFERENCE OPERATOR CONTRO	L AND NR 95ZZZX6261. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700684	19951117	00684	EU 	1995	11	17	A6WR95035 	1	19951017	G	2897	HC760H000C034	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 1	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 1 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. ALL FOUR CABLES FROM FUSELAGE FRAME 18	 TO L.P. COCK. REPLACED CABLES. REFERENCE OPERATOR CONTROL NR 95ZZZX6258, NR 95ZZZX6259, AND NR 95ZZZX6260. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700685	19951117	00685	EU 	1995	11	17	A6WR95036 	1	19951017	G	2897	HC760H0003036	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 2	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 2 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT AT CENTER AREA OF LT WING CORRODED. REPLACED CAB	LES. REFERENCE CONTROL NR 95ZZZX6255, NR 95ZZZX6256, AND NR 95ZZZX6257. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700686	19951117	00686	EU 	1995	11	17	A6WR95037 	1	19951017	G	2720	HC270H0041052	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										RUDDER CONTROL	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND MAIN RUDDER CONTROL CABLES CORRODED AFT OF REAR PRESSURE BULKHEAD. REPLACED CABLES. REFERENCE OP	ERATOR CONTROL NR 95ZZZX6254. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700687	19951117	00687	EU 	1995	11	17	A6WR95038 	1	19951017	G	2730	HC270H0041030	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										RT ELEV CONTROL	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND RT ELEVATOR MAIN CONTROL CABLES CORRODED AFT OF REAR PRESSURE BULKHEAD. REPLACED CABLES. REFEREN	CE CONTROL NR 9ZZZX6253. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700688	19951117	00688	EU 	1995	11	17	A6WR95039 	1	19951017	G	2730	HC270H0041042	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										LT ELEV CONTROL	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND LT ELEVATOR MAIN CONTROL CABLES CORRODED AFT OF REAR PRESSURE BULKHEAD. REPLACED CABLES. REFEREN	CE CONTROL NR 95ZZZX6252. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700689	19951117	00689	EU 	1995	11	17	A6WR95040 	1	19951017	G	2897	HC760H0003008	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 3	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 3 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. FOUR CABLES FROM FUSELAGE FRAME 18 TO 	L.P. COCK. REPLACED CABLES. REFERENCE CONTROL NR 95ZZZX6263, NR 95ZZZX6264, AND NR 95ZZZX6265. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995112400271	19951124	00271	EU 	1995	11	24	A6WR95041 	1	19951017	G	7160	2063010R16	FAN FRAME 			BAG 	BAE146	BAE146100A 	1500260	EU 										NR 2 ENGINE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND CORROSION ON NR 2 ENGINE MAIN FAN FRAME ON TRAILING EDGES OF STRUTS AND AT AFT FIREPROOF BULKHEAD 	SPLIT-LINE. REMOVED CORROSION, TREATED AND PAINTED AFFECTED SURFACES. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995112400272	19951124	00272	EU 	1995	11	24	A6WR95042 	1	19951017	G	7160	2063010R16	FAN FRAME 			BAG 	BAE146	BAE146100A 	1500260	EU 										NR 1 ENGINE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND CORROSION ON NR 1 ENGINE MAIN FAN FRAME ON TRAILING EDGES OF STRUTS. REMOVED CORROSION, TREATED A	ND PAINTED AFFECTED SURFACES. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700690	19951117	00690	EU 	1995	11	17	A6WR95043 	1	19951017	G	7160	204315005	FAN SHROUD 			BAG 	BAE146	BAE146100A 	1500260	EU 										NR 1 ENGINE	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 1 ENGINE FAN SHROUD ASSY TO HAVE CORROSION AND AREAS MISSING PLASMA COATING. REPLACE FAN SHROU	D ASSY. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700691	19951117	00691		1995	11	17	A6WR95044 	4	19951017	G	2565	A3060195102	LIGHT ASSY 		D31002 	BAG 	BAE146	BAE146100A 	1500260	EU 										EVAC SLIDE	DEFECTIVE 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR				0091	E1068				DURING C-CHECK, FOUND AFT SERVICE DOOR EVAC SLIDE LAMP CIRCUIT AMPERAGE LOW DURING LAMP HARNESS TEST. REPLACE LIGHT ASS	Y. CIRCUIT TESTED WITHIN REQUIRED AMPERAGE PARAMETERS. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700692	19951117	00692		1995	11	17	A6WR95045 	4	19951017	G	2565	P4010014110	BATTERY 		D31002 	BAG 	BAE146	BAE146100A 	1500260	EU 										EVAC SLIDE	FAILED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR				032868	E1068				DURING C-CHECK, FORWARD PASSENGER DOOR EVACUATION SLIDE BATTERY FAILED EFFICIENCY CHECK DUE TO LOW VOLTAGE. REPLACED BA	TTERY. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700693	19951117	00693	EU 	1995	11	17	A6WR95046 	1	19951017	G	2897	HC760H0003014	WIRE 			BAG 	BAE146	BAE146100A 	1500260	EU 										FUEL COCK NR 4	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND NR 4 ENGINE LOW PRESSURE FUEL COCK CABLE CIRCUIT CORRODED. FOUR CABLES FROM FUSELAGE FRAME 18 TO 	L.P. COCK. REPLACED CABLES. REFERENCE CONTROL NR 95ZZZX6266, NR 95ZZZX6267, AND NR 95ZZZX6268. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700694	19951117	00694	EU 	1995	11	17	A6WR95047 	1	19951017	G	2731	HC270H0042010	CONTROL CABLE 			BAG 	BAE146	BAE146100A 	1500260	EU 										ELEVATOR TRIM	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING C-CHECK, FOUND ELEVATOR TRIM CABLE CIRCUIT IN CENTER WING AREA CORRODED. REPLACED CABLES. REFERENCE OPERATOR CO	NTROL NR 95ZZZX6269. (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700695	19951117	00695	EU 	1995	11	17	A6WR95048 	1	19951017	G	2710	HC576C0140200	BRACKET 			BAG 	BAE146	BAE146100A 	1500260	EU 										AIL SERVO TAB	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	2FOR					E1068				DURING COMPLIANCE WITH SB 57-47, FOUND 2 EACH AILERON SERVO TAB BRACKETS CORRODED IN SPOT FACE AREA. REPLACED BRACKETS.	 (X)					2	H	7	4 	4F			RT	A49EU 					 
1995111700696	19951117	00696	EU 	1995	11	17	A6WR95049 	1	19951017	G	5510	HC551B0063002	BRACKET 			BAG 	BAE146	BAE146200A 	1500266	EU 										LT HORIZ STAB	CORRODED 	B			A6WR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	31	880DV					E2062				DURING ACCEPTANCE INSPECTION, FOUND EXFOLIATION CORROSION ON LT ELEVATOR NR 2 HINGE A-FRAME BRACKET. REPLACED BRACKET. 	 (X)					2	H	7	4 	4F			RT	A49EU 					 
1995122200439	19951222	00439	CE 	1995	12	22	AKG142C 	1	19951113	G	3040	2026252	CONNECTOR 			BEECH 	200 	200BEECH 	1152920	CE 										WINDSHIELD HEAT	BURNED 	B			AKGR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	05	327RK	1847 				BB335				PILOTS WINDSHIELD HEAT WAS NOT WORKING. FOUND THE PINS IN CANNON PLUG J195 FOR WIRES H15A8 AND H23A8 BURNED. AFTER LOO	KING UP THE SPECIFICATIONS FOR THE PINS IN THE MANUFACTURER'S MANUAL, IT WAS DETERMINED THE SYSTEM CURRENT DEMAND IS RIG	HT AT THE MAX CURRENT LIMIT LISTED FOR THE PIN IN FREE AIR. A NON-PERMANENT INLINE SPLICE OR LARGER PIN CANNON PLUG MUS	T BE USED TO CORRECT THIS PROBLEM.			1	L	7	2 	4T				A24CE 					 
1996061300061	19960613	00061	WP 	1996	6	13	ARWR960699 	1	19950516	G	5330		SKIN 			DOUG 	DC8 	DC862 	3021970	WP 										CARGO DOOR JAMB	CORRODED 	B			ARWR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FORWARD CARGO COMPARTMENT, AFT CARGO DOOR JAMB AREA, FORWARD SIDE HAS CORROSION BETWEEN FUSELAGE S	KIN AND SEAL DEPRESSOR. REPAIRED IAW DAC FAX 293907 AND 297170. (X)					2	L	7	4 	4F				4A25 					 
1995102000110	19951020	00110	EA 	1995	10	20	BIER950022 	2	19950925	G	8530	74541	VALVE 			GULSTM	AA5 	AA5B 	3960105	SO 	LYC 	O360 	O360A4K 	41514	EA 					NR 1 CYL EXH	BROKEN 	B			BIER	K				NONE 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		IN	INSP/MAINT 	1			EA	21	28805		600 			AA5B0824	62494336A			PILOT REPORTED ROUGH RUNNING ENGINE. COMPRESSION CHECK REVEALED 0/80 ON NR 1 CYLINDER. FURTHER INSPECTION REVEALED EXH	AUST VALVE BROKEN - HALF HEAD MISSING. REPLACED CYLINDER/PISTON ASSEMBLY WITH REBUILT UNIT. (X)					1	L	7	1 	3O	3	O		A16EA 	E286				 
1995102000111	19951020	00111	SO 	1995	10	20	BTVR91595 	1	19950915	G	3230	159H10002687LGD4	LINE 			GULSTM	G159 	G159 	3952202	SO 										MLG DRAG BRACE	SEPARATED 	B			BTVR	O				OTHER 				J	K		WARNING INDICATION 	FLUID LOSS 		DE	DESCENT 	1			GL	23	812CC					129				UPON DESCENT INTO PTK, UPON EXTENSION OF THE SPEED BRAKES, ALL HYDRAULIC SYSTEM FLUID WAS LOST. THE FLIGHT CREW EXTENDE	D THE LANDING GEAR BY USING THE EMERGENCY GEAR EXTENSION SYSTEM AND AN UNEVENTFUL LANDING WAS MADE AT PTK. THE FLIGHT C	REW DECLARED AN EMERGENCY WITH AIR TRAFFIC CONTROL PRIOR TO LANDING. (X)				2	L	7	2 	4T				1A17 					 
1995080400557	19950804	00557	SO 	1995	8	4	BTVR950621 	1	19950621	G	3610	1159P419813	DUCT 			GULSTM	G1159 	GIV 	3980115	SO 										LT PYLON	CHAFED 	B			BTVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	23	1901M	3631 			F69246	1039				DURING A NON-ROUTINE, UNSCHEDULED REMOVAL OF THE LEFT ENGINE THRUST STRUT, THE L.P. AIR DUCT MENTIONED WAS REMOVED. AFT	ER REMOVAL, A HOLE WAS DISCOVERED IN THE DUCT CHAFED BY THE AFT THRUST STRUT ATTACH BOLT HEAD (PN GAB511EB14D40). THIS 	DEFECT WAS IN SUCH A LOCATION THAT A STANDARD VISUAL INSPECTION WOULD NOT HAVE DISCOVERED THE DEFECT. (X)				2	L	7	2 	4F			RT	A12EA 					 
1996052300240	19960523	00240	SO 	1996	5	23	CA950504022 	1	19950315	G	2810	561504	HEADER TANK 			AYRES 	S2 	S2RT34NORMAL	0970106	SO 										LOWER SIDE	CORRODED 	W				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CA			1902 								(CAN)FUEL STAIN NOTICED ON LOWER SIDE OF HEADER. HEADER TANK REMOVED, FOUND CORRODED THROUGH FROM INSIDE WITH SUBSTANTIA	L AMOUNT OF DIRT, SMALL STONES, PRC (PROPLETS & RUBBER PIECES). THIS CORROSION WAS FOUND ON TWO OTHER SIMILAR AIRCRAFT (	S/N T34-013 AND T34-014). NEW HEADER TANKS P/N 9104-32 INSTALLED. *NOTE - NEW HEADER TANK HAS A LARGER TAPERED SUMP.				1	L	7	1 	3T				A3SW 					 
1996052300242	19960523	00242	NM 	1996	5	23	CA950621029 	1	19950621	G	2435	23088	STARTER 	LUCAS 		DHAV 	DHC8 	DHC8* 		NM 										CONTROL BOX	SCREWS MISSING 	W				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CA						0					(CAN)ALL FLEET STARTER-GENERATORS CHECKED AND FOUND WITH LOOSE OR MISSING SCREWS ON THE CONTROL BOX CONNECTOR. SCREWS WE	RE TORQUE SEALED BUT NOT TORQUED.					2	H	7	2 	4T			RT	A13NM 					 
1996053100008	19960531	00008	GL 	1996	5	31	CA950829002 	2	19950707	G	7230	6877410	COMPRESSOR VANE 								ALLSN 	250C 	250C20B 	03013	GL 					3RD STAGE	FAILED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA								CAE831009			(CAN)SEVERE EROSION APPEARS TO HAVE CAUSED ONE OR MORE VANES ON THE THIRD STAGE TO SEPARATE FROM ROOT ATTACHMENT BRAZE J	OINTS. SEPARATED VANES CAUSED MASSIVE SUBSEQUENT DAMAGE TO LATER STAGES OF VANES AND BLADES.										3	U			E4CE				 
1996060600855	19960606	00855	GL 	1996	6	6	CA950913203 	1	19950818	G	5511	77210032	STAB REAR SPAR 	? 	772100122 	NAMER 	T6 	HARVARD4 	6400430	GL 										OUTBOARD HINGE	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			8133 			0					(CAN)DURING INSPECTION THE LEFT OUTBOARD HINGE AREA ON THE REAR SPAR, IT WAS FOUND TO HAVE A ONE INCH CRACK ON THE LOWER	 BOLT HOLE AIRCRAFT REPAIRED AND SUBMITTER STATES THAT FOR EASIER INSPECTION THIS AR EA WILL NO LONGER BE PAINTED.					1	L	7	1 	3R				EXPA1L71					 
1996060600856	19960606	00856	SW 	1996	6	6	CA950918020 	1	19950908	G	2910	2781032095	LINE 			SWRNGN	SA226 	SA226TC 	8780404	SW 										HYD SYS	CRACKED 	W				A				UNSCHED LANDING 				J	K		WARNING INDICATION 	FLUID LOSS 		DE	DESCENT 	1			CA											(CAN)BOTH HYDRAULIC FAILURE LIGHTS ON DURING DESCENT. ON APPROACH NOSE LAND GEAR DID NOT INDICATE DOWN AND LOCKED. CREW 	HELD, AND AFTER 20 MINUTES LIGHT ON. AIRCRAFT LANDED OK. HYDRAULIC LINE FROM POWER PACK TO GROUND SERVICE FITTING FOUND 	CRACKED AT RADIUS.				2	L	7	2 	4T			RT	A8SW 					 
1999032600119	19990326	00119	WP 	1999	3	26	CA950928001 	1	19950310	G	2821		FILTER 			HUGHES	369 	369D 	4470706	WP 	ALLSN 	250C 	250C20B 	03013	GL 					FUEL SYSTEM	CONTAMINATED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN) SUBMITTER SUGGESTS THAT THEY CANNOT COMPLY WITH THE FLIGHT MANUAL REQUIREMENT TO SAMPLE FUEL AT THE ENGINE FUEL FI	LTER FOR CONTAMINANTS AS REQUIRED BY HUGHES PRE-FLIGHT. FIELD EXPERIENCE HAS INDICATED THAT THE ENGINE FUEL FILTER SAMP	LE POINT IS VITAL. WHEN USING JET 'A' FUEL, THE ENGINE FUEL FILTER BOWL WILL COLLECT WATER THAT WAS NOT DETECTED AT THE	 FUEL CELL DRAIN. MANUFACTURER CONTACTED AND FLIGHT MANUAL WILL BE CORRECTED.			1	G	7	1 	3U	3	U		H3WE 	E4CE				 
1996062000779	19960620	00779	CE 	1996	6	20	CA951005019 	1	19950921	G	3222	34233	FORK 	EDOFLOATS 	5972790 	CESSNA	185 	A185E 	2072818	CE 										NLG LT SIDE	BROKEN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA						118					(CAN)AIRCRAFT WAS BEING PREPARED FOR PAINTING WHEN IT WAS FOUND THAT THE NOSE WHEEL FORK WAS CRACKED. UPON CLOSER INVEST	IGATION IT WAS FOUND TO BE TOTALLY BROKEN. UNIT REPLACED WITH A SERVICEABLE ONE AND A IRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3O				3A24 					 
1996070800001	19960708	00001	CE 	1996	7	8	CA951011001 	1	19950926	G	3232	08940011	ACTUATOR 			CESSNA	340 	340A 	2076405	CE 										GR DOOR	MT HOLE DEFECT 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)RIGGING OF GEAR DOOR FOUND DIFFICULT. ACTUATOR ATTACHMENT BOLT HOLE ON THE AIRFRAME FOUND ELONGATED. BULKHEAD REPAI	RED.					1	L	7	2 	3O				3A25 					 
1996071000420	19960710	00420	NM 	1996	7	10	CA951018023 	1	19951004	G	5347	AN4	AN BOLT 	PIPER 		PIPER 	PA60 	PA60600 	7106001	NM 	LYC 	O540 	IO540K1F5 	41532	EA 					SEAT FORK BACK	SHEARED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA						0		L1345348A			(CAN)SEAT BACK FAILED ONE SIDE. FOUND BOLT HAD SHEARED AN4 BOLT. OTHER SEAT BACK BOLTS CHECKED AND FOUND SERVICEABLE. BO	LT REPLACED WITH SERVICEABLE ONE.					1	M	7	2 	3O	3	O	RT	A17WE 	1E4				 
1996071800694	19960718	00694	NE 	1996	7	18	CA951026017 	2	19951018	G	7313		FUEL TUBE 								PWA 	PW120 	PW127 		NE 					NR5 FUEL NOZZLE	LEAKING 	W				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			CA			2969 					127079			(CAN)IN CRUISE THE #1 ENGINE PARAMETERS BEGAN TO DECREASE, AND THE PILOT DIVERTED THE AIRCRAFT TO AN ALTERNATE. THE ENGI	NE WAS SHUTDOWN ON APPROACH AND AN UNEVENTFUL LANDING WAS CARRIED OUT. POST FLIGHT IN SPECTION FOUND A FUEL TRANSFER TUB	E LEAKING ON #5 FUEL NOZZLE. THE PACKING WAS REPLACED.									4	T			E20NE				 
1996071800695	19960718	00695	NE 	1996	7	18	CA951026018 	2	19951022	G	7313		PACKING 								PWA 	PW120 	PW127 		NE 					NR13 FUEL NOZZLE	SPLIT 	W		A		E				ENGINE SHUTDOWN 				R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			CA			5431 					127037			(CAN)IN CRUISE THE NR 2 ENGINE TORQUE DECREASED TO 40 PERCENT. THE POWER LEVER WAS RETARDED AND THE EEC WAS RESET. THE	 ENG TORQUE DECREASED TO ZERO FOLLOWED BY AN ENG AUTOFEATHER, BUT THE ENG CONTINUED TO RUN. ON APP THE FIRE WARNING LIG	HT ILLUMINATED AND EXTINGUISHED. SHORTLY AFTER THE NACELLE OHEAT LIGHT ILLUMINATED. THE ENG WAS SHUTDOWN AND THE NAC O	VERHEAT LIGHT EXTINGUISHED. AN UNEVENTFUL SINGLE ENG LANDING WAS CARRIED OUT. POST FLIGHT INSP FOUND A FUEL TRANSFER T	UBE PACKING SPLIT ON NR 13 FUEL NOZ AND PINCHED PACKING ON THE NR 4 FUEL NOZZLE.							4	T			E20NE				 
1996071800697	19960718	00697	SW 	1996	7	18	CA951027007 	1	19951019	G	5711		SPAR 	BLANCA 		BBAVIA	7 	7GCBC 	1220601	SW 										L/H WING	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			1591 			0					(CAN)SUBJECT SPAR INDICATED IRREGULAR LINES ACROSS THE GRAIN AT 163 INCHES FROM THE ROOT END. FORE AND AFT SPAR FACES CL	EANED AND SANDED & THE VERTICAL LINES REMAINED. PRESSURED APPLIED TO THE SPAR EACH SI DE INDICATED SLIGHT MOVEMENT. A HA	RD DOWNWARD PRESSURE FORCE CAUSED THE SPAR TO CRACK ALONG THE APPARENT FAULT LINES. SUBMITTER ENCLOSED A COPY OF A PAGE 	TAKEN FROM THE WOOD ENCYCLOPEDIA WHICH DESCRIBES COMPRESSION FAILURES IN WOOD. SUBMITTER SUGGESTS THAT THIS COULD HAVE B	EEN CAUSED BY GROUND CONTACT OF THE WING TIP, SOMETIME IN THE AIRCRAFTS HISTORY.		1	H	7	1 	3O			NC	A759 					 
1996071800699	19960718	00699	EA 	1996	7	18	CA951027010 	2	19950910	G	7230		BEARING 								PWA 	PT6 	PT6A65B 	52043	EA 					NR 1	DISTRESSED 	W		A		E				ENGINE SHUTDOWN 				M	O		OVER TEMP 	OTHER 		NR	NOT REPORTED 	1			CA			16996					32165			(CAN)THE #1 ENGINE WAS SHUTDOWN AFTER A SERIES OF LOUD BANGS WERE HEARD AND ITT INCREASED TO 975 DEGREES C.INITIAL INSPE	CTION FOUND THE GAS GENERATOR SEIZED THOUGH THE POWER SECTION WAS FREE. THE ENGINE WAS SENT TO R&O. INVESTIGATION OF TH	E ENGINE REVEALED #1 BEARING DISTRESS.									4	T			E4EA				 
1996072300002	19960723	00002	NE 	1996	7	23	CA951027011 	2	19951021	G	7260		AGB DRIVE 								PWA 	JT15 	JT15D1 	52060	NE 					ASSORY GEARBX	DE-COUPLED 	W				E				ENGINE SHUTDOWN 				X			ENGINE FLAMEOUT 			CR	CRUISE 	1			CA								77112			(CAN)IN CRUISE THE CREW HEARD A LOUD BANG FOLLOWED BY A FLAME OUT OF #1 ENGINE. THE PILOT SECURED THE ENGINE AND PERFORM	ED AN UNEVENTFUL SINGLE ENGINE LANDING AT DESTINATION. POST FLIGHT INSPECTION REVEALE D A DE-COUPLING OF THE DRIVE TO TH	E ACCESSORY GEARBOX (AGB). THE ENGINE HAD UNDERGONE AN HOT SECTION INSPECTION (H.S.I.) NINE HOURS PRIOR TO THIS AGB DE-C	OUPLE.								4	F			E1NE				 
1996071000421	19960710	00421	CE 	1996	7	10	CA951030001 	1	19951023	G	2720	S16752	BEARING HALF 			CESSNA	150 	152 	2071835	CE 										RUD PEDAL SHAFT	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			5969 								(CAN)ROUTINE MAINTENANCE FOUND THE UPPER HALF OFTHE PLASTIC RUDDER BEARING FOR THE RUDDER PEDAL CROSS SHAFT CRACKED IN H	ALF.					1	H	7	1 	3O			NT	3A19 					 
1996080200484	19960802	00484	NE 	1996	8	2	CA951102007 	2	19950616	G	7210	310799601	HOUSING 	PWA 							PWA 	118 	PW118 		NE 					RGB MOUNT PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			11863			9B716		115023			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STE EL). THIS CONDITION MAY RESULT IN 	CRACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CAL	LS FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL	 PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996080200494	19960802	00494	EA 	1996	8	2	CA951106203 	1	19951020	G	2710	82700568S001	CONTROL CABLE 			DHAV 	DHC8 	DHC8311 	1386006	EA 										RT AILERON	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			9888 								(CAN) RIGHT AILERON LOWER CABLE FOUND WORN AT PULLEY AT STA YW190. THIS CONDITION NOT VISIBLE WITH GUST LOCK ON AND AILE	RONS IN NEUTRAL.					2	H	7	2 	4T			RT	A13NM 					 
1996080200497	19960802	00497	EA 	1996	8	2	CA951108006 	1	19951031	G	2420	82450067001	BRACKET 			DHAV 	DHC8 	DHC8311 	1386006	EA 										AC CB BOX	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			8801 								(CAN)CIRCUIT BREAKER BRACKET FOUND CRACKED ALLOWING THE CIRCUIT BREAKERS AND WIRING TO COME LOOSE IN THE AC CONTACTOR BO	X.					2	H	7	2 	4T			RT	A13NM 					 
1996080200500	19960802	00500	EA 	1996	8	2	CA951108010 	1	19951030	G	2710	82700568S001	CONTROL CABLE 			DHAV 	DHC8 	DHC8311 	1386006	EA 										AILERON	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			8801 								(CAN) RIGHT WING AILERON LOWER CABLE FOUND WORN AT PULLEY STA YW190.						2	H	7	2 	4T			RT	A13NM 					 
1996080200501	19960802	00501	GL 	1996	8	2	CA951108013 	2	19951021	G	7250	6878426	NOZZLE 	ALLSN 	6898734 						ALLSN 	250C 	250C20 	03013	GL 					2ND STAGE BAND	CRACKED 	W				K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			CA						CAT38622		CAE823494			(CAN)ENGINE WAS SENT IN FOR COMPLAINT OF LOW POWER. THE LOG BOOK INDICATES 3098 HOURS SINCE NEW. ENGINE WAS TESTED AND W	AS FOUND TO HAVE A RUB AND VIBRATION. UNABLE TO COMPLETE TEST TO CONFIRM LOW POWER. ON DISASSEMBLY THE SECOND STAGE NOZZ	LE WAS FOUND TO HAVE A CIRCUMFERENTIAL CRACK EXTENDING 80 PERCENT AROUND THE OUTER BAND ADJACENT TO THE FIRST STAGE BLAD	E PATH.								3	U			E4CE				 
1996080200505	19960802	00505	SO 	1996	8	2	CA951108017 	1	19951030	G	5610	9688401	BRACKET 			PIPER 	PA32 	PA32R300 	7103213	SO 										WINDOW	CORRODED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			3030 								(CAN)BADLY LEAKING WINDOW CAUSED THE INSULATION TO REMAIN DAMP AND IN TURN THE BRACKET ASSEMBLY TO CORRODE. BRACKET REPL	ACED AND INSULATION STRIPPED OUT AND REPLACED. WINDOWS REMOVED AND RESEALED AS PER PI PER SERVICE BULLETIN.					1	L	7	1 	3O				A3SO 					 
1996080800763	19960808	00763	NE 	1996	8	8	CA951108026 	2	19950616	G	7210	310799601	RGB HOUSING 	PWA 							PWA 	118 	PW118 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			4631 			9B716		115021			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STE EL). THIS CONDITION MAY RESULT IN 	CRACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CAL	LS FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL	 PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996080800764	19960808	00764	NE 	1996	8	8	CA951108027 	2	19950616	G	7210	310799601	RGB HOUSING 	PWA 							PWA 	118 	PW118 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			3228 			1C569		115030			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STE EL). THIS CONDITION MAY RESULT IN 	CRACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CAL	LS FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL	 PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996080800765	19960808	00765	NE 	1996	8	8	CA951108028 	2	19950616	G	7210	311116401	RGB HOUSING 	PWA 							PWA 	118 	PW118 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			14843			7C748		115263			REDUCTION GEAR BOX MOUNT PAD WORN											4	T			E20NE				 
1996080800766	19960808	00766	NE 	1996	8	8	CA951108029 	2	19950616	G	7210	310631001	RGB HOUSING 	PWA 							PWA 	120 	PW120A 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			14402			8B904		120027			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STE EL). THIS CONDITION MAY RESULT IN 	CRACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CAL	LS FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL	 PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996080800767	19960808	00767	NE 	1996	8	8	CA951108030 	2	19950616	G	7210	310631001	RGB HOUSING 	PWA 							PWA 	120 	PW120 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			8301 			9B675		120050			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STE EL). THIS CONDITION MAY LEAD TO CR	ACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CALLS	 FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL P	LATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996080800768	19960808	00768	NE 	1996	8	8	CA951108031 	2	19950616	G	7210	310623401	RGB HOUSING 	PWA 							PWA 	120 	PW120A 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			5676 			9B750		120066			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STE EL). THIS CONDITION MAY RESULT IN 	CRACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CAL	LS FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL	 PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996080800769	19960808	00769	NE 	1996	8	8	CA951108032 	2	19950616	G	7210	310960901	RGB HOUSING 	PWA 							PWA 	120 	PW120 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			12774			7C608		120658			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STE EL). THIS CONDITION MAY RESULT IN 	CRACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CAL	LS FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL	 PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNTS.							4	T			E20NE				 
1996080800770	19960808	00770	NE 	1996	8	8	CA951108033 	2	19950616	G	7210		RGB HOUSING 	PWA 							PWA 	PW120 	PW123 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			6998 					123126			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNT (STEE L). THIS CONDITION MAY RESULT IN C	RACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CALL	S FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL 	PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996081500004	19960815	00004	NE 	1996	8	15	CA951108034 	2	19950616	G	7210	310684902	RGB HOUSING 	PWA 							PWA 	PWA120	PW125B 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			9026 			1C290		124007			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STE EL). THIS CONDITION MAY RESULT IN 	CRACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CAL	LS FOR THE INSTALLATION OF A STEEL PLATE ON EACH MOUNTING PAD TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO THE STEEL	 PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996081500005	19960815	00005	NE 	1996	8	15	CA951108035 	2	19950616	G	7210	310997701	RGB HOUSING 	PWA 							PWA 	PWA120	PW125B 		NE 					MOUNTING PAD	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			10093			1D313		124181			(CAN)THE SURFACE OF THE REDUCTION GEARBOX (RGB) MOUNTING PADS BECOME WORN DURING ENGINE OPERATION BECAUSE THE MATERIAL (	MAGNESIUM ALLOY) IS SOFTER THAN THE MATING SURFACE OF THE AIRFRAME ENGINE MOUNTS (STEEL). THIS CONDITION MAY RESULT IN C	RACKING ADJACENT TO THE HELICOIL HOLES. PRATT & WHITNEY SERVICE BULLETIN (SB) #21423 ADDRESSES THIS PROBLEM. THE SB CALL	S FOR THE INSTALLATION OF A STEEL PLATE ON EACH OF THE MOUNTING PADS TO PROTECT THE SURFACE OF THE MOUNTING PAD. ALSO TH	E STEEL PLATE HAS A LARGER CONTACT AREA WITH THE AIRFRAME ENGINE MOUNT.							4	T			E20NE				 
1996071800702	19960718	00702	EA 	1996	7	18	CA951109003 	1	19951030	G	2710	82700564A001	CONTROL CABLE 			DHAV 	DHC8 	DHC8311 	1386006	EA 										BOTH AILERONS	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			8801 								(CAN) BOTH LEFT AND RIGHT WING AILERON LOWER CABLES WERE WORN BY PULLY AT YW400.						2	H	7	2 	4T			RT	A13NM 					 
1996080800775	19960808	00775	CE 	1996	8	8	CA951110003 	1	19951031	G	3211	05411211	SUPPORT 			CESSNA	172 	172 	2072402	CE 										MLG HOLE AFT	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			2855 								(CAN)CRACK FOUND DURING ANNUAL INSPECTION.						1	H	7	1 	3O			NT	3A12 					 
1996080800778	19960808	00778	SW 	1996	8	8	CA951110006 	1	19951023	G	3230	NAS110423D	BOLT 			SWRNGN	SA226 	SA226TC 	8780404	SW 										LH MLG	BENT 	W				L	O			ABORTED APPROACH 	OTHER 			J	O		WARNING INDICATION 	OTHER 		AP	APPROACH 	1			CA											(CAN)LH MLG WOULD NOT EXTEND. INSPECTION FOUND DRAG STRUT HUNG UP ON DOWN ASSIST SPRING CABLE ROD END BOLT HEAD. AT PREV	IOUS INSTALLATION THE CLEARANCE WAS SUCH THAT THE CLOSE PROXIMITY OF THE UPLOCK ASSEM BLY CONTACTED THE BOLT HEAD. SB 32	-050 ADDRESSES THIS ISSUE AND INDICATES THAT INSTALLATION OF ORIGINAL BOLT WOULD ALLEVIATE THIS DIFFICULTY.				2	L	7	2 	4T			RT	A8SW 					 
1996080800786	19960808	00786	SO 	1996	8	8	CA951114010 	2	19950817	G	8520		ROLLER 	CONT 							CONT 	O520 	TSIO520NB 	17040	SO 					NR5 CHEEK CTWT	DAMAGED 	W				O				OTHER 				O			OTHER 			IN	INSP/MAINT 	1			CA				935 							(CAN)ENGINE RECEIVED AT R&O DUE TO METAL CONTAMINATION. INSPECTION DURING TEARDOWN REVEALED ONE COUNTERWEIGHT ROLLER (#5	 CHEEK) DISLODGED FROM COUNTERWEIGHT. COUNTERWEIGHT FOUND RETAINED TO CRANKSHAFT WITH ONLY ONE PIN. DISLODGED PIN HAD BE	COME JAMMED BETWEEN ONE CONNECTING ROD AND THE CRANKCASE, CAUSING EXTENSIVE DAMAGE TO THE CONNECTING ROD AND CRANKCASE.									3	O			E8CE				 
1996071800705	19960718	00705	EA 	1996	7	18	CA951114012 	1	19951030	G	2823	7442833	STUD 	HAMSTD 	7786863 	DHAV 	DHC8 	DHC8311 	1386006	EA 										VALVE TO MOTOR	SHEARED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA				114 		A95050010					(CAN)ONE OF TWO STUDS WHICH ATTACH SHUTOFF VALVE BODY TO THE VALVE MOTOR WAS FOUND SHEARED. FRACTURE OF STUD WAS JUST WH	ERE IT ENTERED CASTING OF MOTOR BODY. FOLLOW-UP INFO INDICATED THAT FAILED STUDS WERE EMBRITTLED, ONE STUD WAS TOO HARD 	AS PER MATERIAL HARDNESS. IN ADDITION, STUDS TO BE REPLACED WITH NAS1860CA12 WHICH IS NOT SUSEPTIBLE TO HYDROGEN EMBRITT	LEMENT AND CAN BE USED TO REPAIR HOUSINGS WHICH HAVE DAMAGED THREADS AS WELL AS A REPLACEMENT. IN ADDITION, CURRENT GASK	ET WILL BE REPLACED WITH SHIM.		2	H	7	2 	4T			RT	A13NM 					 
1996080800789	19960808	00789	SW 	1996	8	8	CA951116004 	1	19951114	G	5310	714771	TAIL POST 	BLANCA 		BBAVIA	8 	8GCBC 	1220803	SW 										BELOW RUD STOP	BROKEN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			4615 			22076					(CAN)TAIL POST BROKEN COMPLETELY THROUGH AT A LOCATION JUST BELOW THE RUDDER STOP PIN. SUBMITTER BELIEVES THAT THE TYPE 	OF OPERATION MAY HAVE CONTRIBUTED TO THE FAILURE - GLIDER TOW PLANE.					1	H	7	1 	3O				A21CE 					 
1996080800790	19960808	00790	SW 	1996	8	8	CA951116005 	1	19950717	G	3221	315436	SPRING LEAF 			BBAVIA	8 	8GCBC 	1220803	SW 										ALIGNMENT HOLE	BROKEN 	W				O				OTHER 				O			OTHER 			TX	TAXI/GRND HDL 	1			CA			400 								(CAN)DURING THE GROUND HANDLING THE PILOT OBSERVED THAT THE TAILWHEEL SPRINGS WERE BROKEN SINCE THE TAILWHEEL HAD NOTICE	ABLE SAG. THIS AIRCRAFT IS ONE OF A FLEET OF GLIDER TUGS. SUBMITTER STATES THAT THIS SEEMS TO BE A WEAKNESS WITH THIS T	YPE OF OPERATION.				1	H	7	1 	3O				A21CE 					 
1996080800793	19960808	00793	CE 	1996	8	8	CA951116008 	1	19951107	G	2810		TANK 			CESSNA	185 	A185F 	2072821	CE 										INSIDE TANK	FOD 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN) WHILE INSTALLING A NEW FUEL FILLER CAP FILLER KIT THE PRO SEALED INSPECTION PLATES WERE REMOVED AND WHAT LOOKED LI	KE A FACTORY PRC CLEANING TOOL WAS FOUND INSIDE THE FUEL TANK. TOOL REMOVED AND FOD CHECK COMPLETED.					1	H	7	1 	3O				3A24 					 
1996080800803	19960808	00803	SW 	1996	8	8	CA951116023 	1	19951107	G	6510	206040352001	SPRING 			BELL 	206 	206B 	1181511	SW 										T/R DRIVE	BROKEN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			3972 								(CAN)DURING INSPECTION OF THE T/R DRIVE SHAFT BEARING HANGERS IN ACCORDANCE WITH ASB 206-95-86RA, 2 SPRINGS WERE FOUND B	ROKEN.					1	G	7	1 	3U				H2SW 					 
1996080800804	19960808	00804	NE 	1996	8	8	CA951116025 	2	19950827	G	7250		BLADES 								PWA 	PT6 	PT6A42 	52043	NE 					NR 2 ENGINE	FRACTURED 	W				E				ENGINE SHUTDOWN 				O	J		OTHER 	WARNING INDICATION 		CR	CRUISE 	1			CA			3889 	900 				93722			(CAN)DURING CRUISE AT 13,000 FEET THE PILOT HEARD A LOUD BANG FOLLOWED BY TORQUE DROPPING TO "0". AN UNEVENTFUL SINGLE E	NGINE LANDING WAS MADE. POST FLIGHT INSPECTION REVEALED THE CAUSE OF THE INFLIGHT SHUTDOWN (IFSD) WAS DUE TO THE RELEASE	 OF 2 COMPRESSOR TURBINE BLADES DUE TO FRACTURED FIR TREE. ALL OTHER DAMAGE WAS SECONDARY.									4	T			E4EA				 
1996080800805	19960808	00805	NE 	1996	8	8	CA951116026 	2	19951024	G	7313		"O" RING PACKING								PWA 	PW120 	PW127 		NE 					FUEL NOZZLES	LEAKING 	W				E	F			ENGINE SHUTDOWN 	ACTIVATE FIRE EXT. 			R			PARTIAL RPM/PWR LOSS 			DE	DESCENT 	1			CA								127113			(CAN)IN CRUISE THE #1 ENGINE TORQUE DECREASED TO 67 PERCENT. DURING DESCENT, THE #1 ENGINE FIRE LIGHT ILLUMINATED. THE E	NGINE WAS SECURED AND THE FIRE BOTTLE WAS DISCHARGED. AN UNEVENTFUL SINGLE ENGINE LAN DING WAS MADE AT DESTINATION. POST	 FLIGHT INSPECTION FOUND FUEL LEAKING FROM THE #12 FUEL NOZZLE AREA. THE FUEL NOZZLE "O" RING PACKING WAS REPLACED AND T	HE AIRCRAFT WAS RETURNED TO SERVICE.								4	T			E20NE				 
1996071800706	19960718	00706	EA 	1996	7	18	CA951120003 	1	19951111	G	2710	82700565S001	CONTROL CABLE 			DHAV 	DHC8 	DHC8311 	1386006	EA 										LEFT AILERON	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			9179 								(CAN) LEFT AILERON CABLE FOUND 50 PERCENT WORN AT FAIRLEAD AT YW155.						2	H	7	2 	4T			RT	A13NM 					 
1996071800707	19960718	00707	EA 	1996	7	18	CA951120004 	1	19951111	G	2710	82700564S001	CONTROL CABLE 			DHAV 	DHC8 	DHC8311 	1386006	EA 										LT & RT AILERON	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			9178 								(CAN) BOTH LEFT AND RIGHT AILERON CABLES WERE FOUND WORN 40 TO 50 PERCENT AT PULLEY AT STA. YW404.						2	H	7	2 	4T			RT	A13NM 					 
1996071800708	19960718	00708	EA 	1996	7	18	CA951120006 	1	19951111	G	2710	82700567S001	CONTROL CABLE 			DHAV 	DHC8 	DHC8311 	1386006	EA 										AILERON	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			9179 								(CAN) DURING INSPECTION THE RIGHT AILERON CABLE WAS FOUND TO BE PARTIALLY WORN AT STA. YW170.						2	H	7	2 	4T			RT	A13NM 					 
1996071800709	19960718	00709	EA 	1996	7	18	CA951120007 	1	19951111	G	2760	82700503003	CONTROL CABLE 			DHAV 	DHC8 	DHC8311 	1386006	EA 										ROLL SPOILER	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			9179 								(CAN)LEFT WING ROLL SPOILER CABLE FOUND 50 PERCENT WORN AT STA. YW90 NEAR FAIRLEAD.						2	H	7	2 	4T			RT	A13NM 					 
1996081500692	19960815	00692	EA 	1996	8	15	CA951120013 	2	19951030	G	8530	77160	VALVE GUIDE 			CESSNA	172 	172N 	2072434	CE 	LYC 	O360 	O360A4M 	41514	EA 					NR3 CYL EXH	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			418 					L3225736A			(CAN) DURING DIFFERENTIAL COMPRESSION CHECK IT WAS FOUND THAT NR 3 CYLINDER HAD A SEVERE EXHAUST LEAK (20/80). AFTER RE	MOVAL AND INSPECTION OF THE NR 3 CYLINDER IT WAS REVEALED THAT THE EXHAUST VALVE GUIDE WAS CRACKED AND BADLY WORN AS A R	ESULT OF THE LONGITUDINAL CRACK. IT SEEMS LIKELY THIS CONDITION WAS CAUSED BY RUNNING THE ENGINE TOO LEAN. THE SAME CO	NDITION WAS ALSO FOUND ON NR 4 CYLINDER (0/80) DURING THE SAME TESTS.			1	H	7	1 	3O	3	O	NT	3A12 	E286				 
1996081500708	19960815	00708	EA 	1996	8	15	CA951122017 	2	19951010	G	8530	73938	VALVE 			PIPER 	PA32 	PA32R300 	7103213	SO 	LYC 	O540 	IO540K1G5 	41532	EA 					CYL HEAD EXH	BROKEN 	W				K				NONE 				E			VIBRATION/BUFFET 			DE	DESCENT 	1			CA			1212 					L1693748A			(CAN)PILOT REPORTED A ROUGH RUNNING ENGINE ON APPRAOCH. POST FLIGHT INVESTIGATION REVEALED ONE OF THE EXHAUST VALVES HAD	 FRACTURED AND SEPARATED FROM ITS STEM AND DESTROYED THE PISTON CROWN AND CYLINDER CA P. THE EXHAUST VALVES ON ALL CYLIN	DERS INDICATED A "TULIP" CONDITION. THE FUEL AND INDUCTION SYSTEMS WERE CLEANED AND INSPECTED AND ALL NEW STEEL CYLINDER	 ASSEMBLIES WERE INSTALLED.			1	L	7	1 	3O	3	O		A3SO 	1E4				 
1996081500713	19960815	00713	GL 	1996	8	15	CA951122023 	3	19951109	G	6111		PROPELLER 													MCAULY	1A90	1A90CF 	GL 	NR 2 BLADE	IMPROPER REPAIR 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)DURING LEADING EDGE DRESSING A DISCOLORATION WAS NOTICED. AN IMPROPER WELD REPAIR WAS CONFIRMED BY ETCHING SUSPECTE	D AREA, IT BECAME NOTICEABLY VISIBLE. WELD LOCATED ON #2 BLADE LEADING EDGE, 7/8" LON G CENTERED AT THE 23" STATION, 3/1	6" WIDE ON THRUST FACE.														5	N	P842	 
1996061900006	19960619	00006	NM 	1996	6	19	CA951122025 	1	19951103	G	5610		WINDOW 			BOEING	757 	75728A 	1384976	NM 										1ST OFFICER IR	CRACKED 	W				K				NONE 				O			OTHER 			CR	CRUISE 	1			CA											(CAN)OUTER PANE OF FIRST OFFICERS IR WINDOW CRACKED AT FL390. WINDOW REPLACED.						2	L	7	2 	4F			RT	A2NM 					 
1996081500716	19960815	00716	SO 	1996	8	15	CA951122031 	1	19951110	G	6120	78249024	PROP CONT UNIT 	HAMSTD 		EMB 	120 	EMB120RT 		SO 						HAMSTD	14RF	14RF9 	NE 	RGB	FAULTY 	W		A		K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			CA			6051 			851228			880130		(CAN) A FACTORY REPAIRED PROPELLER CONTROL UNIT (PCU) HAVING SERVICE BULLETINS 14RF-9-61-22, -26, -32, -34, -38, -43, -4	5, -51, -60, -61 INCORPORATED WAS INSTALLED ON THE #2 ENGINE DURING A 400 HOURS/400 CYCLE INSPECITON ("A" CHECK). DURIN	G RUN-UP FOR SERVICEABILITY CHECK, THE #2 ENGINE/PROPELLER EXPERIENCED AN UNCOMMANDED AUTOFEATHER UPON MOVING THE PROP O	UT OF GROUND IDLE POSITION. THE PCU WAS REMOVED AND RETURNED TO THE FACTORY FOR REPAIR AND INVESTIGATION.			2	L	7	2 	4T			RT	A31SO 		6	C	P11NE	 
1996081500717	19960815	00717	CE 	1996	8	15	CA951123103 	1	19951020	G	2750	05232315	BRACKET 	CESSNA 		CESSNA	175 	175 	2072502	CE 										FLAP TRACK	BROKEN 	W				C				ABORTED TAKEOFF 				F			FLT CONT AFFECTED 			TO	TAKEOFF 	1			CA											(CAN)BRACKET AT THE RIGHT INBOARD FLAP TRACK CRACKED AT BOTH RIVETS. BRACKET DROPPED DOWN AND PREVENTED THE FLAPS FROM R	ETRACTING.					1	H	7	1 	3O			NT	3A17 					 
1996081500720	19960815	00720	NM 	1996	8	15	CA951124002 	1	19951104	G	3250	MS165626	SPRING PIN 		83250032003 	DHAV 	DHC8 	DHC8101 	2809002	NM 										STEERING TILLER	DISPLACED 	W		A		D				RETURN TO BLOCK 				O			OTHER 			TX	TAXI/GRND HDL 	1			CA											(CAN) IN TAXI, CREW EXPERIENCED SUDDEN LOSS OF STEERING CONTROL AIRCRAFT VEERED SHARPLY TO ONE SIDE. INVESTIGATION REVEA	LED THAT SPRING PIN SECURING CCX-A1-10 COUPLING TO STEERING TILLER HAD FALLEN OUT OF POSITION. THE COUPLING IN TURN FEL	L FROM INSTALLED POSITION AND LANDED ON FLOOR. LOSS OF UNIVERSAL COUPLING WHICH DISCONNECTED THE STEERING TILLER HANDLE 	FROM THE POTENTIOMETER WAS CAUSE OF STEERING LOSS.			2	H	7	2 	4T			RT	A13NM 					 
1996081500721	19960815	00721	NM 	1996	8	15	CA951124003 	1	19951116	G	3230	8800121	CYLINDER 	ROTOL 		DHAV 	DHC8 	DHC8101 	2809002	NM 										NLG OUTER	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)CRACK FOUND ON AFT SIDE OF NOSE LANDING GEAR OUTER CYLINDER.						2	H	7	2 	4T			RT	A13NM 					 
1996081500722	19960815	00722	SO 	1996	8	15	CA951127002 	1	19951116	G	2910	159H10078C0126	HOSE 			GULSTM	G159 	G159 	3952202	SO 										L/H ED PUMP	LEAKING 	W				E				ENGINE SHUTDOWN 				K			FLUID LOSS 			TX	TAXI/GRND HDL 	1			CA											(CAN) AIRCRAFT LOST HYDRAULIC PRESSURE AFTER LANDING. ENGINES WERE SHUT DOWN AND WAS TOWED OFF TAXIWAY. HYDRAULIC LINE F	ROM L/H ENGINE DRIVEN PUMP (PRESSURE SUPPLY) HAD FAILED. LINE WAS REPLACED WITH AN IMPROVED 3000 PSI LINE FROM MANUFACTU	RER.				2	L	7	2 	4T				1A17 					 
1996082200230	19960822	00230	EU 	1996	8	22	CA951127203 	1	19951115	G	2435	02420305	WASHER 	LUCAS 	23080005 	BRAERO	DH125 	BAE125800A 	1500285	EU 										TERMINAL BLOCK	MISSING 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA						3804					(CAN)MISSING WASHERS BETWEEN STATOR TERMINALS AND TERMINAL STUDS RESULTING IN STATOR LEADS BEING PUSHED INWARDS AND RUBB	ING ON THE ARMATURE BALANCING RING.					2	L	7	2 	4F			RT	A3EU 					 
1996082200232	19960822	00232	NM 	1996	8	22	CA951129201 	1	19951117	G	3010	829489	VALVE 	BENDIX 	153212A 	DHAV 	DHC8 	DHC8102 	2809003	NM 										DEICING	FAILED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA						RF3587					(CAN)DE-ICING CONTROL VALVE FAILED BECAUSE OF LACK OF DRAIN HOLE. IT HAD BEEN PLUGGED BY POTTING COMPOUND WHEN VALVE HEA	TERS WERE INSTALLED.					2	H	7	2 	4T			RT	A13NM 					 
1996082200242	19960822	00242	SW 	1996	8	22	CA951130015 	1	19951116	G	3260	MS250413	SOCKET 			GULSTM	112 	112 	0144701	SW 	LYC 					HARTZL				GEAR IND	LOOSE 	W				K				NONE 				J			WARNING INDICATION 			AP	APPROACH 	1			CA			1478 								(CAN)WHILE CARRYING OUT FLIGHT TEST AFTER AN INSPECTION THE RIGHT HAND GEAR LIGHT FAILED TO ILLUMINATE. PILOT TAPPED TH	E SOCKET AND THE LIGHT CAME ON. ALL THREE POSITION LIGHT SOCKETS WERE FOUND TO BE LOOSE AND THEREFORE NEW PARTS WERE OR	D ERED FOR THE AIRCRAFT.				1	L	7	1 	3O				A12SO 					 
1996082200245	19960822	00245	NE 	1996	8	22	CA951130020 	2	19951126	G	7261		SEAL 								PWA 	PW120 	PW127 		NE 					PROP SHAFT	FAILED 	W				E	A			ENGINE SHUTDOWN 	UNSCHED LANDING 			O	J		OTHER 	WARNING INDICATION 		CR	CRUISE 	1			CA								127150			(CAN)IN CRUISE THE #1 ENGINE OIL PRESSURE FLUCTUATED APPROXIMATELY 5 PSI AND DECREASED UNTIL THE OIL PRESSURE LIGHT ILLU	MINATED ON AND OFF. THE PILOT SECURED THE ENGINE AND MADE AN EMERGENCY LANDING. POSTFLIGHT INSPECTION REVEALED OIL LOSS 	PAST THE PROPELLER TRANSFER TUBE SEAL.									4	T			E20NE				 
1996082200246	19960822	00246	NE 	1996	8	22	CA951130022 	2	19951002	G	7322		FUEL CONTROL 								PWA 	PW120 	PW126A 		NE 					NR 1 ENGINE	FAULTY 	W				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			CL	CLIMB 	1			CA								124224			(CAN)IN CLIMB A REPORTED LOSS OF POWER OCCURRED ON #1 ENGINE. POST FLIGHT INSPECTION DETERMINED THE FAULT WAS THE HYDROM	ECHANICAL FUEL CONTROL UNIT WHICH WAS REPLACED.										4	T			E2ONE				 
1996082200247	19960822	00247	NE 	1996	8	22	CA951130023 	2	19951107	G	7250		BOLT 								PWA 	120 	PW120 		NE 					INTERSTAGE TURB	FRACTURED 	W				F	C	D		ACTIVATE FIRE EXT. 	ABORTED TAKEOFF 	RETURN TO BLOCK 		O	A		OTHER 	FLAME/FIRE 		TO	TAKEOFF 	1			CA			15753					120214			(CAN)A LOUD NOISE WAS HEARD FROM #1 ENGINE WITH A LOSS OF POWER DURING TAKEOFF. FIRE WAS REPORTED BUT NO FIRE WARNING WA	S OBSERVED. THE FIRE BOTTLE WAS DISCHARGED AND THE AIRCRAFT RETURNED TO ITS POINT OF DEPARTURE. POST FLIGHT INSPECTION 	REVEALED 30 PERCENT OF THE 2ND STAGE POWER TURBINE BLADES WERE MISSING. DETAILED INSPECTION FOUND THE CAUSE OF THE IN-FL	IGHT SHUTDOWN WAS THE FRACTURE OF A TURBINE INTERSTAGE BOLT.								4	T			E20NE				 
1996082200248	19960822	00248	NE 	1996	8	22	CA951130024 	2	19951013	G	7260		TOWERSHAFT 								PWA 	118 	PW118 		NE 					ACCESSY GEARBX	FAILED 	W				O				OTHER 				X			ENGINE FLAMEOUT 			CR	CRUISE 	1			CA								115298			(CAN)THE ENGINE SHUT ITSELF DOWN IN CRUISE. THE ENGINE WAS DISMANTLED AND THE CAUSE OF THE INFLIGHT SHUTDOWN WAS CONFIRM	ED TO BE TOWERSHAFT FAILURE.										4	T			E20NE				 
1996082200252	19960822	00252	SO 	1996	8	22	CA951206004 	2	19951205	G	7414	62224	GASKET 	SLICK 	4301 	CESSNA	150 	150H 	2071818	CE 	CONT 	O200 	O200A 	17020	SO 					MAG MOUNT BASE	FAILED 	W				D				RETURN TO BLOCK 				E			VIBRATION/BUFFET 			TO	TAKEOFF 	1			CA			24 			94100249		661467A			(CAN)PILOT REPORTED HIGH MAG DROP DURING RUN-UP. MAGNETO WAS INSTALLED WITH THE WRONG GASKET RESULTING IN THE MAGNETO B	EING LOOSE ON ITS MOUNT BASE AND CAUSING THE MAGNETO TO OPERATE OUT OF TIME. CORRECT GASKET SHOULD HAVE BEEN P/N 534750	. N.B. THIS PROBLEM WAS ADDRESSED IN FEED-BACK MAGAZINE 1/95, PAGE 7.				1	H	7	1 	3O	3	O		3A19 	E252				 
1996082200253	19960822	00253	SO 	1996	8	22	CA951206005 	2	19951205	G	8530	653450A5	CYLINDER 								CONT 	O360 	TSIO360GB 	17025	SO 					NR 2	CRACKED 	W				A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			CA				230 							(CAN) PILOT REPORTED SUDDEN ROUGHNESS IN ENGINE DURING CRUISE FLIGHT. POST-FLI GHT INSPECTION FOUND NR 2 CYLINDER TO BE	 CRACKED CIRCUMFERENCIALLY IN THE ALLOY HEAD MATERIAL WHERE IT JOINS WITH THE STEEL BARREL. WITH THE NR 2 CYLINDER REM 	OVED THE CRACK WAS FOUND TO BE FROM THE 2 O'CLOCK POSITION AROUND THE BOTTOM TO THE 10 O'CLOCK POSITION OF THE CYLINDER 	HEAD.								3	O			E9CE				 
1996082200256	19960822	00256	CE 	1996	8	22	CA951206008 	1	19951120	G	3010	6208031111	DIODE 			CESSNA	525 	525 	2076601	CE 										R/H WING LE	OPEN CIRCUIT 	W				D				RETURN TO BLOCK 				M	J		OVER TEMP 	WARNING INDICATION 		TX	TAXI/GRND HDL 	1			CA			418 	418 							(CAN)PILOT REPORTED RIGHT WING "HOT" ON GROUND WITH WING ANTI-ICE SELECTED OFF. DIODE FOUND OPEN WHICH ALLOWS ENGINE BLE	ED AIR TO PASS THROUGH THE WING ANTI-ICE VALVE, HEATING THE LEADING EDGE.					1	L	7	2 	4F			RT	A1WI 					 
1996082200263	19960822	00263	SW 	1996	8	22	CA951211013 	1	19951126	G	3220	3216	BRACKET ASSY 	SCOTT 	3200 	BBAVIA	7 	7ECA 	21101NN	SW 	LYC 									TAIL FORK ASSY	BROKEN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			2230 			10179					(CAN)TAKING OFF THE WHEEL TO INSTALL THE TAIL SKI THE FORK ASSEMBLY CAME OFF COMPLETELY FROM THE BRACKET ASSEMBLY DUE TO	 THE INTERNAL FRACTURE OF THE BOLT HOLDING THE FORK TO THE BRACKET. SUBMITTER STATES THAT PART SHOULD BE INSPECTED EVER	 Y 500 HOURS AND THAT NDT DYE PENETRANT SHOULD BE USED AS AN INSPECTION TECHNIQUE.				1	H	7	1 	3O				A759 					 
1996082200265	19960822	00265	CE 	1996	8	22	CA951212001 	1	19951121	G	3230	6664	LINE 	WIPLINEINC 	8000 	CESSNA	208 	208 	2073702	CE 	PWA 									L/H FLOAT	RUPTURED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			4270 								(CAN)AIRCRAFT LANDING GEAR FAILED TO OPERATE DUE TO A RUPTURED HYDRAULIC LINE. OPERATING PRESSURE OF HOSE IS 1100 PSI. S	UBMITTER SUSPECTS THAT THE HOSE MAY HAVE BEEN WEAKENED BY SALT WATER EXPOSURE.					1	H	7	1 	3T			NT	A37CE 					 
1996082200267	19960822	00267	SO 	1996	8	22	CA951212003 	1	19950818	G	5230	8732910	LOCK ASSY 	PIPER 	9691700 	PIPER 	PA34 	PA34220T 	7103420	SO 	CONT 					MCAULY				NOSE BAG DOOR	WORN 	W		A		A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			CA			2861 								(CAN)IMMEDIATELY AFTER TAKEOFF THE AIRCRAFT WAS OBSERVED TO CLIMB APPROXIMATELY 100 FEET ABOVE GROUND, ENTER A STEEP LEF	T TURN AND DESCEND NOSE FIRST TO THE GROUND. THE FOUR OCCUPANTS SUSTAINED FATAL INJURIES. THE INVESTIGATION HAS DETERM	INED THAT IT IS PROBABLE THAT THE NOSE BAGGAGE DOOR OPENED AFTER TAKEOFF. THIS MAY HAVE CONTRIBUTED TO THE LOSS OF CONT	ROL. FAA AIRWORTHINESS DIRECTIVE 88-04-05 REQUIRES A ONE TIME COMPLIANCE WITH PIPER SB 872, WHICH MANDATES AN INSPECTIO	N OF THE FORWARD BAGGAGE DOOR FOR POSITIVE LATCHING AND LOCKING. SB 872 STATES THAT IF THE BAGGAGE DOOR KEY CAN BE REMO	VED FROM THE LOCK AT ANY POINT OTHER THAN FULLY LOCKED, THE LOCK MUST BE REPLACED. THIS AIRCRAFT WAS NOT IN COMPLIANCE	1	L	7	2 	3O				A7SO 					 
1996082200268	19960822	00268	CE 	1996	8	22	CA951212005 	1	19951127	G	3213	244101139	CYLINDER 			LEAR 	55 	55LEAR 	5170702	CE 										MLG	BROKEN 	W				K				NONE 				J			WARNING INDICATION 			CL	CLIMB 	1			CA			5006 								(CAN)ON DEPARTURE AIRCRAFT LIFTED UP NORMALLY BUT AFTER GEAR WAS SELECTED UP, THE CREW FELT THAT THE GEAR WAS NOT COMPLE	TELY UP AND LOCKED SO THEY FLEW AT REDUCED AIRSPEED. ON LANDING, A VIBRATION AND LOW WING CONDITION WAS NOTICED DURING 	TAXI TO TERMINAL. ON INSPECTION, NOTED LOWER PART OF STRUT CYLINDER DETACHED AT CIRCLIP CUTOUT AREA.				2	L	7	2 	4F				A10CE 					 
1996082200269	19960822	00269	SO 	1996	8	22	CA951212006 	1	19951204	G	3210	2082900	SIDE BRACE STUD 			PIPER 	PA24 	PA24250 	7102404	SO 	LYC 									MLG	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			5034 								(CAN)WHILE COMPLYING WITH AD 95-20-07 THE LEFT AND RIGHT SIDE BRACE STUDS WERE FOUND CRACKED USING MAGNETIC PARTICLE INS	PECTION. SUBMITTER STATES THAT THIS AD SHOULD BE COMPLIED WITH IMMEDIATELY RATHER THAN WITHIN THE 100 HOUR RECOMMENDATIO	N.				1	L	7	1 	3O				1A15 					 
1996082200271	19960822	00271	SO 	1996	8	22	CA951212008 	1	19951204	G	7922	75944	VALVE 			PIPER 	PA28 	PA28180 	7102808	SO 	LYC 	O360 	O360A4A 	41514	EA 					THERMO BYPASS	LOOSE NUT 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			1139 					L1109236A			(CAN)DURING COMPLIANCE WITH LYCOMING SERVICE BULLETIN 518C (INSPECTION OF THERMOSTATIC BYPASS VALVE) THE VERNATHERM CRIM	P NUT WAS FOUND LOOSE. VERNATHERM VALVE REPLACED.					1	L	7	1 	3O	3	O		2A13 	E286				 
1996082200276	19960822	00276	NE 	1996	8	22	CA951215006 	2	19950729	G	8530	47518	CYLINDER 								PWA 	R985 	R985AN14B 	52008	NE 					NR 1 CYL	FAILED 	W				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			CA				20 				JP211055			(CAN)ENGINE WAS RUNNING ROUGH ON TAKEOFF. POST FLIGHT INSPECTION FOUND LOW COMPRESSION ON #1 CYLINDER, BARREL WAS IN GOO	D CONDITION WITH NO OIL LEAKS AT HEAD AND BARREL. EXHAUST VALVE GUIDE WAS WORN OUT AND THE EXHAUST VALVE WAS POUNDED INT	O THE SEAT AND BADLY DISTORTED. THE INTAKE PORT WAS FUEL STAINED AND LEAKING. THE CYLINDER WAS RUNNING LEAN CAUSING OVER	HEATING. THE CYLINDER IS REPAIRABLE. THIS ENGINE HAS BEEN RUNNING ON AUTOMOTIVE GASOLINE.								3	R			5E1				 
1996082200277	19960822	00277	NE 	1996	8	22	CA951215007 	2	19950810	G	8530	47518	CYLINDER 								PWA 	R985 	R985AN14B 	52008	NE 					NR1 CYLINDER	SEPARATED 	W				A				UNSCHED LANDING 				E	R	K	VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 	FLUID LOSS 	CL	CLIMB 	1			CA				133 				9141			(CAN)ENGINE WAS RUNNING ROUGH ON TAKEOFF. POST FLIGHT INSPECTION FOUND #1 CYLINDER SEPARATED AT THE BARREL/HEAD AT THE L	AST THREAD. THE CYLINDER DOME AND EXHAUST PORT WERE OIL FOULED. THERE WAS A BAD FUEL LEAK AT THE INTAKE PORT. THE VALVE	S, VALVE GUIDES AND SEATS WERE IN GOOD CONDITION AND THERE WAS NO EVIDENCE OF ANY OIL LEAKS AT THE BARREL/HEAD. THIS ENG	INE HAS BEEN OPERATING WITH AUTOMOTIVE GASOLINE.								3	R			5E1				 
1996082200278	19960822	00278	NE 	1996	8	22	CA951215008 	2	19950802	G	8530	47518	CYLINDER 	? 							PWA 	R985 	R985AN14B 	52008	NE 					NR 3 CYLINDER	SEPARATED 	W				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			CA				146 		AR14633		JP211055			(CAN)ENGINE WAS RUNNING ROUGH ON TAKEOFF POST FLIGHT INSPECTION FOUND #3 CYLINDER SEPARATED AT THE BARREL/HEAD, BARREL 	WAS BROKEN OFF AT THE LAST THREADTHE DOME AND THE EXHAUST PORT WERE OIL FOULED THEEXHAUST VALVE WAS POUNDED INTO THE SE	AT. THIS ENGINE IS BEING OPERATED USING AUTOMOTIVE GASOLINE.									3	R			5E1				 
1996082200279	19960822	00279	NE 	1996	8	22	CA951215009 	2	19950810	G	8530	47518	CYLINDER 								PWA 	R985 	R985AN14B 	52008	NE 					NR 3 CYLINDER	SEPARATED 	W				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			CA				132 		AR12235		9141			(CAN)ENGINE WAS RUNNING ROUGH ON TAKEOFF POST FLIGHT INSPECTION FOUND THAT #3 CYLINDER HAD A BAD OIL LEAK AT THE BARREL	/HEAD AND WAS STARTING TO SEPARATE THERE WERE FUEL STAINS AT THE INTAKE PORT THE CY LINDER HAD BEEN RUNNING HOT AND THE	 EXHAUST VALVE GUIDE WAS WORN. THIS ENGINE HAS BEEN OPERATING USING AUTOMOTIVE GASOLINE.									3	R			5E1				 
1996082200280	19960822	00280	NE 	1996	8	22	CA951215010 	2	19950810	G	8530	47518	CYLINDER 	? 							PWA 	R985 	R985AN14B 	52008	NE 					NR 6 CYLINDER	SEPARATED 	W				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			CA				140 		AR12228		9141			(CAN)ENGINE WAS RUNNING ROUGH ON TAKEOFF POST FLIGHT INSPECTION FOUND #6 CYLINDER HAD A BAD OIL LEAK AT THE BARREL/HEAD	 AND WAS STARTING TO SEPARATE .THE VALVE GUIDES AND VALVE SEATS WERE WITHIN LIMITS THIS ENGINE HAS BEEN OPERATING USING	 AUTOMOTIVE GASOLINE.									3	R			5E1				 
1996082200282	19960822	00282	NE 	1996	8	22	CA951215012 	2	19950810	G	8530	47518	CYLINDER 	? 							PWA 	R985 	R985AN14B 	52008	NE 					ENGINE	SEPARATED 	W				A				UNSCHED LANDING 				E	R		VIBRATION/BUFFET 	PARTIAL RPM/PWR LOSS 		CL	CLIMB 	1			CA				132 		AR16039		JP211055			(CAN)ENGINE WAS RUNNING ROUGH ON TAKEOFF. POST FLIGHT INSPECTION FOUND A CYLINDER BROKEN/SEPARATED AT THE TOP OF THE BAR	REL . THIS ENGINE HAS BEEN OPERATING USING AUTOMOTIVE GASOLINE										3	R			5E1				 
1996082200287	19960822	00287		1996	8	22	CA951215017 	4	19951207	G	2562	002504	BATTERY 	MARTECH 	EB2BCD 	PIPER 	PA28 	PA28151 	7102805	SO 	LYC 									ELT	CORRODED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA						40013					(CAN)ELT WAS SENT IN FOR RECERTIFICATION AND BATTERY REPLACEMENT. CASE HAD TO BE PRIED OPEN. ELT UNIT WAS FOUND SEIZED B	ETWEEN THE BATTERY CASE AND THE INSIDE OF THE CASE DUE TO HEAVY BATTERY LEAKAGE AND S UBSEQUENT CORROSION. BATTERY DUE D	ATE WAS JULY 1995, THE SAME DUE DATE AS REPORTED ON SDR 950801411. SUBMITTER REPORTS THIS AS BEING THE 5TH SUCH OCCURREN	CE HE HAS REPORTED.			1	L	7	1 	3O				2A13 					 
1996082200289	19960822	00289	NE 	1996	8	22	CA951215019 	3	19951208	G	6111	7854031	BORE PLUG 	HAMSTD 	SFA13MIOA 											HAMSTD	14SF	14SF7 	NE 	PROP BLADE	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA				646 		853879					(CAN)DURING INSPECTION A CRACK WAS FOUND AT THE BORE PLUG OF THE PROPELLER BLADE ON THE INNER SIDE AROUND THE THREAD. A 	SMALL AMOUNT OF OIL WAS ALSO FOUND IN THE TAPER BORE.															6	C	P7NE	 
1996082200302	19960822	00302	EU 	1996	8	22	CA951218012 	1	19951205	G	2422	MGH182100	INVERTER 			BRAERO	748 	HS7482A 	4231001	EU 										AC SYS	WORN BRUSHES 	W				K				NONE 				L			NO TEST 			TX	TAXI/GRND HDL 	1			CA				544 							(CAN)INVERTER FAILED ON GROUND TEST. REMOVED SENT FOR OVERHAUL, BRUSHES FULLY WORN. REPLACED.						2	L	7	2 	3T				A24EU 					 
1996082200306	19960822	00306	SW 	1996	8	22	CA951218021 	1	19951210	G	6510	206040338009	HANGER ASSEMBLY 			BELL 	206 	206B 	1181511	SW 										T/R DRIVE	WORN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)WHILE PERFORMING ASB 206-95-86 REVISION B A WEAR STEP AND CRACK FOUND IN THE FILLET RADIUS OF HANGER LUG.						1	G	7	1 	3U				H2SW 					 
1996082200308	19960822	00308	EU 	1996	8	22	CA951218201 	1	19951012	G	3233	7733690395	RELAY 		7733690395 	SOCATA	TB20 	TB21 	8680697	EU 										MLG EXT	SHORTED CLOSED 	W				L				ABORTED APPROACH 				O			OTHER 			AP	APPROACH 	1			CA			322 	322 							(CAN)PILOT WAS ATTEMPTING AN APPROACH WHEN THE CIRCUIT BREAKER FOR THE LANDING GEAR KEPT POPPING OUT AFTER BEING RESET S	EVERAL TIMES MANUAL GEAR EXTENSION WAS PERFORMED BUT GEAR DOWN AND LOCKED LIGHTS WOU LD NOT ILLUMINATE. AFTER SEVERAL A	TTEMPTS TO LOCK GEAR, PILOT REPORTED THREE IN THE GREEN AND MADE AN UNEVENTFUL LANDING. INSPECTION FOUND THE RELAY HAD S	HORTED OUT AND WOULD NOT ALLOW THE ELECTRIC MOTOR TO RUN THE HYDRAULICS.			1	L	7	1 	3O			RT	A51EU 					 
1996082200315	19960822	00315	CE 	1996	8	22	CA951221001 	1	19951127	G	2720	AN15122RS	FORK CABLE 	CESSNA 	07123091 	CESSNA	185 	A185E 	2072818	CE 										RH RUDDER CABLE	CORRODED/BROKEN 	W		A		O				OTHER 				F			FLT CONT AFFECTED 			TX	TAXI/GRND HDL 	1			CA											(CAN)WHILE TAXIING IN A CROSSWIND THE RIGHT HAND RUDDER PEDAL WENT FULL FORWARD. INSPECTION REVEALED THAT CORROSION IN 	THE UPPER PART OF THE BELLCRANK ASSEMBLY HAD SEIZED THE RUDDER CABLE FORK END TO THE BELLCRANK. THE SINGLE STRAND OF L 	OCKWIRE ON THE TURNBUCKLE FAILED AT THE SAME TIME.				1	H	7	1 	3O				3A24 					 
1996082200317	19960822	00317	CE 	1996	8	22	CA951221012 	1	19951230	G	5320		STRUT FITTING 	CESSNA 		CESSNA	206 	U206D 	2073342	CE 	CONT 									LH STRUT LOWER	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			8668 								(CAN)WHILE CARRYING OUT SEB 93-5 ON THE LOWER LEFT HAND DOOR POST STRUT FITTING, A CRACK WAS FOUND AT THE WING STRUT SUP	PORT FITTING. CESSNA SERVICE KIT SK 206-42C WAS INSTALLED AND THE AIRCRAFT RETURNED T O SERVICE.					1	H	7	1 	3O				A4CE 					 
1996080200525	19960802	00525		1996	8	2	CA951221022 	4	19951220	G	3451	A7C1	CAPACITOR 			BOEING	727 	727171C 	1384057	NM 										NR 1 DME	SHORTED 	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER 			CR	CRUISE 	1			CA											(CAN)DURING FLIGHT IT WAS NOTICED THAT THE #1 DME WAS NO LONGER COUNTING MILEAGE. THE SYSTEM HAD LOCATED THE STATION SEL	ECTED AND HAD A IDENT BUT WOULD NOT INDICATE DISTANCE. DME CHANGED. A7C1 CAPACITOR HA D SHORTED.					2	L	7	3 	4F				A3WE 					 
1996080200526	19960802	00526	EA 	1996	8	2	CA951221023 	1	19951220	G	3240	950377	BRAKE ASSEMBLY 	GOODYEAR 		DHAV 	DHC6 	DHC6300 		EA 										NR1	LEAKING 	W				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CA						JUL781100					(CAN)DURING PREFLIGHT #1 BRAKE UNIT FOUND LEAKING. FOUND WEAR IN PISTON CYLINDERS.						1	H	7	2 	3T				A9EA 					 
1996072500369	19960725	00369	NM 	1996	7	25	CA951221024 	1	19951220	G	2424	939D1502	REGULATOR 	WESTINGHOUSE	939D1502 	BOEING	727 	727171C 	1384057	NM 										NR 2 GEN	INTERMITTENT 	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER 			CR	CRUISE 	1			CA						UK663M					(CAN)DURING FLIGHT THE #2 GENERATOR TRIPPED OFF LINE DUE TO AN UNDERVOLTAGE AND UNDEREXCITATION CONDITION. THE VOLTAGE R	EGULATOR WAS CHANGED AND THE SYSTEM GROUND CHECKED SERVICEABLE.					2	L	7	3 	4F				A3WE 					 
1996072500370	19960725	00370		1996	7	25	CA951221025 	4	19951220	G	3414	A4144910005	INDICATOR 			BOEING	727 	727171C 	1384057	NM 										MACH INST	INTERMITTENT 	W				K				NONE 				I			FLT. ATTITUDE INST. 			NR	NOT REPORTED 	1			CA											(CAN)DURING SELECTION FROM MODE A TO MODE B IN THE MACH INDICATOR THE BARBER POLE WAS SEEN TO INTERMITTENTLY STICK AT AN	 UNUSUAL SETTING. THE INDICATOR OPERATED NORMALLY OTHERWISE AND FOLLOWING THE FLIGHT THE INSTRUMENT WAS CHANGED.					2	L	7	3 	4F				A3WE 					 
1996082900006	19960829	00006	NE 	1996	8	29	CA951221039 	2	19951213	G	7261	219379001	DETECTOR HOUSING								LYC 	ALF502	ALF502R5 	41580	NE 					OIL PUMP	LOOSE BOLTS 	W				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CA								LF05227A			(CAN)DURING THE INSTALLATION OF THE ENGINE, THE CHIP DETECTOR HOUSING WAS FOUND LOOSE ON ITS MOUNT INTERFACE WITH THE OI	L PUMP. AFTER THE SAFETY WIRE WAS REMOVED IT WAS FOUND THAT ONE OF THE HELICOIL FASTENERS WAS GONE AND THE MOUNTING BOLT	S HAD NO THREADS TO ENGAGE. THE ENGINE ARRIVED THIS WAY FROM ALLIED SIGNAL.									4	F			E6NE				 
1996082900007	19960829	00007		1996	8	29	CA951221040 	1	19951213	G	2432	VP170KH	CELL 	SAFT 	1756 															CELL	BROKEN STUD 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			2005 			46796					(CAN)DURING BATTERY DEEP CYCLE AND WHILE TORQUEING TERMINAL NUTS, ONE CELL STUD BROKE OFF. CELL REPLACED. CELL P/N VP170	KH.																		 
1996082900014	19960829	00014	NM 	1996	8	29	CA951222009 	1	19951221	G	2760	532DB	PANEL 	DHAV 		DHAV 	DHC8 	DHC8* 		NM 										ROLL SPOILER	CHAFED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)ALL FLEET AIRCRAFT CHECKED AND ONE FOUND WITH PANEL RH 532DB AND LH 632DB CHAFED THROUGH HONEYCOMB. CLAMPS WERE CHA	NGED AND REINSTALLED SO THAT CURVED PORTION OF CLAMP FACES UP, CREATING MORE ROOM BET WEEN CLAMP AND FLAP CLOSURE PANEL.					2	H	7	2 	4T			RT	A13NM 					 
1996082900015	19960829	00015	NE 	1996	8	29	CA951222010 	2	19951206	G	7320		P3 LINE 								PWA 	PT6 	PT6A67A 	52043	NE 					FUEL CONTROL SYS	RUPTURED 	W				E				ENGINE SHUTDOWN 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			CA			1114 					105024			(CAN)IN CRUISE, WITH ENGINE PARAMETERS NORMAL, #2 ENGINE SPOOLED DOWN. POST FLIGHT INSPECTION REVEALED A RUPTURED P3 LIN	E.										4	T			E26NE				 
1996082900016	19960829	00016	NE 	1996	8	29	CA951222011 	2	19951123	G	7250		PT BLADES 								PWA 	PT6 	PT6A67D 		NE 					2ND STAGE TURB	LIBERATED 	W				E				ENGINE SHUTDOWN 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			CA			5484 					114165			(CAN)#1 ENGINE EXPERIENCED AN IN FLIGHT SHUTDOWN. POST FLIGHT INSPECTION OF THE ENGINE REVEALED THAT THE 2ND STAGE POWER	 TURBINE BLADES HAD BEEN LIBERATED AT VARIOUS LENGTHS FROM ABOVE THE PLATFORM TO MID SPAN. POWER SECTION WAS STIFF TO R	OTATE.									4	T			E26NE				 
1996082900017	19960829	00017		1996	8	29	CA951228001 	2	19951219	G	7314	SPE19841	PUMP 	PLESSEY 	BPIRSMK6 															FUEL SYS	OUT OF SPECS 	W				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CA						41627A					(CAN)FUEL PUMP COMMUTATOR BELOW MIN. UNAPPROVED BEARING INSTALLED.																			 
1996082900029	19960829	00029	SO 	1996	8	29	CA960102103 	2	19951228	G	7322	30764	FLOAT ASSEMBLY 	MARVELSCHEB 		CESSNA	180 	180H 	2072618	CE 	CONT 	O470 	O470R 	17026	SO 					CARB FLOAT	BROKEN 	W				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CA			600 					238057R			(CAN)SEPARATION OF FLOAT CHAMBER FROM FRAME. SOLDERING OF JOINT APPEARS TO BE IMPROPERLY PERFORMED.						1	H	7	1 	3O	3	O		5A6 	E273				 
1996082900033	19960829	00033	CE 	1996	8	29	CA960103005 	1	19951211	G	5620	10243009115	WINDOW 			BEECH 	58 	58P 	1152744	CE 										RIGHT SIDE	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			1700 								(CAN)WHILE INSPECTING THE AIRCRAFT FOR MANDATORY SERVICE BULLETIN 2630, THE SECOND AND THIRD WINDOW ON THE RIGHT SIDE WE	RE ALSO FOUND CRACKED. WINDOWS REPLACED.					1	L	7	2 	3O				A23CE 					 
1996082900036	19960829	00036	CE 	1996	8	29	CA960103008 	1	19951218	G	5320	57130505	WEB 			CESSNA	441 	441 	2076020	CE 										NLG WHEEL WELL	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			5596 								(CAN)WEB P/N 5713050-5 AND DOUBLER P/N 5713050-11 CRACKED. CRACK EXTENDS 3/4" ABOVE L/H DRAG BRACE BRACKET TO APPROXIMAT	ELY 3/4" BELOW BRACKET RUNNING VERTICAL ON THE AFT SIDE OF BRACKET. SERVICE NEWS LETT ER 85-44 ADDRESSES THIS PROBLEM.					1	L	7	2 	3T			RT	A28CE 					 
1996082900040	19960829	00040	NE 	1996	8	29	CA960103014 	2	19951028	G	7311		OIL COOLER 								PWA 	PWA120	PW125B 		NE 					NR 2 ENGINE	CONTAMINATED 	W				E				ENGINE SHUTDOWN 				J			WARNING INDICATION 			CL	CLIMB 	1			CA			8148 	4994 				124170			(CAN)IN CLIMB, A LEVEL 3 WARNING WAS RECEIVED, THE ENGINE OIL PRESSURE LIGHT ILLUMINATED AND OIL PRESSURE INDICATED BELO	W 40 PSI. THE PILOT SHUT DOWN THE ENGINE AND THE AIRCRAFT RETURNED TO ITS POINT OF DE PARTURE. POST FLIGHT INSPECTION RE	VEALED CONTAMINATED FUEL. THE FUEL COOLED OIL COLLER WAS REPLACED.									4	T			E20NE				 
1996082900071	19960829	00071	EA 	1996	8	29	CA960103532 	2	19951124	G	8530		VALVE SEAT 								LYC 	O540 	O540E4B5 	41532	EA 					CYLINDER	WRONG DEPTH 	W				O				OTHER 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			CA								RL928640			(CAN)AFTER THE ENGINE WAS OVERHAULED, WITH SIX (6) NEW CYLINDERS FROM CONTINENTAL, THE ENGINE FAILED TO ACHIEVE FULL POW	ER ON THE POST INSPECTION/OVERHAUL RUN-UP. THE MAXIMUM RPM WAS 2700, INSTEAD OF THE REQUIRED 2850 RPM. TROUBLESHOOTING R	EVEALED THAT ONE OF THE INTAKE VALVE SEAT WAS 1/8 OF AN INCH DEEPER IN THE HEAD THAN THE OTHER FIVE. THE CYLINDER WAS RE	PLACED AND THE PROPER ENGINE RPM WAS ACHIEVED AT FULL POWER.								3	O			E295				 
1996082900072	19960829	00072	EA 	1996	8	29	CA960103533 	2	19951124	G	8550	STD1973	WOODRUFF KEY 								LYC 	O540 	O540E4B5 	41532	EA 					OIL PUMP	BROKEN 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA								RL928640			(CAN)THE OWNER REPORTED THAT #5 CYLINDER PISTON ROD MOVED ABNORMALLY AND THERE WAS A LOT OF METAL IN THE OIL FILTER. INT	ERNAL INSPECTION REVEALED THE ENGINE HAD LACKED OIL BECAUSE THE OIL PUMP DRIVE KEY (W OODRUFF KEY) HAD BROKEN. THE OIL P	UMP AND THE ENGINE WERE ALMOST TOTAL WRITE OFFS DUE TO LACK OF LUBRICATION.									3	O			E295				 
1996082900073	19960829	00073	EU 	1996	8	29	CA960103534 	2	19951129	G	7310	RK18668A	PIPE FUEL SERVO 			FRCHLD	F27 	F27F 	3373008	EA 	RROYCE	DART 	DART5297E 	54507	EU 					OUTER CASING	BLISTERED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA				3779 				13858			(CAN)DURING FIFTY HOUR ROUTINE (SERVICE BULLETIN) INSPECTION OF THE SERVO FUEL PIPE, WHICH RUNS FROM THE HIGH PRESSURE F	UEL PUMP TO THE FUEL CONTROL UNIT, WAS FOUND BLISTERED. THE PART WAS REMOVED AND A NEW PIPE P/N 1021106 WAS INSTALLED.					2	H	7	2 	4T	4	T		7A1 	E297				 
1996082900074	19960829	00074	SO 	1996	8	29	CA960108101 	1	19951027	G	3230	7642603	UPPER DRAG LINK 	PIPER 	7642603 	PIPER 	PA28 	PA28RT201T 	7102817	SO 	CONT 									FWD OF ACTUATOR	BROKEN 	W				A				UNSCHED LANDING 				O			OTHER 			CL	CLIMB 	1			CA			2235 								(CAN)A LOUD BANG WAS HEARD DURING GEAR RETRACTION. TWO GREEN LIGHTS WERE NOTED ON EXTENSION. THE ACFT LANDED WITHOUT FUR	THER INCIDENT AND THE UPPER DRAG BRACE WAS FOUND BROKEN IN HALF FWD OF THE HY D ACTUATOR. FURTHER EXAMINATION REVEALED E	VIDENCE OF CORROSION INITIATED STRESS CRACK. THE SUBMITTER STATES THAT AD 94-14-14 HAD BEEN C W 160 HRS PREVIOUSLY WITH 	NO EVIDENCE OF CRACK BEING FOUND. NEW PART IS 50 PERCENT THICKER THAN THE OLD PART IN THE AREA OF THE CRACK. SUBMITTER H	AS PERSONAL KNOWLEDGE OF TWO ADDITIONAL FAILURES OF THE SAME KIND.		1	L	7	1 	3O				2A13 					 
1996082900076	19960829	00076	EA 	1996	8	29	CA960109003 	1	19950726	G	2820	ASC4131	HOSE ASSEMBLY 	AEROQUIP 		DHAV 	DHC8 	DHC8311 	1386006	EA 										FIREWALL FITTING	SEPARATED 	W				D				RETURN TO BLOCK 				K	X		FLUID LOSS 	ENGINE FLAMEOUT 		TX	TAXI/GRND HDL 	1			CA											(CAN)MOTIVE FUEL FLEXIBLE HOSE ASSEMBLY SEPARATED FROM AFT END FITTING WHICH CONNECTS TO NACELLE VERTICAL FIREWALL. RESU	LTING LOSS OF FUEL CAUSED AIRCRAFT TO VEER SLIGHTLY TO LEFT DURING TAXI. HOSE RETURNE D TO MANUFACTURER FOR INVESTIGATIO	N.				2	H	7	2 	4T			RT	A13NM 					 
1996082900078	19960829	00078	NM 	1996	8	29	CA960109005 	1	19951123	G	2760	532DB	PANEL 	DHAV 		DHAV 	DHC8 	DHC8* 		NM 										LH & RH SPOILER	GOUGED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)SLIGHT CABLE RUB EVIDENT ON BOTH PANELS. P/N OF OTHER 632DB.						2	H	7	2 	4T			RT	A13NM 					 
1996082900079	19960829	00079	NM 	1996	8	29	CA960109006 	1	19951123	G	2760	532DB	PANEL 	DHAV 		DHAV 	DHC8 	DHC8* 		NM 	GE 									ROLL SPOILER	GOUGED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)CLAMP WEAR EVIDENT ON BOTH ROLL SPOILER PANELS. OTHER P/N 632DB.						2	H	7	2 	4T			RT	A13NM 					 
1996082900080	19960829	00080	NM 	1996	8	29	CA960109007 	1	19951123	G	2760	632DB	PANEL 	DHAV 		DHAV 	DHC8 	DHC8* 		NM 										ROLL SPOILER	GOUGED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)RUBBING EVIDENT ON RH ROLL SPOILER PANEL.						2	H	7	2 	4T			RT	A13NM 					 
1996082900085	19960829	00085	CE 	1996	8	29	CA960110006 	1	19951205	G	7810	109950001	DE-ICE DUCT 			BEECH 	90 	C90A 	1152911	CE 										EXHAUST STACK	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			5550 								(CAN)EXHAUST STACK CRACKING WHERE COWL ANTI-ICE TUBE ATTACHES TO THE MAIN EXHAUST STACK.						1	L	7	2 	3T			RT	3A20 					 
1996090500246	19960905	00246	CE 	1996	9	5	CA960111017 	1	19951229	G	7810	311494001	EXHAUST DUCT 			CESSNA	500 	550 	2076604	CE 	PWA 	JT15 	JT15D4 	52112	NE 					ENGINE	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			396 					PCE71818			(CAN)INSPECTION REVEALED TWO (2) CRACKS RADIATING AXIALLY FROM THE AFT EDGE OF THE EXH DUCT. ONE CRACK 1 7/8" LONG, THE 	OTHER 3/4" LONG. 6 1/2" SPACE BETWEEN THE CRACKS, WITH THE CRACKS RUNNING PARALLEL.					1	L	7	2 	4F	4	F		A22CE 	E1NE				 
1996090500268	19960905	00268	EA 	1996	9	5	CA960115018 	2	19951201	G	7322		FUEL CONTROL 								PWA 	PT6 	PT6A41 	52043	EA 					NR 2 ENGINE	FAULTY 	W				E				ENGINE SHUTDOWN 				O			OTHER 			CL	CLIMB 	1			CA			2955 					93550			(CAN)DURING CLIMB THE #2 ENGINE RPM INCREASED, TORQUE FLUCTUATED AND T5 INCREASED TO 800 DEGREES C. THE ENGINE WAS SHUTD	OWN. A GROUND INSPECTION REVEALED NO DAMAGE TO THE ENGINE. DURING A TEST RUN-UP THE ENGINE SHUT ITSELF DOWN WHILE AT IDL	E. THE FUEL CONTROL UNIT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.									4	T			E4EA				 
1996090500269	19960905	00269	NE 	1996	9	5	CA960115019 	2	19951204	G	7230		BEARING 								PWA 	PT6 	PT6A60A 	52043	NE 					NR 1	FRACTURED 	W				E				ENGINE SHUTDOWN 				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			CA			1350 					95488			(CAN)IN CRUISE PILOT NOTICED AN OIL ODOR IN THE CABIN. HE SHUT BLEED AIR OFF. WHEN MAIN OIL PRESSURE BEGAN TO DECAY ON #	1 ENGINE THE ENGINE WAS SHUTDOWN. ENGINE DISASSEMBLY REVEALED A SPALLED #1 BEARING AND A FRACTURED #1 BEARING AIRSEAL.										4	T			E4EA				 
1996090500271	19960905	00271	NE 	1996	9	5	CA960115021 	2	19951216	G	7230		BEARING 								PWA 	PW120 	PW126A 		NE 					COMP NR 1	FAILED 	W				O				OTHER 				O			OTHER 			CR	CRUISE 	1			CA				954 				124235			(CAN)AT 16,000 FEET THE PILOT REPORTED LOUD BANGS FROM #2 ENGINE AND THE AIRCRAFT BEGAN TO DESCEND. ALTHOUGH THE PROPELL	ER BEGAN AN AUTOFEATHER THE PILOT HAD TO SELECT MANUAL MODE TO COMPLETE THE SEQUENCE.GROUND INSPECTION REVEALS THE TORQU	E SHAFT HANGING ABOUT 45 DEGREES THROUGH THE INLET CASE, BEING DETACHED AT ITS FORWARD END. THE CASING HAS A HOLE 5" X 5	". ALL LAST STAGE PT BLADES ARE IN PLACE BUT THERE IS DAMAGE TO THE AIRFOILS. INITIAL INVESTIGATION LEADS TO THE FAILURE	 OF THE #1 BEARING AS THE PRIMARY CAUSE OF THE INCIDENT.							4	T			E2ONE				 
1996090500272	19960905	00272	NE 	1996	9	5	CA960115022 	2	19951116	G	7250		BLADES 								PWA 	118 	PW118 		NE 					1ST STAGE PT	FRACTURED 	W				E				ENGINE SHUTDOWN 				O	B		OTHER 	SMOKE/FUMES/ODORS/SPARKS 		CR	CRUISE 	1			CA			7015 	13 				115554			(CAN)IN CRUISE A LOUD BANG WAS HEARD FOLLOWED BY VIBRATION ON #2 ENGINE. NP DECREASED, TORQUE REACHED 100 PERCENT AND IT	T INCREASED. HEAVY WHITE SMOKE WAS REPORTED FROM THE TAIL PIPE. THE PILOT SHUTDOWN THE ENGINE. POST FLIGHT INSPECTION RE	VEALED THE #6/7 BEARING OIL SUPPLY TUBE TO HAVE FRACTURED. THERE WAS ALSO METAL IN THE CHIP DETECTOR. TEARDOWN REVEALED 	THE RELEASE OF FOUR 1ST STAGE POWER TURBINE BLADES, THE FIR TREES OF WHICH WERE FOUND IN THE DEBRIS.								4	T			E20NE				 
1996090500275	19960905	00275	EA 	1996	9	5	CA960116001 	1	19951107	G	2710	C2CF1197	LINK 	DHAV 		DHAV 	DHC2 	DHC2EVANS 	2801832	EA 										AILERON	BROKEN 	W				O				OTHER 				F			FLT CONT AFFECTED 			CR	CRUISE 	1			CA											(CAN)AILERON CHAIN LINK BROKE IN FLIGHT. PILOT ABLE TO LAND. FAILURE POSSIBLY CAUSED BY WORK HARDENING OF SHANK OF LINK 	WHICH CAUSED IT TO FRACTURE, POSSIBLY BECAUSE OF USE OF 'VICE-GRIPS' TO ADJUST AILERON TENSION. EVIDENCE TO THIS FOUND O	N OTHER END OF LINK WHICH IS BENT. OTHER SIDE PART #C2CF1198.				1	H	7	1 	3O				A806 					 
1996091900552	19960919	00552	SO 	1996	9	19	CA960126035 	2	19951230	G	8530		CYLINDER 			CESSNA	182 	182G 	2072716	CE 	CONT 	O470 	O470R 	17026	SO 					NR 5 CYL	CRACKED 	W				A				UNSCHED LANDING 				E			VIBRATION/BUFFET 			CR	CRUISE 	1			CA								2001409R			(CAN)IN CRUISE ENGINE BEGAN TO RUN ROUGH, AIRCRAFT LANDED AT NEAREST AIRPORT AND GROUND INSPECTION FOUND #5 CYLINDER CRA	CKED AT THE EXHAUST VALVE & SPARKK PLUG HOLE. CYLINDER REPLACED & AIRCRAFT RETURNED T O SERVICE.					1	H	7	1 	3O	3	O	NT	3A13 	E273				 
1996091900556	19960919	00556	SW 	1996	9	19	CA960126041 	1	19950920	G	2913		HYD POWER PACK 			GULSTM	112 	112TCA 	7630307	SW 										MLG	FAILED STATOR 	W				A				UNSCHED LANDING 				O			OTHER 			AP	APPROACH 	1			CA											(CAN)THE PILOT NOTICED THAT HE HAD AN UNDERCARRIAGE PROBLEM CAUSED BY THE MOTOR OF THE HYDRAULIC POWER PACK. FAILED STAT	OR.					1	L	7	1 	3O				A12SO 					 
1996091900564	19960919	00564	SW 	1996	9	19	CA960129005 	1	19951216	G	5312	222031506003	BULKHEAD 			BELL 	222 	222 	1182122	SW 										LIFT BEAM AREA	CRACKED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			4717 								(CAN)WHAT APPEARED TO BE A 1" CRACK WAS DETECTED ON THE FORWARD FACE OF THE LIFT BEAM BULKHEAD P/N 222-031-506-003. IT W	AS RADIATING FROM THE LOWER HOLE OF THE AFT LEFT TRANSMISSION NODAL BEAM TO AIRFRAME ATTACHMENT HI LOK PIN HOLE. AN ATT	EMPT TO MAP OUT THE EXTENT OF THE CRACK BY EDDY CURRENT WAS INCONCLUSIVE. AFTER REMOVAL OF THE TRANSMISSION, THE NODAL B	EAM AND THE ATTACHMENT FITTING P/N 222-031-592-103, FIVE (5) CRACKS WERE FOUND TO A TOTAL LENGTH OF ALMOST 5". A REPAIR 	SCHEME HAS BEEN DEVELOPED BY BELL ENGINEERING.		1	G	7	2 	3U				H9SW 					 
1996091900565	19960919	00565	SO 	1996	9	19	CA960129006 	1	19950716	G	3230	AN2420A	BOLT CLEVIS 	PIPER 	9652200 	PIPER 	PA34 	PA34200 	7103405	SO 										NLG SPRING	MIS INSTALLED 	W				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			CA											(CAN)THE NOSE LANDING GEAR WOULD NOT EXTEND PRIOR TO LANDING. THE PILOT ATTEMPTED TO LAND ON THE MAIN GEAR ONLY BUT STAL	LED THE AIRCRAFT, TOUCHED DOWN HARD AND COLLAPSED THE MAIN GEAR. EXAMINATION REVEALEDTHAT THE NOSE GEAR HAD JAMMED DUE T	O INTERFERENCE BETWEEN THE NOSE GEAR CENTERING SPRING CLEVIS BOLT AND THE NOSE GEAR DOOR ACTUATION AFT TUBE ASSEMBLY IN 	THE NOSE WHEEL WELL. THE CLEVIS BOLT HAD BEEN INSTALLED WITH THE HEAD IN THE UP POSITION. THE PIPER SENECA SERVICE MANUA	L AND FAA AD 92-13-05, SERVICE BULLETIN NO.893 AND SERVICE LETTER NO.852 STATE THAT THE CLEVIS BOLT MUST BE INSTALLED WI	TH THE HEAD DOWN TO PREVENT INTERFERENCE AS THE NOSE GEAR RETRACTS OR EXTENDS.	1	L	7	2 	3O				A7SO 					 
1996091900572	19960919	00572	CE 	1996	9	19	CA960129017 	1	19951212	G	2410	640932	DRIVE GEAR 	PRESTOLITE 	ALV9407 	CESSNA	310 	310R 	2074245	CE 										LH ALTERNATOR	PITTED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			1417 			4J000124					(CAN)WHILE CARRYING OUT AD 76-02-07 & ALTERNATOR DRIVE INSPECTION, ALTERNATOR DRIVE GEAR WAS FOUND PITTED AND REPLACED.						1	L	7	2 	3O				3A10 					 
1996091900573	19960919	00573	SO 	1996	9	19	CA960129019 	2	19950413	G	8520		CONNECTING ROD 			CESSNA	185 	185B 	2072806	CE 	CONT 	O470 	IO470F 	17026	SO 					#6 CYLINDER	BROKEN 	W				A				UNSCHED LANDING 				E	K	Y	VIBRATION/BUFFET 	FLUID LOSS 	ENGINE STOPPAGE 	CL	CLIMB 	1			CA				1042 				CS769553F			(CAN)AIRCRAFT WAS IN CLIMB AT LOW ALTITUDE WHEN FAILURE OF #6 CYLINDER CONNECTING ROD CAUSED A SUDDEN AND COMPLETE STOPP	AGE OF THE ENGINE. THE BROKEN CONNECTING ROD PIERCED THE CRANKCASE. THE AIRCRAFT CARRIED OUT A FORCED LANDING IN A FIELD	.				1	H	7	1 	3O	3	O		3A24 	3E1				 
1996101000418	19961010	00418	SW 	1996	10	10	CA960131202 	1	19951208	G	6322	369H56555	BEARING 			HUGHES	500N 	500N 	3027374	SW 										BLOWER ASSEMBLY	FAILED 	W				A				UNSCHED LANDING 				O			OTHER 			CR	CRUISE 	1			CA			950 								(CAN)UPPER BEARING OF OIL COOLER BLOWER ASSEMBLY FAILED CAUSING LOSS OF BELT TENSION AND VIBRATION. BEARING DID NOT SEIZ	E, INDICATIONS TO PILOT WERE A BANG FOLLOWED BY SQUEALING OF THE BELT AND RUMBLING OFTHE BLOWER ASSEMBLY. A PRECAUTIONAR	Y LANDING WAS CARRIED OUT. THERE WAS NO LOSS OF POWER OR CONTROL OF AIRCRAFT.				1	G	7	1 	3U			NC	H3WE 					 
1996101000424	19961010	00424	CE 	1996	10	10	CA960202009 	1	19950715	G	5520	MS276404	BEARING 	CESSNA 		CESSNA	340 	340CESSNA 	2076404	CE 	CONT 	O520 	TSIO520C 	17040	SO 					ELEV	FAILED 	W				K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			CA								L217790K			(CAN)AIRCRAFT EXPERIENCED HUNTING WHEN AUTOPILOT WAS SELECTED. LATER INVESTIGATION FOUND THE BEARING MS276404 WAS BROKE	N IN PIECES AND LYING IN THE EMPENAGE. SUBMITTER NOTES THE DIFFICULTY IN INSPECTING THIS LOCATION AND ACCESS HAD TO BE 	G AINED THROUGH SMALL INSPECTION PANEL LOCATED IN THE EMPENAGE.				1	L	7	2 	3O	3	O		3A25 	E8CE				 
1996101000438	19961010	00438	NE 	1996	10	10	CA960202024 	2	19951206	G	7261		O-RING 								PWA 	PWA120	PW125B 		NE 					FRONT INLET CASE	CUT 	W				E				ENGINE SHUTDOWN 				J	K		WARNING INDICATION 	FLUID LOSS 		CR	CRUISE 	1			CA			5174 	5174 				125076			(CAN)#1 ENGINE WAS SHUTDOWN BECAUSE OF LOW OIL PRESSURE. POST FLIGHT INSPECTION FOUND THE ENGINE SOAKED WITH OIL. THE 	PROP SEAL WAS REPLACED, BUT THE PROBLEM WAS NOT CURED. FURTHER INVESTIGATION FOUND AN OIL LEAK AT THE FRONT INLET CASE 	CO VER DUE TO A PINCHED/CUT "OIL" RING.									4	T			E20NE				 
1996101000896	19961010	00896	EA 	1996	10	10	CA960212018 	1	19951214	G	3250	C6CF12425	CONTROL CABLE 	DHAV 	C6CF12251 	DHAV 	DHC6 	DHC6 	2802606	EA 										NOSE STEERING	BROKEN 	W				A				UNSCHED LANDING 				F			FLT CONT AFFECTED 			TO	TAKEOFF 	1			CA											(CAN)LOOSE NOSE WHEEL TILLER NOTED ON PREFLIGHT. ON TAKEOFF ROLL PILOT REQUIRED A LOT OF LEFT RUDDER. GROUND OBSERVER TO	LD CREW THAT NOSE WHEEL NOT CENTERED. AIRCRAFT LANDED IMMEDIATELY WITH SOME DIFFICULT Y, AS AIRCRAFT VEERED RIGHT. INSPE	CTION FOUND 4 STRANDS OF 7 BROKEN ON NOSE WHEEL STEERING CABLE.				1	H	7	2 	3T			RT	A9EA 					 
1996101000931	19961010	00931	CE 	1996	10	10	CA960221204 	1	19950725	G	3260	20700291	SWITCH 			CESSNA	177 	177RG 	2073709	CE 										GEAR PROX	BURNED CONTACTS 	W				K				NONE 				P			NO WARNING INDICATION 			IN	INSP/MAINT 	1			CA			2400 								(CAN)GEAR PROXIMITY SWITCH FAILED. GEAR DOWN AND LOCKED BUT LIGHT FAILED TO COME ON. SWITCH REPLACED AND AIRCRAFT RETURN	ED TO SERVICE.					1	H	7	1 	3O				A20CE 					 
1996121200513	19961212	00513	NE 	1996	12	12	CA960223015 	2	19950904	G	8530	399353	CYLINDER 			DHAV 	DHC2 	DHC2MK1 	2800102	EA 	PWA 	R985 	R985AN14B 	52008	NE 					#9 CYLINDER	HEAD SEPARATED 	W				C	D	E		ABORTED TAKEOFF 	RETURN TO BLOCK 	ENGINE SHUTDOWN 		E	B		VIBRATION/BUFFET 	SMOKE/FUMES/ODORS/SPARKS 		TO	TAKEOFF 	1			CA								JP208229			(CAN) CYLINDER HEAD SEPARATED FROM CYLINDER BARREL OF #9 CYLINDER.						1	H	7	1 	3R	3	R		A806 	5E1				 
1997011600108	19970116	00108	EA 	1997	1	16	CA960306004 	2	19951205	G	8550	9645200	BREATHER 								LYC 	O360 	IO360C1E6 	41514	EA 					BREATHER OPENING	BLOCKED 	W				E				ENGINE SHUTDOWN 				E	K		VIBRATION/BUFFET 	FLUID LOSS 		CR	CRUISE 	1			CA								L100267A			(CAN) DURING CRUISE, PILOT NOTICED ROUGHNESS IN THE RIGHT ENGINE AND HE REDUCED POWER. THE PILOT ELECTED TO SHUT THE ENG	INE DOWN AND RETURN TO ORIGIN, AS HE DID WITHOUT FURTHER INCIDENT. INSPECTION REVEALED THAT THE ENGINE BREATHER ICE CONT	ROL APERTURE HAD FROZEN OVER WHICH RESULTED IN EXCESSIVE CRANKCASE PRESSURE THAT DISLODGED THE CRANKSHAFT SEAL CAUSING S	UFFICIENT OIL LOSS TO CREATE THE ROUGH RUNNING. THE ENGINE CRANKCASE WAS ALSO CRACKED ABOVE THE NUMBER THREE CYLINDER BA	SE. SUBSEQUENT INSPECTION REVEALED A BROKEN CONNECTING ROD ON #3 CYLINDER. THE ENGINE BREATHER WAS MODIFIED TO A FLUTED 	APERTURE.						3	O			1E10				 
1997011600113	19970116	00113	SO 	1997	1	16	CA960311004 	2	19951120	G	7414		MAGNETO 			CESSNA	421 	421C 	2076016	CE 	CONT 	O520 	GTSIO520L 	17032	SO 					LEFT ENGINE	OUT OF ADJUST 	W				C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			R	F		PARTIAL RPM/PWR LOSS 	FLT CONT AFFECTED 		TO	TAKEOFF 	1			CA								239802R			(CAN) ON TAKEOFF, THE LEFT ENGINE SUFFERED A POWER LOSS, CAUSING A YAW TO THE LEFT. THE PILOT WAS UNABLE TO CONTROL OR 	STOP THE AIRCRAFT DUE TO ICY CONDITIONS AND THE AIRCRAFT RAN OFF THE END OF THE RUNWAY INTO GRASS AND BUSHES. INSPECTIO	N BY MAINTENANCE REVEALED INCORRECT MAGNETO TIMING, BELOW STANDARD FUEL FLOWS, AND LOW MANIFOLD PRESSURE ON THE LEFT ENG	INE. MAGNETO TIMING AND FUEL FLOWS WERE RETURNED TO THEIR PROPER SETTINGS AND AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	3O	3	O		A7CE 	E7CE				 
1996110100063	19961101	00063	SO 	1996	11	1	CA960312201 	2	19951219	G	8520		CRANKSHAFT 			CESSNA	206 	U206D 	2073342	CE 	CONT 	O520 	IO520F 	17032	SO 	MCAULY	2A34C	D2A34C58 	GL 	#4 & #6 CRANKS	BROKEN 	W				E				ENGINE SHUTDOWN 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			CA				1140 				247653R	754438		(CAN)ENGINE TEARDOWN FOLLOWING SUDDEN FAILURE. CRANKSHAFT BROKEN IN THREE PIECES. THE BREAKS ARE THROUGH THE NUMBER 4 AN	D 6 CRANK CHEEKS. ALSO SEVERE DAMAGE TO SEVERAL CONRODS, COUNTERWEIGHTS AND INTERIOR OF CASE. CRANKSHAFT DID NOT SHOW A	NY SIGNS OF LACK OF LUBRICATION.				1	H	7	1 	3O	3	O		A4CE 	E5CE	5	C	P3EA	 
1996110100414	19961101	00414		1996	11	1	CA960320005 	2	19951115	G	8520		CAMSHAFT 			PIPER 	PA28 	PA28180 	7102808	SO 	LYC 									LOBES	PITTED CORRODED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN)ENGINE WAS BEING INSPECTED PRIOR TO THE EXTENSION PER AMA 571-103/1. CAMSHAFT AND FOLLOWERS CORRODED AND PITTED. AL	SO, 3 CRACKED CYLINDERS.					1	L	7	1 	3O				2A13 					 
1996111400618	19961114	00618	NM 	1996	11	14	CA960418012 	1	19951219	G	2435		COIL 	LUCAS 	23088002A 	DHAV 	DHC8 	DHC8102 	2809003	NM 										START/GEN	OPEN CIRCUIT 	W				B				EMER. DESCENT 				H	P		ELECT. POWER LOSS-50 PC 	NO WARNING INDICATION 		CR	CRUISE 	1			CA											(CAN)AIRCRAFT LOST PRESSURIZATION IN FLIGHT. FOLLOWING EMERGENCY DESCENT CREW NOTICED THE LH DC BUSSES WERE OFF-LINE WIT	HOUT INDICATION.EMERGENCY PROCEDURES FOR FAILED DC GENERATOR CARRIED OUT, AT WHICH TIME BUSS TIE CLOSED. THE STARTER GEN	ERATOR CAUTION LIGHT CAME ON, BUT STARTER GENERATOR WOULD NOT RESET. GENERATOR TEARDOWN SHOWED AN OPEN CIRCUIT IN THE ST	ATOR COIL.			2	H	7	2 	4T			RT	A13NM 					 
1996111400632	19961114	00632	EA 	1996	11	14	CA960422001 	2	19950602	G	7250	3010351	BLADE 	PWA 	PT6A6 						PWA 	PT6 	PT6A6 	52043	EA 					CT VANE	BURNT BROKEN 	W				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			CA			10162	1114 		20166		20166			(CAN)ENGINE FAILED IN CRUISE. ENGINE TEARDOWN AT MANUFACTURER AND METALLURGICAL ANALYSIS REVEALED A VANE FRACTURED DUR T	O THERMAL FATIGUE. OVERTEMP MAY HAVE CONTRIBUTED. TSB REPORT LP 119/05 REFERS.										3	T			E4EA				 
1996111400633	19961114	00633	NE 	1996	11	14	CA960422002 	2	19950606	G	7260	311169301	SPUR GEAR 								PWA 	120 	PW120 		NE 					PUMP DRIVE	BROKEN TEETH 	W				A				UNSCHED LANDING 				Y			ENGINE STOPPAGE 			CR	CRUISE 	1			CA			14170	9661 				120278			(CAN)LEFT ENGINE FAILED IN CRUISE FOLLOWED BY OIL PRESSURE WARNING. FUEL PUMP DRIVE SHAFT SPUR GEAR AND MATING GEARSHAFT	 FAILED. 12 TEETH FAILED ON SPUR GEAR DUE TO REVERSE BENDING FATIGUE INITIATING AT TH E TOOTH FILLET RADIUS. TSB REPORT 	LP 119/95 REFERS.									4	T			E20NE				 
1996121900814	19961219	00814	EU 	1996	12	19	CA960529013 	1	19950909	G	1100		PLACARD 			WSK 	M18 	M18DROMADER 	9810102	EU 										FUEL VENT/DRAIN	UNCLEAR MARKING 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA											(CAN) PILOT REPORTS THAT THE MARKING FOR THE FUEL VENT AND FUEL DRAINS ARE UNCLEAR.						1	L	7	1 	3O				A47EU 					 
1996121200210	19961212	00210	NE 	1996	12	12	CA960612025 	2	19951218	G	7250	3035664	PT STATOR 			DHAV 	DHC8 	DHC8101 	2809002	NM 	PWA 	120 	PW120A 		NE 					FRONT FLANGE	CRACKED 	W				K				NONE 				O			OTHER 			UK	UNKNOWN 	1			CA			21078	16298				120107			(CAN)OPERATOR REPORTED A POWER TURBINE RUB. THE CAUSE OF THE PT TIP RUB WAS A CRACK IN THE 2ND STAGE PT STATOR ON THE FR	ONT FLANGE. THIS STATOR WAS PRE-SB 20952, THEREFORE DID NOT HAVE THE EXTRA STRENGTHEN ING WELD AROUND THE FRONT FLANGE.					2	H	7	2 	4T	4	T	RT	A13NM 	E20NE				 
1996121200214	19961212	00214	NE 	1996	12	12	CA960612029 	2	19951019	G	7210	310703301	BEARING 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					RGB NR 15 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			11491	2318 				120880			(CAN)METAL ON THE RGB CHIP DETECTOR. #15 BEARING OUTER RACE HEAVILY SPALLED OVER 60 PERCENT OF RACEWAY. ALSO ON RACEWAY,	 WERE ROWS OF SMALL PITS TYPICAL OF ELECTRICAL DISCHARGE PITTING. NO MAGNETISM ON THESTEEL COMPONENTS INDICATES THAT PIT	TING IS DUE TO A SOURCE OF ELECTRICAL DISCHARGE OTHER THAN LIGHTNING STRIKE.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200215	19961212	00215	NE 	1996	12	12	CA960612030 	2	19951102	G	7230	311362301	BEARING 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	120 	PW120 		NE 					GAS GEN NR 5 BRG	DISINTEGRATED 	W		A		A	E			UNSCHED LANDING 	ENGINE SHUTDOWN 			A			FLAME/FIRE 			CR	CRUISE 	1			CA			6339 					121116			(CAN)IN CRUISE, SMOKE IN COCKPIT AND FLAMES OBSERVED COMING FROM ENGINE EXHAUST DUCT. ENGINE SECURED. GAS GENERATOR CHIP	 DETECTOR HAD LARGE AMOUNTS OF FLAKES AND FILINGS. #5 BEARING FAILED WITH MAJOR ROLLE R END WEAR ON THE REAR OF EACH ROL	LER AND DISTORSION ON ALL OF THE BEARING CAGE ROLLER POCKETS. POSSIBLE OIL STARVATION.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200217	19961212	00217	NE 	1996	12	12	CA960612032 	2	19951221	G	7210	310703301	BEARING 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					NR 15 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			13660	4836 				120492			(CAN)METAL ON THE RGB CHIP DETECTOR, #15 BEARING INNER RACE SPALLED. NO OBVIOUS CAUSE FOR THE FAILURE AND NO EVIDENCE OF	 PITTING BY ELECTRICAL DISCHARGE.					2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200218	19961212	00218	NE 	1996	12	12	CA960612033 	2	19951218	G	7230	310815201	BEARING 			EMB 	120 	EMB120 	3260201	SO 	PWA 	118 	PW118 		NE 					NR 5 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			14247	7675 				115208			(CAN)METAL FOUND IN AN OIL SAMPLE. #5 BEARING ROLLER LIGHTLY SPALLED AND THE BEARING CAGE DAMAGED IN THE AREA OF THE SPA	LLED ROLLER. ASSOCIATED DAMAGE: GAS GENERATOR CASE PART NUMBER 3110202-24 REVEALED 15CRACKS IN THE #5 BEARING AREA.					2	L	7	2 	4T	4	T	RT	A31SO 	E20NE				 
1996121200219	19961212	00219	NE 	1996	12	12	CA960612034 	2	19951010	G	7250	310882301	POWER TURBINE 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					1ST STAGE DISC	BLADE SHIFTED 	W		A		A	E			UNSCHED LANDING 	ENGINE SHUTDOWN 			R			PARTIAL RPM/PWR LOSS 			CR	CRUISE 	1			CA			13690	9105 				120435			(CAN)IN FLIGHT SHUTDOWN DUE TO INTERNAL FAILURE. THE PRIMARY FAILURE WAS FOUND TO BE A BLADE SHIFT IN THE 1ST STAGE POW	ER TURBINE DISC AND BLADE ASSEMBLY. AN ECHELON OF FIVE BLADES MOVED FORWARD IN THE ROOT FLEXING UNTIL THE LEAD BLADES C	ONTACTED THE 1ST STAGE PT STATOR ASSEMBLY. THIS RESULTED IN THE FRACTURE OF THE STATOR INTO SEGMENTS AND INGESTION OF T	HE PARTS BY THE POWER TURBINE.			2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200220	19961212	00220	NE 	1996	12	12	CA960612035 	2	19951010	G	7210	310924401	BEARING 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					RGB NR 15 BRG	CRACKED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			10543	3460 				120917			(CAN) OPERATOR REPORTED METAL CONTAMINATION OF THE RGB OIL SYSTEM. NR 15 BEARING HEAVILY SPALLED ON THE ROLLERS AND OVE	R 120 DEGREES OF THE OUTER RACE. THE INNER RACE ALSO HAD AN AXIAL CRACK COMPLETELY THROUGH. UNABLE TO DETERMINE IF THE	 INNER RACE CRACK LED TO THE SPALLING OR IF THE SPALLING LED TO THE CRACK.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200221	19961212	00221	NE 	1996	12	12	CA960612036 	2	19951030	G	7230		BEARING 			EMB 	120 	EMB120 	3260201	SO 	PWA 	118 	PW118 		NE 					LP COMPRESSOR	SPALLED 	W		A		O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			CA			11888	1490 							(CAN) LOSS OF OIL PRESSURE CAUSED BY A CRACKED OIL COOLER. ENGINE SHUTDOWN. AT ENGINE TEARDOWN, NR 3 BEARING WAS BURNT	 AND ERODED WITH THE BEARING BALLS REDUCED TO A FRACTION OF THEIR SIZE. AXIAL AND RADIAL LOCATION OF THE LP COMPRESSOR 	WAS LOST ALLOWING IT AND THE LP TURBINE ASSEMBLY TO SHIFT FORWARD AND COME IN CONTACT WITH THE NR 2 BEARING HOUSING AND 	THE LP IMPELLER HOUSING. HEAVY RUBBING DAMAGE AT EACH LOCATION.			2	L	7	2 	4T	4	T	RT	A31SO 	E20NE				 
1996121200222	19961212	00222	EU 	1996	12	12	CA960612037 	1	19951030	G	6130	120413	BRAKE 	PWA 		AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					PROPELLER	BURNT 	W				E	F			ENGINE SHUTDOWN 	ACTIVATE FIRE EXT. 			B			SMOKE/FUMES/ODORS/SPARKS 			TX	TAXI/GRND HDL 	1			CA			13626	4440 		120413		120413			(CAN)WHILE GROUND RUNNING, PROPELLER BRAKE CAUGHT ON FIRE. FUEL SHUT OFF AND "HALON" EXTINGUISHER ACTIVATED WHICH PUT T	HE FIRE OUT IN THE NACELLE HOWEVER, A CONTINUING FIRE IN THE INTAKE HAD TO BE EXTINGUI SHED BY DISCHARGE OF A "FORAY" DR	Y CHEMICAL. ENGINE SENT TO OVERHAUL SHOP WHERE IT WAS DISASSEMBLED TO INVESTIGATE THE CONDITION AND EXTENT OF CONTAMINAT	ION OF THE GAS PATH WITH EXTINGUISHING AGENT. ALL INTERNAL COMPONENTS CLEANED AND INSPECTED FOR CORROSION. NO CORROSION 	FOUND.		2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200223	19961212	00223	NE 	1996	12	12	CA960612038 	2	19951108	G	7230	310815201	BEARING 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					HP COMP NR 5 BRG	DISINTEGRATED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			9996 					120925			(CAN)METAL FOUND ON THE CHIP DETECTOR. DISASSEMBLY OF THE ENGINE REVEALED THAT #5 BEARING HAD DISINTEGRATED. THE EXTENT 	OF THE DAMAGE TO THE BEARING PARTS WAS SUCH THAT THE FAILURE MODE CANNOT BE ASCERTAIN ED ALTHOUGH THE GENERAL APPEARANCE	 OF THE BEARING DID NOT SUGGEST OVERHEATING OR LACK OF LUBRICATION.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200224	19961212	00224	NE 	1996	12	12	CA960612039 	2	19950918	G	7250	MS970511	BOLT 	PWA 	310642201 	AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					INTER CASE FLANG	BROKEN-CORRODED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			1792 			710		120867			(CAN)ENGINE REMOVED DUE TO TURBINE DAMAGE. TEARDOWN REVEALED 2 TURBINE INTERSTAGE CASE MOUNTING BOLTS FAILED DUE TO CORR	OSION ON THE MOUNTING FLANGE. BOLTS HAD BEEN INSTALLED NEW AT SHOP VISIT 1792 HOURS P REVIOUS. THE CAUSE OF THE CORROSIO	N COULD NOT BE ASCERTAINED. THIS INTERSTAGE CASE IS PRE SB 21175.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200225	19961212	00225	NE 	1996	12	12	CA960612040 	2	19950919	G	7210	310703301	BEARING 	PWA 		AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	120 	PW120 		NE 					RGB NR 15 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			7285 			121125		121125			(CAN)REDUCTION GEAR BOX PRODUCING METAL. #15 BEARING INNER RACE SPALLED AND ELECTRICAL DISCHARGE PITTING MARKS WERE FOUN	D ON THE ROLLERS AND OUTER RACE. THREE MORE BEARINGS IN THIS UNIT ALSO HAD ELECTRICALPITTING ALTHOUGH NO SIGNIFICANT LEV	EL OF MAGNETISM WAS FOUND ON STEEL PARTS, THEREFORE, NO LIGHTNING STRIKE.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200226	19961212	00226	NE 	1996	12	12	CA960612041 	2	19950922	G	7250	310920201	BLADE 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					LP TURB	FRACTURED 	W		A		K				NONE 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			CA			11420	5867 				120610			(CAN)ENGINE REMOVED FOR TURBINE BLADE DAMAGE. FOUR LOW PRESSURE TURBINE BLADES FRACTURED AT APPROXIMATELY 1/3 OF THE WAY	 FROM THE TIPS. SECTIONING OF ONE OF THE FRACTURED BLADES SHOWED EXTENSIVE CORROSION IN THE HOLLOW CORE WITH LAYERS OF 	MATERIAL FLAKING OFF. SECTIONING OF ONE OTHER BLADE FROM THE ASSEMBLY ALSO REVEALED CORROSION IN THE CORE. THIS TYPE OF 	BLADE BEING REPLACED BY A SOLID BLADE PER SB 20465.			2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200227	19961212	00227	NE 	1996	12	12	CA960612042 	2	19951005	G	7210	310703301	BEARING 	PWA 		AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					RGB NR 15 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CA			5634 			121148		121148			(CAN)REDUCTION GEAR BOX PRODUCING METAL. #15 BARING BALLS AND OUTER RACE HEAVILY SPALLED. OTHER BEARINGS IN THE SAME GEA	RBOX HAD CLUSTER PITTING TYPICAL OF ELECTRICAL DISCHARGE. THE LACK OF RESIDUAL MAGNET ISM ON THE STEEL COMPONENTS MAKES 	IT UNLIKELY THAT THE ELECTRICAL DISCHARGE WAS DUE TO LIGHTNING STRIKE.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200228	19961212	00228	NE 	1996	12	12	CA960612043 	2	19950803	G	7210	310062301	BEARING 	PWA 		EMB 	120 	EMB120 	3260201	SO 	PWA 	118 	PW118 		NE 					RGB NR 19 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CA			12700	3301 		115378		115378			(CAN)RGB REPORTED MAKING METAL. #19 BEARING SPALLED AND INNER RACE CRACKED. 1ST STAGE OIL JETS WERE FLOW TESTED AND 3 NO	ZZLES WERE FOUND BLOCKED BY PLASTIC MEDIA WHICH IS NORMALLY USED AS ABRASIVE BLAST MA TERIAL. IT IS LIKELY THAT THE GEAR	BOX WAS NOT PROPERLY FLUSHED AT THE PREVIOUS SHOP VISIT.				2	L	7	2 	4T	4	T	RT	A31SO 	E20NE				 
1996121200229	19961212	00229	NE 	1996	12	12	CA960612044 	2	19950721	G	7210	310062301	BEARING 	PWA 		EMB 	120 	EMB120 	3260201	SO 	PWA 	118 	PW118 		NE 					RGB NR 19 BRG	CRACKED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			13672	8624 		115141		115141			(CAN)DURING SCHEDULED OVERHAUL, #19 BEARING INNER RACE FOUND CRACKED. MARKS ON THE PROPSHAFT AND INNER RACE OF THE BEARI	NG INDICATE A PIECE OF GRIT SCORED THE RACE DURING PREVIOUS INSTALATION IN THE AREA O F THE CRACKED RACE.					2	L	7	2 	4T	4	T	RT	A31SO 	E20NE				 
1996121200230	19961212	00230	NE 	1996	12	12	CA960612045 	2	19950815	G	7210	310924401	BEARING 	PWA 		AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					RGB NR 15 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			CA			11492	2940 		120807		120807			(CAN)REDUCTION GEAR BOX REMOVED FOR METAL ON THE CHIP DETECTOR. #15 BEARING HAD ONE ROLLER HEAVILY SPALLED AS WELL AS EL	ECTRICAL PITTING AND MECHANICAL DENTS ON THE RACEWAY. SEVERAL STEEL COMPONENTS SHOWEDHIGH LEVELS OF MAGNETISM CONSISTENT	 WITH A LIGHTNING STRIKE.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200231	19961212	00231	NE 	1996	12	12	CA960612046 	2	19950918	G	7250	311260201	BLADES 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					LP TURBINE DISC	FRACTURED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			13849	9620 				120353			(CAN)LOW PRESSURE TURBINE BLADES FOUND DAMAGED DURING GROUND SERVICING. 4 LP BLADES POST SB 20465 FRACTURED APPROXIMATEL	Y 0.5 INCH FROM THE TIP. MICRO ANALYSIS INDICATED MATERIAL PROPERTY DEGRADATION TYPIC AL OF OVERTEMPERATURE ALTHOUGH CON	TINUOUS ENGINE MONITORING OF THE ENGINE PARAMETERS BY THE OPERATOR SHOWS "NO" OVERTEMP EVENTS.				2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200232	19961212	00232	NE 	1996	12	12	CA960612047 	2	19950906	G	7210	310703201	BEARING 			AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					RGB NR 19 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			10258	3524 				120925			(CAN)METAL CONTAMINATION DETERMINED BY SAMPLING. #19 BEARING INNER RACE HEAVILY SPALLED. NO DETERMINATION AS TO CAUSE FO	R THE FAILURE.					2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200233	19961212	00233	NE 	1996	12	12	CA960612048 	2	19950401	G	7250	311260201	BLADE 			DHAV 	DHC8 	DHC8101 	2809002	NM 	PWA 	120 	PW120A 		NE 					LP TURBINE	FRACTURED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			10818					120900			(CAN)ROUTINE BORESCOPE INSPECTION FOUND 1 FRACTURED LOW PRESSURE TURBINE BLADE. MICRO ANALYSIS OF FAILED BLADE SHOWED PA	RTIAL GAMMA PRIME SOLUTIONING, INDICATIVE OF TEMPERATURE EXPOSURE GREATER THAN 2000F.LP STATOR ASSEMBLY HAD SEVERAL VANE	S BUCKLED AT THE 6 O'CLOCK POSITION, INDICATIVE OF A LOCALIZED OVERTEMPERATURE, PROBABLY A HOT START.				2	H	7	2 	4T	4	T	RT	A13NM 	E20NE				 
1996121200234	19961212	00234	NE 	1996	12	12	CA960612049 	2	19950529	G	7210	310874601	HELICAL GEAR 	PWA 		DHAV 	DHC8 	DHC8102 	2809003	NM 	PWA 	120 	PW120A 		NE 					LH 1ST STAGE RGB	SPALLED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			14262	5107 		120013		120013			(CAN)REDUCTION GEAR BOX PRODUCING METAL. LEFT HAND FIRST STAGE HELICAL GEAR SPALLED HEAVILY ON 120 DEGREES ARC OF TEETH.	 CAUSE UNDETERMINED.					2	H	7	2 	4T	4	T	RT	A13NM 	E20NE				 
1996121200235	19961212	00235	NE 	1996	12	12	CA960612050 	2	19950527	G	7210	310960401	PINION GEAR 	PWA 		AEROSP	ATR42 	ATR42* 	8680900	EU 	PWA 	PW121 	PW121 	52124	NE 					RH SECOND STAGE	SPALLED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			5570 			121136		121136			(CAN)ROUTINE FILTER CHECK FOUND ALLOY STEEL FLAKES IN THE SCAVENGE FILTER. RIGHT HAND SECOND STAGE PINION GEAR HAD LOST 	MATERIAL FROM PATCHES IN THE FRONT 25 PERCENT OF THE TOOTH. #15 BEARING RETAINING BOL TS WERE ALL LOOSE AND WERE REMOVED	 BY FINGERS ONLY. #15 BEARING BORE WAS A POST SB 20985 SLEEVE, WAS OVERSIZE, OUT OF ROUND AND OUT OF TRUE POSITION AND A	LIGNMENT WITH THE #18 AND #19 BORES.			2	H	7	2 	4T	4	T	RT	A53EU 	E20NE				 
1996121200236	19961212	00236	NE 	1996	12	12	CA960612051 	2	19950718	G	7210	310703301	BEARING 	PWA 		EMB 	120 	EMB120 	3260201	SO 	PWA 	118 	PW118 		NE 					RGB NR 15 BRG	SPALLED 	W		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			17693	11256		115118		115118			(CAN)ROUTINE CHECK, METAL ON THE CHIP DETECTOR. #15 BEARING OUTER RACE SPALLED. ELECTRICAL PITTING ON #15, #18 AND #19 B	EARINGS AND HIGH LEVELS OF RESIDUAL MAGNETISM ON THESE PARTS INDICATES THAT THE ENGIN E MAY HAVE BEEN SUBJECTED TO LIGHT	NING STRIKE.				2	L	7	2 	4T	4	T	RT	A31SO 	E20NE				 
1997112600296	19971126	00296	GL 	1997	11	26	CA970902016 	3	19950815	G	6111		BLADES 			CESSNA	180 	180 	2072602	CE 	CONT 	O470 	O470K 	17026	SO 	MCAULY	2A34C	2A34C66 	GL 	PROP	CORRODED 	W				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CA			1342 	531 				49358R	805190		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CORROSION WAS FOUND ON THE PROPELLER BLADES AND THE CYLINDER WAS FOUN	D TO BE OVERSIZE.					1	H	7	1 	3O	3	O	NC	5A6 	E273	5	C	P3EA	 
1998043000053	19980430	00053	CE 	1998	4	30	CA971106001 	1	19951021	G	3213	AN625A	BOLTS 			CESSNA	180 	180C 	2072608	CE 										LT MLG AXLE	BROKEN 	W				K				NONE 				G			MULTIPLE FAILURE 			LD	LANDING 	1			CA											(CAN) DURING A HARD LANDING, THE LEFT MAIN GEAR AXLE SEPARATED FROM THE LANDING GEAR. TWO OF THE FOUR BOLTS SECURING TH	E AXLE ON THE GEAR HAD BROKE AND TWO WERE STRIPPED.					1	H	7	1 	3O				5A6 					 
1995042800727	19950428	00727	EA 	1995	4	28	CHI1426 	1	19950215	G	6320	114DS6653	BEARING 		234D62006 	BOEING	234 	234 	1385049	EA 										PINION ASSY	PITTED 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	237CH	1294 			VB286G	MJ003				BEARING ROLLERS BREAKING DOWN AFTER SHORT PERIOD OF RUNNING TIME. PITTING WAS THE RESULT OF THE FATIGUE ON THE BEARING 	ROLLERS. WONDER IF THE ADDITION OF THE COPPER PLATING ON THE ID OF THE BEARING WAS TAKEN INTO ACCOUNT FOR THE OVERALL F	ITS AND CLEARANCES BETWEEN THE BEARING AND PINION SHAFT. MIN. CLEARANCE 0.0008T; ACTUAL 0.0025T. (X)				2	G	7	2 	4U				H9EA 					 
1995042800728	19950428	00728	EA 	1995	4	28	CHI1427 	1	19950216	G	6320	114DS2407	BEARING 	SKF 	234D22004 	BOEING	234 	234 	1385049	EA 										PINION ASSY	SPALLED 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	237CH	817 			VB121	MJ003				SPALLED ROLLER. THE TRANSMISSION WAS REMOVED FOR MAKING CHIPS. FOUND INPUT PINION BEARING ROLLERS SPALLED. (X)						2	G	7	2 	4U				H9EA 					 
1995042800729	19950428	00729	EA 	1995	4	28	CHI1428 	1	19950216	G	6320	114DS2823	BEARING 		234D22004 	BOEING	234 	234 	1385049	EA 										SECOND STAGE	SPALLED 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	237CH	513 			VB280C	MJ003				SPALLED ROLLERS. AFT TRANSMISSION WAS REMOVED FOR MAKING CHIPS. FOUND SPALLED ROLLERS ON THE SECOND STAGE PLANET BEARI	NG. (X)					2	G	7	2 	4U				H9EA 					 
1995042800730	19950428	00730	EA 	1995	4	28	CHI1429 	1	19950216	G	6320	114DS2512	BEARING 		234D22004 	BOEING	234 	234 	1385049	EA 										FAN DRIVE	SPALLED 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	237CH				A91595	MJ003				SPALLED BALL AND OUTER RACE. AFT TRANSMISSION WAS REMOVED FOR MAKING CHIPS. FOUND SPALLED BALLS AND OUTER RACE ON FAN D	RIVE HOUSING ASSEMBLY BEARING. (X)					2	G	7	2 	4U				H9EA 					 
1995102000112	19951020	00112	NE 	1995	10	20	CHI1477 	2	19950821	G	7210	M2001517	SWITCH 			BOEING	234 	234 	1385049	EA 	LYC 	AL5512	AL5512 	41581	NE 					NR 1 ENGINE	BROKE 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	2FOR				89438	MJ003				DURING REMOVAL OF ENGINE SCREEN AND NOSE BOX COWL, NOTICED NR 1 ENGINE TRANSMISSION TEMP SWITCH WAS HANGING BY THE CANNO	N PLUG WHERE IT HAD BROKEN IN HALF AT THE WELDED SEAM. NO SIGN OF LEAKAGE. CAUSE UNKNOWN. (X)					2	G	7	2 	4U	4	U		H9EA 	E4NE				 
1995101300480	19951013	00480	NE 	1995	10	13	CHI1478 	2	19950808	G	7210	M2001517	SWITCH 			BOEING	234 	234 	1385049	EA 	LYC 	AL5512	AL5512 	41581	NE 					NR 1 ENGINE	BROKEN 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	239CH				33043	MJ006				PILOTS REPORTED INTERMITTENT NR 1 ENGINE TRANSMISSION HOT LIGHT. DURING TROUBLESHOOTING, FOUND M2001-517 TEMP SWITCH BR	OKE IN HALF AND WIRES PULLED OUT AT CANNON PLUG. REPLACED TEMP SWITCH AND CANNON PLUG. CHECKED GOOD. CAUSE UNKNOWN. S	UBMITTER SUGGESTS POSSIBLE VIBRATION OR STRUCK DURING MAINTENANCE. (X)				2	G	7	2 	4U	4	U		H9EA 	E4NE				 
1996040500070	19960405	00070		1996	4	5	CHI1488 	4	19950827	G	2211	234VS1007	COMPUTER 	HONEYWELL 		BOEING	234 	234 	1385049	EA 										NR 1 AFCS	FAILED 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	239CH				N0043	MJ006				AT MORNING START-UP DURING THE AFCS CHECK, WHEN THE AFCS WAS TURNED ON, THE ROLL EXTENSIBLE LINK STARTED MOVING ERRATICA	LLY. THE PROBLEM WAS ISOLATED TO THE NR 1 AFCS, AT THIS TIME, THE ROLL LINK STARTED MOVING MORE ERRATICALLY UP AND DOWN	. UPON FURTHER TROUBLESHOOTING, FOUND THE PROBLEM WAS IN THE 'AIR SENSING' SIDE OF THE NR 1 AFCS COMPUTER. THE COMPUTE	R WAS REPLACED AND OPS CHECKED GOOD.			2	G	7	2 	4U				H9EA 					 
1996032200167	19960322	00167	NE 	1996	3	22	CHI1512 	2	19951026	G	7250		ENGINE 			BOEING	234 	234 	1385049	EA 	LYC 	AL5512	AL5512 	41581	NE 					TURBINE	DAMAGED 	B	L		CHIR	E				ENGINE SHUTDOWN 				O			OTHER 			EX	EXTERNAL LOAD 	1			NM	09	234CH					MJ001	LE60002			INFLIGHT ENGINE SHUT-DOWN DURING LOGGING OPERATION. NO VISIBLE DAMAGE TO INLET OF ENG OR FIRST STAGES OF COMPRESSOR. C	OMPR WOULD ROTATE, BUT WITH DIFFICULTY, & RUBBING NOISES. VISIBLE DMG TO EGV & NR 4 TURBINE WHEEL. PT WOULD NOT TURN. 	 NO VISIBLE DMG TO COMPR CASES, COMB CAN OR NR 4 NOZZLE. UPON REMOVAL OF PT, DAMAGE NOTED TO NR 2 TURB WHEEL, NR 2 & NR	 3 NOZZLES & NR 3 TURB WHEEL BLADES. REMOVED NR 2 AND NR 1 TURB WHEELS. NO DAMAGE FND FWD OF NR 1 NOZZLE. NO DMG TO C	URL OR AIR DIFFUSER. FND DAMAGE TO L/E OF BLADES. NR 4 NOZZLES VANES HEAVILY DMG'D & METALIZED IN NR 4 & NR 3 TURB WHE	EL TIP PATH AREAS. DMG TO NR 3 TURB WHEEL L/E OF BLADES. CHIP DETECTOR & BASKETS, & OIL FILTER FND FREE OF METAL. (X)	2	G	7	2 	4U	4	U		H9EA 	E4NE				 
1996040500071	19960405	00071	EA 	1996	4	5	CHI1513 	1	19951107	G	6320	114D208011	CARRIER 		234D22004 	BOEING	234 	234 	1385049	EA 										2ND STAGE	CRACKED 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	234CH	6118 			M5047	MJ001				THE AFT TRANSMISSION WAS REMOVED FOR MAKING CHIPS. THE UPPER HOUSING WAS DISASSEMBLED TO INSPECT THE CARRIER BEARINGS F	OR SOURCE OF CHIPS. A SPALLED BEARING WAS FOUND. A VISUAL INSPECTION OF THE SECOND STAGE CARRIER DISCOVERED A CRACK. (	X)				2	G	7	2 	4U				H9EA 					 
1996040500072	19960405	00072	EA 	1996	4	5	CHI1514 	1	19951215	G	6230	173RS3081	BEARING 		414R350510 	BOEING	234 	234 	1385049	EA 										SWASHPLATE	FAILED 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	239CH	25 			AE843	MJ006				POST-FLIGHT CHECK REVEALED BLACK GREASE RUBBER AND WIRE FRAGMENTS COMING OUT OF THE GAP BETWEEN THE STATIONARY RING AND 	THE ROTATING RING. UNIT WAS REMOVED AND REPLACED. DISASSEMBLY OF SWASHPLATE SHOWED THE WIRE CAGE SEPARATOR HAD BROKEN 	UP. PAST FAILURES HAVE BEEN ATTRIBUTED TO FORMING CRACKS DURING MANUFACTURE OF THE CAGE. (X)				2	G	7	2 	4U				H9EA 					 
1995042800731	19950428	00731	EA 	1995	4	28	CHIR1425 	1	19950215	G	6320	414D62102	CLUTCH SHAFT 		234D62006 	BOEING	234 	234 	1385049	EA 										SPIRAL BEVEL	BEARING DAMAGED 	B			CHIR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	237CH	1294 			M5627	MJ003				ON AND OFF THRUST LOADING OF THE INNER CLUTCH SHAFT CAUSES AXIAL MOVEMENT OF THE SHAFT. AS THE ALUMINUM SPACERS (PN 414	D6215-1 AND PN 114D6261-1) WEAR, THE AXIAL MOVEMENT INCREASES UNTIL THE INNER SHAFT SHOULDER NEXT TO THE PN 114DS661-1 B	EARING CONTACTS THE ROLLERS OF THE 114DS661-1 BEARING. THIS ON AND OFF CONTACT CREATED A SEVERE SCALLOPING OF THAT SHOU	LDER ON THE INNER SHAFT. POSSIBLE SOLUTION WOULD BE TO FABRICATE THE ALUMINUM SPACERS OUT OF A MORE WEAR RESISTANT STEE	L TO RESTRICT MOVEMENT. (X)		2	G	7	2 	4U				H9EA 					 
1995120800591	19951208	00591	CE 	1995	12	8	CWQR061D 	1	19951205	G	2750	NAS624H113	BOLT 			CESSNA	500 	S550 	2076607	CE 										FLAP BELLCRANK	SEIZED 	B			CWQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			GL	05	288QS	7803 				S5500088				RUST ON SUPPORT ASSY FROM FLAP BELLCRNK ASSY. UPON REMOVAL FOUND BOLT (PIVOT) SEIZED TO BEARINGS, SPACER. BEARINGS ARE	 FACTORY LUBED AND NOT FIELD LUBED. ALSO, BOLT IS INSTALLED DRY (NO LUBE). ALSO, NO INSPECTION CALLED OUT TO CHECK ON 	LUBE OF THESE COMPONENTS. (X)				1	L	7	2 	4F			RT	A22CE 					 
1995080400124	19950804	00124	EU 	1995	8	4	EGRA95100 	1	19950612	G	2844	81071370010	TRANSMITTER 			AEROSP	SA365 	AS365N2 	8680815	EU 										FUEL PRESS	FAILED 	E			EGRA	O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			EA	17	272NE	259 				6435				INOPERATIVE, NO FUEL PRESSURE # 2 ENGINE REPLACED FUEL PRESSURE TRANSMITTER						1	G	7	2 	3U			RT	H10EU 					 
1995080400125	19950804	00125	NE 	1995	8	4	EGRA95101 	2	19950612	G	7412	9580113800	GENERATOR 		ARRIEL1C2 	AEROSP	SA365 	AS365N2 	8680815	EU 	TMECA 	ARRIEL	ARRIEL1C 	60030	NE 					ENGINE	INOP 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	272NE	281 			12105	6435				HE GENERATOR INOPERATIVE . REPLACED						1	G	7	2 	3U	3	U	RT	H10EU 	E19EU				 
1995080400126	19950804	00126	EU 	1995	8	4	EGRA95102 	1	19950613	G	6410	365A12002000	BLADE 			AEROSP	SA365 	AS365N2 	8680815	EU 										T/R	CRACKED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	272NE	281 				6435				FOUND SIX FENESTRON BLADES TO HAVE SURFACE CRACKS IN THE SURFACE PENETRATING INTO THE FIBER AFTER SANDING PAINT AND PRIM	ER. REF: MWC 64.21.00.602 CHAP 2-3. S/N'S OFF 19249/19251/19253/19254/19360/19395. INSTALLED THE FOLLOWING S/N'S 25131/2	5129/25136/25130/25143/25140.				1	G	7	2 	3U			RT	H10EU 					 
1995080400127	19950804	00127	EU 	1995	8	4	EGRA95103 	1	19950613	G	3213	117501031	TUBE 			BOLKMS	117 	BK117B1 	5626012	EU 										SKID TUBE	DENTED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2595 				7178				SKID TUBE ASSY DENTED BEYOND LIMITS REPLACED SKID TUBE ASSY						1	G	7	2 	3U				H13EU 					 
1995080400128	19950804	00128	EU 	1995	8	4	EGRA95104 	1	19950613	G	5210	1172118102	WINDOW ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 										CABIN	CRACKED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2779 				7095				WINDOW CRACKED. REPLACED WINDOW						1	G	7	2 	3U				H13EU 					 
1995080400129	19950804	00129	EU 	1995	8	4	EGRA95105 	1	19950613	G	2823	1140A141	VALVE 			AEROSP	SA365 	AS365N2 	8680815	EU 										FUEL CUTOFF	LEAKS 	E			EGRA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	17	272NE	313 				6435				FUEL CUTOFF VALVE LEAKS . REPLACED CUTOFF VALVE.						1	G	7	2 	3U			RT	H10EU 					 
1995080400130	19950804	00130	EU 	1995	8	4	EGRA95106 	1	19950613	G	2400	870UN01S4BE7AC	TOGGLE SWITCH 			AEROSP	SA365 	AS365N2 	8680815	EU 										COCKPIT	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	272NE	343 				6435				SWITCH DIFFICULT TO SWITCH ON AND OFF REPLACED SWITCH.						1	G	7	2 	3U			RT	H10EU 					 
1995080400131	19950804	00131	EU 	1995	8	4	EGRA95107 	1	19950613	G	2510	365A62811503	COVER 			AEROSP	SA365 	AS365N2 	8680815	EU 										FLT COMPT	CRACKED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	272NE	335 				6435				COVER CRACKED REPLACED COVER						1	G	7	2 	3U			RT	H10EU 					 
1995080400132	19950804	00132	EU 	1995	8	4	EGRA95108 	1	19950614	G	2435	23032027	STARTER 			BOLKMS	117 	BK117A3 	5626015	EU 										START/GEN	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB					7095				UNIT REMOVED IN THE FIELD DUE TO PROBELM STARTS, BRUSHES FOUND WORN BEYOND LIMITS, REMOVED FOR OVERHAUL. REPLACED UNIT						1	G	7	2 	3U				H13EU 					 
1995080400133	19950804	00133	EU 	1995	8	4	EGRA95109 	1	19950614	G	5230	1172433901	LATCH ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 										DOOR	BROKEN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	3007 				7095				LATCH SPRING BROKEN REPLACED LATCH ASSY						1	G	7	2 	3U				H13EU 					 
1995080400134	19950804	00134	EU 	1995	8	4	EGRA9511 	1	19950321	G	7714	1179405603	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										ENG N1	ERRATIC 	E			EGRA	O				OTHER 				O			OTHER 			CR	CRUISE 	1			EA	17	116MB	2864 				7095				#1 ENGINE N1 GAUGE ERRATIC AND UNRELIABLE. REPLACED N1 GAUGE WITH A USED SERVICEABLE ONE.						1	G	7	2 	3U				H13EU 					 
1995080400135	19950804	00135	NE 	1995	8	4	EGRA95110 	1	19950614	G	6240	7690001881103	AMPLIFIER 			SKRSKY	S76 	S76A 	8143006	NE 										VIB ABSORB	INOP 	E			EGRA	O				OTHER 				O			OTHER 			HO	HOVERING 	1			EA	17	903SK	3 				760218				UNIT INOPERATIVE REPLACED UNIT						1	G	7	2 	3U				H1NE 					 
1995080400136	19950804	00136	SW 	1995	8	4	EGRA95111 	1	19950615	G	2910	212076015001	VALVE 			BELL 	412 	412 	1182202	SW 										HYD CHECK	LEAKING 	E			EGRA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	17	412PP	224 				33207				VALVE FOUND TO BE LEAKING REPLACED VALVE						1	G	7	2 	4U				H4SW 					 
1995080400137	19950804	00137	EU 	1995	8	4	EGRA95112 	1	19950615	G	2422	M3901613072L	RELAY 			AEROSP	SA365 	AS365N2 	8680815	EU 										INVERTER	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	272NE	259 				6435				MED INVERTER RELAY INOPERATIVE REPLACED RELAY.						1	G	7	2 	3U			RT	H10EU 					 
1995080400138	19950804	00138	NE 	1995	8	4	EGRA95113 	1	19950626	G	2420	7655009005108	CONTROL 			SKRSKY	S76 	S76B 	8143007	NE 										AC GENERATOR	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	176AS	7 				760327				AC GENERATOR INTERMITTENT, DROPS OFF LINE. REPLACED AC GENERATOR CONTROL UNIT.						1	G	7	2 	4U				H1NE 					 
1995080400139	19950804	00139	EU 	1995	8	4	EGRA95114 	1	19950626	G	7931	IPT70RT11000250G	TRANSDUCER 			BOLKMS	117 	BK117B1 	5626012	EU 										ENG OIL PRESS	FLUCTUATES 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2596 				7178				#2 ENGINE OIL PRESSURE FLUCTUATES REPLACED TRANSDUCER.						1	G	7	2 	3U				H13EU 					 
1995080400140	19950804	00140	EU 	1995	8	4	EGRA95115 	1	19950627	G	7714	1179405603	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										ENG N1	ERRATIC 	E			EGRA	O				OTHER 				O			OTHER 			TX	TAXI/GRND HDL 	1			EA	17	116MB	2909 				7095				N1 INDICATOR HAS ERRACTIC READINGS, REPLACE SIGHT GLASS.						1	G	7	2 	3U				H13EU 					 
1995080400141	19950804	00141	EU 	1995	8	4	EGRA9512 	1	19950321	G	6720	741C000005	ACTUATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	LEAKING 	E			EGRA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	17	116MB	39 				7095				TAIL ROTOR ACTUATOR LEAKING. REPLACED WITH USED SERVICEABLE ACTUATOR.						1	G	7	2 	3U				H13EU 					 
1995080400142	19950804	00142	EU 	1995	8	4	EGRA9513 	1	19950321	G	6730	D107614	SERVO MOTOR 			BOLKMS	117 	BK117B1 	5626012	EU 										CYCLIC TRIM	INOPERATIVE 	E			EGRA	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			O			OTHER 			TO	TAKEOFF 	1			EA	17	7062J	2499 				7178				LATERAL CYCLIC TRIM ACTUATOR INOPERATIVE REMOVED AND REPLACED TRIM ACTUATOR.						1	G	7	2 	3U				H13EU 					 
1995080400143	19950804	00143	EU 	1995	8	4	EGRA9514 	1	19950321	G	7931	1179405807	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										ENG OIL	FLUCTUATES 	E			EGRA	O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			EA	17	116MB	2833 				7095				#1 ENGINE OIL PRESSURE FLUCTUATES. REMOVED AND REPLACED #1 ENGINE OIL PRESSURE GAUGE.						1	G	7	2 	3U				H13EU 					 
1995080400144	19950804	00144	EU 	1995	8	4	EGRA9516 	1	19950322	G	7712	30571496	TORQUEMETER 			AEROSP	SA365 	AS365N2 	8680815	EU 										COCKPIT	DEFECTIVE 	E			EGRA	O				OTHER 				O			OTHER 			HO	HOVERING 	1			EA	17	272NE	210 				6435				TORQUE INDICATOR HAS INTERMITTENT FLAG PROBELM. REPLACED TORQUE INDICATOR.						1	G	7	2 	3U			RT	H10EU 					 
1995080400145	19950804	00145	EU 	1995	8	4	EGRA9517 	1	19950322	G	2432	B1090000	BATTERY 			AEROSP	SA365 	AS365N2 	8680815	EU 										EMERG LIGHTS	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	272NE	210 				6435				EMERGENCY LIGHTS INOPERATIVE. TROUBLESHOOT AND FOUND EMERGENCY LIGHTS POWER SUPPLY BATTERY DEAD AND OUT OF DATE. REPLA	CED EMERGENCY LIGHTS POWER SUPPLY.					1	G	7	2 	3U			RT	H10EU 					 
1995080400146	19950804	00146		1995	8	4	EGRA9519 	4	19950330	G	2340	U2025	SWITCH 		A21896561601	BOLKMS	117 	BK117B1 	5626012	EU 										INTERPHONE	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2499 			8716044	7178				ICS SWITCH WORN OUT, INTERMITTENT. REPLACED ICS TRIGGER SWITCH.						1	G	7	2 	3U				H13EU 					 
1995080400147	19950804	00147	EU 	1995	8	4	EGRA952 	1	19950219	G	6720	11788659	BELLCRANK ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	319 				7178				BEARINGS IN BELLCRANK WORN BEYOND LIMITS REPLACED BELLCRANK .						1	G	7	2 	3U				H13EU 					 
1995080400148	19950804	00148	EU 	1995	8	4	EGRA9521 	1	19950403	G	2422	2A10001G	INVERTER 			AEROSP	SA365 	AS365N2 	8680815	EU 										AC SYS	INOPERATIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	272NE	257 				6435				INVERTER INOPERATIVE. REPLACED INVERTER.						1	G	7	2 	3U			RT	H10EU 					 
1995080400149	19950804	00149	EU 	1995	8	4	EGRA9523 	1	19950405	G	2822	1176415103	BOOSTER PUMP 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL SYS	INOPERATIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	544 				7095				FUEL BOOST PUMP INOPERATIVE. REPLACED FUEL BOOST PUMP.						1	G	7	2 	3U				H13EU 					 
1995080400150	19950804	00150	GL 	1995	8	4	EGRA9524 	2	19950410	G	7321	25490922	FUEL CONTROL 		250C30P 	BELL 	206 	206L 	1181522	SW 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	MALFUNCTION 	E			EGRA	O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			EA	17	209PD	277 			895752	52075				FUEL CONTROL REQUIRES INTERNAL ADJUSTMENT TO START DERICH AND ACCEL. FUEL CONTROL SENT TO AIRWORK FOR REPAIR. UNIT REPAI	RED BY AIRWORK UNDER WORK ORDER # V04689. UNIT RETURNED TO KEYSTONE AND PERFORMED OPERATIONAL CHECKS. OP CHECKED GOOD.					1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995080400151	19950804	00151	EU 	1995	8	4	EGRA9525 	1	19950413	G	5246	1176701107	HINGE HALF 			BOLKMS	117 	BK117A3 	5626015	EU 										OIL COOL DOOR	BROKEN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	923 				7095				OIL COOLER INSPECTION DOOR UPPER HINGE HALF BROKEN. REPLACED WITH NEW HINGE FROM KHC STOCK.						1	G	7	2 	3U				H13EU 					 
1995080400152	19950804	00152	EU 	1995	8	4	EGRA9526 	1	19950413	G	5210	1172428401	STOPPER 			BOLKMS	117 	BK117B1 	5626012	EU 										LT DOOR	BROKEN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	469 				7178				DOOR STOPPER BROKEN OFF. REPLACED WITH NEW ONE FROM KHC STOCK.						1	G	7	2 	3U				H13EU 					 
1995080400153	19950804	00153	EU 	1995	8	4	EGRA9527 	1	19950413	G	6210	11715856	ELASTIC BUSHING 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R	DETERIORATION 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	118MB	1480 				7096				ELASTIC BUSHING REMOVED BECAUSE OF RUBBER PROTRUSION. REPLACED WITH NEW ELASTIC BUSHINGS.						1	G	7	2 	3U				H13EU 					 
1995080400154	19950804	00154	EU 	1995	8	4	EGRA9528 	1	19950413	G	5210	1172428111	CATCHER 			BOLKMS	117 	BK117B1 	5626012	EU 										LT DOOR	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	431 				7178				CATCHER L/H FOUND WORN. REPLACED CATCHER L/H WITH ONE FROM KHC STOCK.						1	G	7	2 	3U				H13EU 					 
1995080400155	19950804	00155	EU 	1995	8	4	EGRA9529 	1	19950413	G	6420	1053170018	FITTED BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	CORRODED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	911CH	105 				7223				FITTED BOLT FOUND CORRODED. REPLACED WITH NEW BOLT FROM KHC STOCK.						1	G	7	2 	3U				H13EU 					 
1995080400156	19950804	00156	SW 	1995	8	4	EGRA953 	1	19950309	G	2841	206063633103	INDICATOR 			BELL 	206 	206L 	1181522	SW 										FUEL QTY	STICKS 	E			EGRA	O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			EA	17	3NJ	13 				52107				FUEL QTY INDICATOR NEEDLE STICKS WHILE IN OPERATION. REPLACED FUEL QTY INDICATOR.						1	G	7	1 	3U				H2SW 					 
1995080400157	19950804	00157	EU 	1995	8	4	EGRA9530 	1	19950413	G	5210	1172428401	STOPPER 			BOLKMS	117 	BK117A3 	5626015	EU 										LT DOOR	BROKEN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	9024Z	1587 				7134				LEFT HAND DOOR STOPPER FOUND BROKEN REPLACED LEFT HAND DOOR STOPPER WITH ONE FROM KHC STOCK						1	G	7	2 	3U				H13EU 					 
1995080400158	19950804	00158	EU 	1995	8	4	EGRA9531 	1	19950413	G	7120	365A51103800	SUPPORT MOUNT 			AEROSP	SA365 	AS365N2 	8680815	EU 										LT ENG MOUNT	DEFORMED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	365WM	23 				6429				RIGHT AND LEFT HAND ENGINE MOUNT CRADLES DEFORMED. REPLACED DEFORMED CRADLES						1	G	7	2 	3U			RT	H10EU 					 
1995080400159	19950804	00159	EU 	1995	8	4	EGRA9533 	1	19950420	G	6230		SEAL 			AEROSP	SA365 	AS365N2 	8680815	EU 										M/R MAST	LEAKING 	E			EGRA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	17	272NE					6435				MAIN ROTOR MAST SEAL LEAKING. REMOVED MAIN ROTOR DYNAMIC COMPONENTS AND CHANGED MAIN ROTOR MAST SEAL, REINSTALLED MAIN R	OTOR DYNAMIC COMPONENTS. CHECKED MAST SEAL FOR LEAKS, CHECKED GOOD.					1	G	7	2 	3U			RT	H10EU 					 
1995080400160	19950804	00160		1995	8	4	EGRA9534 	4	19950420	G	2210		AUTO PILOT 			AEROSP	SA365 	AS365N2 	8680815	EU 										AUTO FLIGHT	MALFUNCTION 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	272NE					6435				AUTO PILOT NOT WORKING PROPERLY ASSISTED AEC TECH REPS IN TROUBLESHOOTING AND REPAIRING AUTOPILOT SYSTEM. INSPECTED AND 	CLOSED BAGGAGE COMPARTMENT AS REQUIRED.					1	G	7	2 	3U			RT	H10EU 					 
1995080400161	19950804	00161	NE 	1995	8	4	EGRA9535 	1	19950420	G	5510		STABILIZER 			SKRSKY	S76 	S76B 	8143007	NE 										H STAB	DEBONDED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	22CP					760427				HORIZONTAL STABILIZER FOUND DEBONDED. STABILIZER SHIPPED TO KEYSTONE FOR REPAIR. REPAIRED DISBONDED STABILIZER IAW CMM S	A4047-76-5 REPAIR PROCEDURE #2 FOR BOND SEPERATIONS AND REPAIR PROCEDURE #3 FOR SKIN PATCH REPAIR. REPAIRED STABILIZER R	ETURNED AFTER REPAIR.				1	G	7	2 	4U				H1NE 					 
1995080400162	19950804	00162	EU 	1995	8	4	EGRA9536 	1	19950424	G	2431	10591596	TEMP WARN 			BOLKMS	117 	BK117A3 	5626015	EU 										BATT WARN	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2779 				7095				TEMP. WARNING UNIT FAILED OPERATIONAL CHECK. REPLACED TEMP. WARNING UNIT.						1	G	7	2 	3U				H13EU 					 
1995080400163	19950804	00163	EU 	1995	8	4	EGRA9537 	1	19950424	G	5210	T6610101	HANDLE MECHANISM			BOLKMS	117 	BK117A3 	5626015	EU 										CABIN	JAMMED DOOR 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2284 				7095				HANDLE MECHANISM CAME APART AND JAMMED DOOR. REPLACED LINK FROM HANDLE MECHANISM. LINK REMOVED FROM HANDLE MECHANISM IN 	KHC STOCK.					1	G	7	2 	3U				H13EU 					 
1995080400164	19950804	00164	EU 	1995	8	4	EGRA954 	1	19950305	G	6210	10514101111	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	SCORED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2499 				7178				SECONDARY BLADE BOLT HAS SCORE MARKS ON BOLT SURFACE BEYOND LIMITS. REPLACED BOLT.						1	G	7	2 	3U				H13EU 					 
1995080400165	19950804	00165	EU 	1995	8	4	EGRA9540 	1	19950426	G	6420	10531737103	BEARING SLEEVE 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2356 				7178				BEARING SLEEVES WORN BEYOND LIMITS. REPLACED BEARING SLEEVES.						1	G	7	2 	3U				H13EU 					 
1995080400166	19950804	00166	EU 	1995	8	4	EGRA9541 	1	19950426	G	6520	0750111095	SHAFT SEAL 			BOLKMS	117 	BK117A3 	5626015	EU 										INT GR BOX	LEAKING 	E			EGRA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	17	116MB	2163 				7095				OIL SEEPING FROM VERTICAL FIN. REMOVED IGB FROM AIRCRAFT, REPLACED INPUT SEAL.						1	G	7	2 	3U				H13EU 					 
1995080400167	19950804	00167	EU 	1995	8	4	EGRA9543 	1	19950426	G	6220	11211410225	WASHER 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R SEAL	DAMAGED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2356 				7178				MAIN ROTOR INNER SEAL WASHERS DAMAGED BEYOND LIMITS. REPLACED WASHERS.						1	G	7	2 	3U				H13EU 					 
1995080400168	19950804	00168	EU 	1995	8	4	EGRA9544 	1	19950426	G	6220	1051418103	FLANGE BUSHING 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R GRIP	DAMAGED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2356 				7178				YELLOW AND BLUE MAIN ROTOR GRIP SECONDARY FLANGE BUSHINGS DAMAGED BEYOND LIMITS REPLACED FLANGE BUSHINGS WITH NEW ONES F	ROM KHC STOCK.					1	G	7	2 	3U				H13EU 					 
1995080400169	19950804	00169	EU 	1995	8	4	EGRA9545 	1	19950426	G	5210	T6678103	PUSH PULL ROD 			BOLKMS	117 	BK117A3 	5626015	EU 										DOOR HANDLE	FAILED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2198 				7095				LOWER PUSH PULL ROD ASSY BENT AND ROD END BROKE INSIDE TUBE ASSY REPLACED DOOR HANDLE MECHANISM ASSY						1	G	7	2 	3U				H13EU 					 
1995080400170	19950804	00170	EU 	1995	8	4	EGRA9546 	1	19950426	G	6220	1051011305	BELLOWS 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R	TORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	805 				7095				MAIN ROTOR BELLOWS FOUND TORN DURING INSPECTION REPLACED MAIN ROTOR BELLOWS WITH NEW ONE						1	G	7	2 	3U				H13EU 					 
1995080400171	19950804	00171	EU 	1995	8	4	EGRA9548 	1	19950426	G	5345	105800314	RELEASE PIN 			BOLKMS	105 	BO105LSA3 	5626020	EU 										WIRE STRIKE	FAILED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	39VA	39 				2041				WIRE STRIKE KIT RELEASE PIN FAILED. BEARINGS AT END OF RELEASE PIN FELL OUT. PART SCRAPPED AT KHC. REPLACED WITH NEW REL	EASE PIN.					1	G	7	2 	3U				H3AU 					 
1995080400172	19950804	00172	EU 	1995	8	4	EGRA9549 	1	19950426	G	5244	1173084103	HINGE 			BOLKMS	117 	BK117B1 	5626012	EU 										TAIL FAIRING	BROKEN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2210 				7178				TAIL FAIRING ACCESS PANEL HINGE BROKEN REPLACED HINGE WITH NEW ONE. PART SCRAPPED AT KEYSTONE						1	G	7	2 	3U				H13EU 					 
1995080400173	19950804	00173	EU 	1995	8	4	EGRA9550 	1	19950427	G	6220	1051011305	BELLOWS 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	TORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	805 				7178				MAIN ROTOR BELLOWS FOUND TORN DURING INSPECTION. REPLACED BELLOWS.						1	G	7	2 	3U				H13EU 					 
1995080400174	19950804	00174	EU 	1995	8	4	EGRA9551 	1	19950427	G	6210	11715856	ELASTIC BUSHING 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R BLADE	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2779 				7095				MAIN ROTOR BLADE SECONDARY BUSHINGS WORN BEYOND LIMITS REPLACED MAIN ROTOR BLADE SECONDARY BUSHINGS WITH NEW ONES FROM K	HC STOCK					1	G	7	2 	3U				H13EU 					 
1995080400175	19950804	00175	EU 	1995	8	4	EGRA9552 	1	19950427	G	6210	117150031	TRIM TAB ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R BLADE	CRACKED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2779 				7095				YELLOW MAIN ROTOR BLADE OUTBOARD TRIM TAB CRACKED REPLACED TRIM TAB						1	G	7	2 	3U				H13EU 					 
1995080400176	19950804	00176	EU 	1995	8	4	EGRA9553 	1	19950427	G	6210	1051418303	FLANGE BUSHING 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R GRIP	SCORED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2779 				7095				BLUE AND YELLOW MAIN ROTOR BLADE GRIP SECONDARY BUSHINGS SCORED AND PITTED REPLACED BUSHINGS						1	G	7	2 	3U				H13EU 					 
1995080400177	19950804	00177	EU 	1995	8	4	EGRA9554 	1	19950427	G	6210	134615P	BUSHING 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R BLADE	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2779 				7095				MAIN ROTOR BLADE PRIMARY BUSHINGS FOUND WORN BEYOND LIMITS REPLACED BUSHINGS						1	G	7	2 	3U				H13EU 					 
1995080400178	19950804	00178	EU 	1995	8	4	EGRA9556 	1	19950427	G	6420	1053170023	BEARING 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	9024Z	1726 				7134				TAIL ROTOR BLADE BEARINGS WORN BEYOND LIMITS REPLACED WITH NEW BEARINGS						1	G	7	2 	3U				H13EU 					 
1995080400179	19950804	00179	NE 	1995	8	4	EGRA9557 	2	19950427	G	7421	CH34016	IGNITER PLUG 			BOLKMS	117 	BK117A3 	5626015	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENGINE	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2163 				7095				ENGINE IGNITER PLUG INOPERATIVE.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995080400180	19950804	00180	EU 	1995	8	4	EGRA9558 	1	19950427	G	7170	360A54112171	HOSE 			AEROSP	SA365 	AS365N2 	8680815	EU 										FUEL DRAIN	LEAKS 	E			EGRA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	17	291LL	991 				6402				#1 ENGINE OVERBOARD FUEL DRAIN LEAKS ON LEFT HAND MAIN LANDING GEAR REMOVED DEFECTIVE DRAIN LINE AND INSTALLED NEW DRAIN	 LINE AND SECURED IAW 365N2 MWC					1	G	7	2 	3U			RT	H10EU 					 
1995080400181	19950804	00181	EU 	1995	8	4	EGRA9559 	1	19950427	G	2910	11745020	MODULE 			BOLKMS	117 	BK117B1 	5626012	EU 										HYD	MALFUNCTION 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	911CH	1156 				7223				AUTO PILOT PROBELMS RELATED TO THE HYDRAULIC MODULE. REMOVED AND REPLACED HYDRAULIC MODULE						1	G	7	2 	3U				H13EU 					 
1995080400182	19950804	00182	EU 	1995	8	4	EGRA956 	1	19950305	G	6230	1051011305	BELLOWS 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	TORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	524 				7178				MAIN ROTOR SWASHPLATE BOOT TORN. REPLACED MAIN ROTOR SWASHPLATE BOOT.						1	G	7	2 	3U				H13EU 					 
1995080400183	19950804	00183	EU 	1995	8	4	EGRA9560 	1	19950427	G	6220	350A31182702	FREQ ADAPTERS 			AEROSP	SA365 	AS365N2 	8680815	EU 										M/R	SPLIT 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	291LL	189 				6402				FREQUENCY ADAPTERS SPLIT BEYOND LIMITS REPLACED FREQUENCY ADAPTERS						1	G	7	2 	3U			RT	H10EU 					 
1995080400184	19950804	00184	EU 	1995	8	4	EGRA9561 	1	19950427	G	5244	1173084103	HINGE 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R FAIRING	BROKEN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2210 				7178				TAIL FAIRING ACCESS PANEL HINGE BROKEN REPLACED HINGE WITH NEW ONE. PART SCRAPPED AT KHC						1	G	7	2 	3U				H13EU 					 
1995080400185	19950804	00185	EU 	1995	8	4	EGRA9563 	1	19950427	G	6220	10513141	ROD END ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2356 				7178				ROD END BEARINGS FOUND WORN REPLACED ROD END ASSYS						1	G	7	2 	3U				H13EU 					 
1995080400186	19950804	00186	EU 	1995	8	4	EGRA9564 	1	19950427	G	3340	1179203103	CONTROL UNIT 			BOLKMS	117 	BK117B1 	5626012	EU 										LIGHTS	INOPERATIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	81 				7178				LIGHT CONTROL INOPERATIVE, LIGHTS WILL NOT DIM WHEN ON OR OFF						1	G	7	2 	3U				H13EU 					 
1995080400187	19950804	00187	EU 	1995	8	4	EGRA9566 	1	19950428	G	6210	143764P	GUARD WASHER 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2779 				7095				MAIN ROTOR BLADE GUARD WASHERS WORN BEYOND LIMITS REPLACED MAIN ROTOR BLADE GUARD WASHERS						1	G	7	2 	3U				H13EU 					 
1995080400188	19950804	00188	EU 	1995	8	4	EGRA9568 	1	19950428	G	7330	1176122811	TUBE ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 										ENGINE	DAMAGED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	116MB	2779 				7095				FUEL AND TORQUE INDICATION TUBE ASSY HAS DAMAGED THREADS REPLACED TUBE ASSY.						1	G	7	2 	3U				H13EU 					 
1995080400189	19950804	00189	NE 	1995	8	4	EGRA9569 	2	19950428	G	7261	0292105230	OIL PUMP 			SKRSKY	S76 	S76 	8143010	NE 	TMECA 	ARRIEL	ARRIEL1S 	60030	NE 					ENG	MALFUNCTION 	E			EGRA	C				ABORTED TAKEOFF 				O			OTHER 			TX	TAXI/GRND HDL 	1			EA	17	154AE	107 				760407	3097			FLUCTUATING OIL PSI @ 35-45 PSI REPLACED OIL PUMP						1	G	7	2 	3U	3	U		H1NE 	E19EU				 
1995080400190	19950804	00190	NE 	1995	8	4	EGRA9570 	1	19950502	G	6230	7610408013043	RETAINER ASSY 			SKRSKY	S76 	S76 	8143010	NE 										M/R	GROOVED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				GROOVE WORN ON RETAINER. CAUSE IMPROPER DIMENSION ON SHIM PINCH REPLACED RETAINER ASSY.						1	G	7	2 	3U				H1NE 					 
1995080400191	19950804	00191	NE 	1995	8	4	EGRA9571 	1	19950502	G	6230	SB5007101	UNIBALL ASSY 			SKRSKY	S76 	S76 	8143010	NE 										M/R MAST	BLISTERED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				CORROSION BLISTER ON SURFACE OF BALL. REPLACED UNIBALL ASSY.						1	G	7	2 	3U				H1NE 					 
1995080400192	19950804	00192	NE 	1995	8	4	EGRA9572 	1	19950502	G	3242	5007555	BRAKE ASSY 			SKRSKY	S76 	S76 	8143010	NE 										MLG	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				BRAKE ASSY WORN BEYOND LIMITS REPLACED BRAKE ASSY						1	G	7	2 	3U				H1NE 					 
1995080400193	19950804	00193	NE 	1995	8	4	EGRA9573 	1	19950502	G	6230	SB52001	BEARING 			SKRSKY	S76 	S76 	8143010	NE 										SCISSORS	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				ROTATING SCISSOR BEARINGS WORN OUT OF LIMITS (.110) REPLACED BEARINGS						1	G	7	2 	3U				H1NE 					 
1995080400194	19950804	00194	NE 	1995	8	4	EGRA9574 	1	19950502	G	6410	SB7303102	SNUBBER 			SKRSKY	S76 	S76 	8143010	NE 										T/R	TORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				TAIL ROTOR BLADE SNUBBER FOUND TORN. REPLACED NEW SNUBBERS.						1	G	7	2 	3U				H1NE 					 
1995080400195	19950804	00195	NE 	1995	8	4	EGRA9575 	1	19950502	G	6700	0401275250	ROD 			SKRSKY	S76 	S76 	8143010	NE 										RT N2	BENT 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				RH N2 ROD BENT AND MISSING LOCKING HOLES REPLACED RH N2 ROD IAW CBT-TC-95-0398						1	G	7	2 	3U				H1NE 					 
1995080400196	19950804	00196	NE 	1995	8	4	EGRA9576 	1	19950502	G	6220	NAS464P842	BOLT 			SKRSKY	S76 	S76 	8143010	NE 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				BOLTS FOUND WORN REPLACED BOLTS						1	G	7	2 	3U				H1NE 					 
1995080400197	19950804	00197	NE 	1995	8	4	EGRA9577 	1	19950502	G	6220	SB5080102	BEARING 			SKRSKY	S76 	S76 	8143010	NE 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				PITCH LINK BEARINGS FOUND WORN REPLACED BEARINGS						1	G	7	2 	3U				H1NE 					 
1995080400198	19950804	00198	NE 	1995	8	4	EGRA9578 	1	19950503	G	6220	NAS6608D47	BOLT 			SKRSKY	S76 	S76 	8143010	NE 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				BOLTS FOUND WORN BEYOND LIMITS REPLACED BOLTS.						1	G	7	2 	3U				H1NE 					 
1995080400199	19950804	00199	NE 	1995	8	4	EGRA9579 	1	19950503	G	6220	MS20002C8	WASHER 			SKRSKY	S76 	S76 	8143010	NE 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				PITCH LINK ROD BOLT WASHERS FOUND WORN REPLACED WASHERS						1	G	7	2 	3U				H1NE 					 
1995080400200	19950804	00200	EU 	1995	8	4	EGRA958 	1	19950310	G	6720	391110002	ACTUATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										SPAS	INOPERATIVE 	E			EGRA	O				OTHER 				L			NO TEST 			TO	TAKEOFF 	1			EA	17	7062J	2523 				7178				SPAS ACTUATOR INOPERATIVE, SYSTEM WILL NOT TEST CORRECTLY. REPLACED SPAS ACTUATOR.						1	G	7	2 	3U				H13EU 					 
1995080400201	19950804	00201	NE 	1995	8	4	EGRA9580 	1	19950503	G	6220	SB5064102	BEARING 			SKRSKY	S76 	S76 	8143010	NE 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				PITCH LINK BEARING FOUND WORN REPLACED BEARING						1	G	7	2 	3U				H1NE 					 
1995080400202	19950804	00202	NE 	1995	8	4	EGRA9581 	1	19950503	G	6230	SB5083101	BEARING 			SKRSKY	S76 	S76 	8143010	NE 										SWASHPLATE	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				ROTATING SWASHPLATE BEARING FOUND WORN REPLACED BEARING						1	G	7	2 	3U				H1NE 					 
1995080400203	19950804	00203	NE 	1995	8	4	EGRA9582 	1	19950503	G	6220	MS200028	WASHER 			SKRSKY	S76 	S76 	8143010	NE 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				PITCH LINK ROD WASHERS FOUND WORN REPLACED WASHERS						1	G	7	2 	3U				H1NE 					 
1995080400204	19950804	00204	NE 	1995	8	4	EGRA9584 	1	19950503	G	6230	NAS111075D	BOLT 			SKRSKY	S76 	S76 	8143010	NE 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				STATIONARY SCISSORS BOLT FOUND WORN. REPLACED BOLT						1	G	7	2 	3U				H1NE 					 
1995080400205	19950804	00205	NE 	1995	8	4	EGRA9585 	1	19950503	G	6230	NAS111087D	BOLT 			SKRSKY	S76 	S76 	8143010	NE 										M/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				STATIONARY SCISSORS BOLT FOUND WORN REPLACED BOLT						1	G	7	2 	3U				H1NE 					 
1995080400206	19950804	00206		1995	8	4	EGRA9586 	4	19950504	G	3451	DMNI5062	ANTENNA 			SKRSKY	S76 	S76 	8143010	NE 										DME	CRACKED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				ANTENNA FOUND CRACKED REPLACED ANTENNA						1	G	7	2 	3U				H1NE 					 
1995080400207	19950804	00207	NE 	1995	8	4	EGRA9587 	1	19950504	G	6730	7665005803102	SERVO 			SKRSKY	S76 	S76 	8143010	NE 										T/R	LEAKING 	E			EGRA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				TAIL ROTOR SERVO FOUND LEAKING REMOVED SERVO AND SENT FOR REPAIR. REINSTALLED LEAK CHECKED GOOD, OPS CHECKED GOOD						1	G	7	2 	3U				H1NE 					 
1995080400208	19950804	00208	NE 	1995	8	4	EGRA9588 	1	19950505	G	6730	7665009807101	SERVO 			SKRSKY	S76 	S76 	8143010	NE 										M/R	LEAKING 	E			EGRA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				MAIN ROTOR SERVO FOUND LEAKING, REMOVED AND SENT FOR REPAIR REINSTALLED SERVO AFTER REPAIR LEAK CHECKED GOOD, OP CHECKE	D GOOD					1	G	7	2 	3U				H1NE 					 
1995080400209	19950804	00209	NE 	1995	8	4	EGRA9589 	1	19950505	G	6410	7610105501042	BLADE 			SKRSKY	S76 	S76 	8143010	NE 										T/R	DISBONDED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				TAIL ROTOR BLADE HAS DISBONDED SNUBBER PADS.						1	G	7	2 	3U				H1NE 					 
1995080400210	19950804	00210	NE 	1995	8	4	EGRA9590 	1	19950505	G	6410	7610105501042	BLADE 			SKRSKY	S76 	S76 	8143010	NE 										T/R	DISBONDED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	399KK	298 				760421				TAIL ROTOR BLADE HAS DEBONDED SNUBBER PADS INSTALLED REPAIRED TAIL ROTOR BLADE FROM CTI						1	G	7	2 	3U				H1NE 					 
1995080400211	19950804	00211		1995	8	4	EGRA9591 	4	19950510	G	2312	3002181050	AUDIO CARD 		RT138 	SKRSKY	S76 	S76B 	8143007	NE 										VHF	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	1NJ					760331				HIGH BAND RADIO RT-138 HAS CONSTANT SQUELCH ON SELECTED PL TONES RT-138F, P/N 400-014525, S/N 1285 TROUBLESHOT AND REPL	ACED DEFECTIVE A3 AUDIO CARD, P/N 300-2181-050. REPAIR DONE IAW VENDOR REPORT #1325, JUL 1/89.					1	G	7	2 	4U				H1NE 					 
1995080400212	19950804	00212	SW 	1995	8	4	EGRA9592 	1	19950522	G	6220		TRUNNION 			BELL 	206 	206L 	1181522	SW 										M/R	OFF CENTER 	E			EGRA	C				ABORTED TAKEOFF 				O			OTHER 			TO	TAKEOFF 	1			EA	17	3NJ					52107				DURING GROUND RUN UP OF AIRCRAFT A GROUND BOUNCE CONDITION OCCURRED. CHECKED CENTERING ON M/R HEAD TRUNNION. TRUNNION OF	F CENTER BY .003. ADJUSTED TRUNNION. REASSEMBLIED. C/W MAIN ROTOR TRACK AND BLANCE, CHECKED GOOD.					1	G	7	1 	3U				H2SW 					 
1995080400213	19950804	00213		1995	8	4	EGRA9593 	4	19950523	G	3452	066011410101	TRANSPONDER 			BELL 	206 	206L 	1181522	SW 										COCKPIT	DEFECTIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	3NJ	17 				52107				IDENT BUTTON STICKS. REPLACED TRANSPONDER.						1	G	7	1 	3U				H2SW 					 
1995080400214	19950804	00214	EU 	1995	8	4	EGRA9594 	1	19950608	G	6720	11731822	PITCH LINK ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2505 				7178				TAIL ROTOR PITCH LINK ROD ASSY'S FOUND WORN. REPLACED TAIL ROTOR PITCH LINK ROD ASSY'S.						1	G	7	2 	3U				H13EU 					 
1995080400215	19950804	00215	EU 	1995	8	4	EGRA9595 	1	19950608	G	7931	IPT70RT11000250G	TRANSDUCER 			BOLKMS	117 	BK117B1 	5626012	EU 										OIL PRESS	FAILED 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2542 				7178				NO OUPUT WITH OIL PRESSURE APPLIED REPLACED PRESSURE TRANSDUCER						1	G	7	2 	3U				H13EU 					 
1995080400216	19950804	00216	EU 	1995	8	4	EGRA9596 	1	19950608	G	6320	1172321801	STAY ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										XMSN LT	WORN 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17	7062J	2555 				7178				LEFT HAND TRANSMISSION STAY ASSY FOUND WORN BEYOND LIMITS REPLACED LEFT HAND STAY ASSY.						1	G	7	2 	3U				H13EU 					 
1995080400217	19950804	00217	EU 	1995	8	4	EGRA9597 	1	19950608	G	2422	2A10001G	INVERTER 			AEROSP	SA365 	AS365N2 	8680815	EU 										AC SYS	INOPERATIVE 	E			EGRA	C				ABORTED TAKEOFF 				H			ELECT. POWER LOSS-50 PC 			TO	TAKEOFF 	1			EA	17	272NE	219 				6435				INVERTER INOPERATIVE REPALCED INVERTER.						1	G	7	2 	3U			RT	H10EU 					 
1995080400218	19950804	00218	NE 	1995	8	4	EGRA9598 	1	19950609	G	2121	7650007901102	BLOWER MOTOR 			SKRSKY	S76 	S76A 	8143006	NE 										AIR DIST	INOPERATIVE 	E			EGRA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	17										UNIT INOPERATIVE UPON INSTALLATION REPLACED WITH ANOTHER UNIT						1	G	7	2 	3U				H1NE 					 
1995080400219	19950804	00219	EU 	1995	8	4	EGRA9599 	1	19950612	G	2422	2A10001G	INVERTER 			AEROSP	SA365 	AS365N2 	8680815	EU 										AC SYS	INOPERATIVE 	E			EGRA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	17	272NE	7 				6435				INOPERATIVE, WIRED INCORRECTLY FROM AEC. REPLACED INVERTER.						1	G	7	2 	3U			RT	H10EU 					 
1995070700351	19950707	00351	NE 	1995	7	7	EKGA9520836 	2	19950505	G	7321	0164448080	FUEL CONTROL 			SNIAS 	350 	AS350B 	8680801	EU 	TMECA 	ARRIEL	ARRIEL1B 	6OO30	NE 					ENGINE	DEFECTIVE 	E			EKGA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	123TV	2057 				1682	4045			FCU WILL NOT PRODUCE MINIMUM ROTOR RPM.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995091500237	19950915	00237	GL 	1995	9	15	EKGA9520837 	2	19950505	G	7261	6854424	SHAFT SEAL 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30P 	03013	GL 					STARTER DRIVE	LEAKING 	E			EKGA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	07	303PS	291 				23016	898237			STARTER DRIVE SEAL IS LEAKING.						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995070700352	19950707	00352	SW 	1995	7	7	EKGA9520860 	1	19950505	G	6220	222310117103	SPRING 			BELL 	230 	230 	1182149	SW 										M/R FLAPPING	DEFECTIVE 	E			EKGA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	303PS	347 				23016				M/R FLAPPING SPRING IS DEFECTIVE.						1	G	7	2 	3U			NC	H9SW 					 
1995070700353	19950707	00353	SW 	1995	7	7	EKGA9520861 	1	19950505	G	6220	222310117103	SPRING 			BELL 	230 	230 	1182149	SW 										M/R FLAPPING	DEFECTIVE 	E			EKGA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	303PS	347 				23016				M/R FLAPPING SPRING IS DEFECTIVE.						1	G	7	2 	3U			NC	H9SW 					 
1996092600002	19960926	00002	GL 	1996	9	26	ERAA9565 	2	19950503	G	7250	6898782	WHEEL 								ALLSN 	250C 	250C20B 	03013	GL 					2ND STAGE	DAMAGED SPLINE 	A			ERAA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03										NEW WHEELS WITH -0- HRS THAT HAVE 2ND STAGE WHEELS HAVE DAMAGED SPLINES.											3	U			E4CE				 
1996092600003	19960926	00003	GL 	1996	9	26	ERAA9566 	2	19950503	G	7250	A6898784	ADAPTER 								ALLSN 	250C 	250C20B 	03013	GL 					SPLINED ADAPTER	ROUGH SPLINES 	A			ERAA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			AL	03										NEW ADAPTERS WITH -0- HOURS HAVE ADAPTER HAS ROUGH SPLINES.SERIAL NUMBERS ARE PX253, PX231, PX252											3	U			E4CE				 
1995081100230	19950811	00230	EU 	1995	8	11	F6LM95101 	1	19950727	G	6410	355A09103600	BEARING 		355A12004008	SNIAS 	350 	AS350B2 	8680813	EU 										T/R	TORN 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	490 			4169	2671				BEARINGS TORN BEYOND LIMITS BEARINGS REPLACED BY AMERICAN EUROCOPTER DURING BLADE MINOR REPAIR, (WO 04153)						1	G	7	1 	3U				H9EU 					 
1995081100231	19950811	00231	EU 	1995	8	11	F6LM95102 	1	19950727	G	6220	704A3363310951	STOP ASSY 		350A31000106	SNIAS 	350 	AS350B2 	8680813	EU 										M/R HEAD	DEFECTIVE 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	995 			M1077	2671				BEARING HAS A BLISTER AND RUBBER RUNS AT TOP. REPLACED BEARING						1	G	7	1 	3U				H9EU 					 
1995081100232	19950811	00232	EU 	1995	8	11	F6LM95103 	1	19950727	G	6220	704A3363310951	STOP ASSY 		350A31000106	SNIAS 	350 	AS350B2 	8680813	EU 										M/R HEAD	DEFECTIVE 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	995 			M1077	2671				BEARING HAS DEEP WEATHER CRACKS, REPLACED BEARING						1	G	7	1 	3U				H9EU 					 
1995081100233	19950811	00233	EU 	1995	8	11	F6LM95104 	1	19950727	G	6220	704A3363310951	STOP ASSY 		350A31000106	SNIAS 	350 	AS350B2 	8680813	EU 										M/R HEAD	CRACKED 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	995 			M1077	2671				BEARING HAS LOTS OF DEEP WEATHER CRACKS, REPLACED BEARING						1	G	7	1 	3U				H9EU 					 
1995081100234	19950811	00234	EU 	1995	8	11	F6LM95105 	1	19950727	G	6410	355A12004008	BLADE TAB 		355A12004008	SNIAS 	350 	AS350B2 	8680813	EU 										T/R	SEPARATION 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	995 				2671				BLADE HAS TRAILING EDGE TAB SEPARATION OUTBOARD OF RIVET ON BOTH BLADES. INSTALLED RENTAL T/R BLADE.						1	G	7	1 	3U				H9EU 					 
1995081100235	19950811	00235	EU 	1995	8	11	F6LM9572 	1	19950124	G	2911	08226801902	ACCUMULATOR 			SNIAS 	350 	AS350B2 	8680813	EU 										HYD	DEFECTIVE 	H			F6LM	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SO	19	6093B	878 				2670				HAD NO ACCUMUALTOR TEST TO THE LEFT, FOUND ACCM. HAD NO PRESSURE, DURING SERVICING COULD HEAR AIR IN HYD RESV. REPLACED 	ACCUMULATOR & SERVICED SYSTEM WITH NITROGEN. LEAK CHECK OKAY.					1	G	7	1 	3U				H9EU 					 
1995081100236	19950811	00236	EU 	1995	8	11	F6LM9573 	1	19950125	G	6730	SC50821	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	LEAK 	H			F6LM	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	6093B	345 				2670				LEAKS @ TOP WEEP HOLE REPLACED SERVO						1	G	7	1 	3U				H9EU 					 
1995081100237	19950811	00237	EU 	1995	8	11	F6LM9576 	1	19950210	G	5412	350A5801100801	FIREWALL 			SNIAS 	350 	AS350B2 	8680813	EU 										LOWER	CRACKED 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	905 				2670				FIREWALL CRACKED @ THE TOP OF THE "X" (LOTS OF CRACKS) REPLACED FIREWALL.						1	G	7	1 	3U				H9EU 					 
1995081100238	19950811	00238	EU 	1995	8	11	F6LM9578 	1	19950210	G	2810	1578	KNOB 			SNIAS 	350 	AS350B2 	8680813	EU 										TANK PURGE	FAILED 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	905 				2670				TANK PURGE ASSY KNOB FELL OFF, PARTS BOOK SHOW A KNOB BUT RECEIVED A COMPLET CABLE ASSY. REPLACED JUST THE CENTER PORTI	ON FROM THE NEW CABLE ASSY					1	G	7	1 	3U				H9EU 					 
1995081100239	19950811	00239	EU 	1995	8	11	F6LM9579 	1	19950214	G	2435	150SG10095	STARTER 		150SG122Q 	SNIAS 	350 	AS350B2 	8680813	EU 										START/GEN	FAILED 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	275 			7295	2671				STARTER WOULD NOT TURN , FOUND BRUSHES WORN BEYOND LIMITS. SUBMITTER STATES THIS SEEMS TO BE A PROBLEM WITH THIS TYPE O	F STARTER. ONLY GETTING ABOUT 250-300 H RS OF BRUSH LIFE. REPLACED BRUSHES.					1	G	7	1 	3U				H9EU 					 
1995081100240	19950811	00240		1995	8	11	F6LM9580 	4	19950222	G	3416	5934P1A83	ALTIMETER 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT	READS LOW 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	793 				2671				READS 125 FT LOW. REPLACED ALTIMETER						1	G	7	1 	3U				H9EU 					 
1995081100241	19950811	00241	NE 	1995	8	11	F6LM9581 	2	19950227	G	7421	956013490	HE IGNITER 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					ENGINE	DEFECTIVE 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	744 				2671	9241			IGNITER WOULD NOT FIRE, TESTED ON OTHER BOX STILL INOP. REPLACED HE IGNITER, OPS CHECKED OKAY						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995081100242	19950811	00242	EU 	1995	8	11	F6LM9582 	1	19950302	G	2121	420800001	BLOWER ASSY 			SNIAS 	350 	AS350B2 	8680813	EU 										AIR COND	INOPERATIVE 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	804 				2671				A/C WEAK, FOUND L/H CONDENSOR BLOWER INOP REPLACED BLOWER ASSY						1	G	7	1 	3U				H9EU 					 
1995081100243	19950811	00243	EU 	1995	8	11	F6LM9583 	1	19950313	G	6520	350A33215300	HINGE LAMINATE 		350A33020005	SNIAS 	350 	AS350B2 	8680813	EU 										T/R	TORN 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	602 			MA0148	2670				ONE BEARING TORN COMPLETLY AROUND. REPLACED BEARINGS						1	G	7	1 	3U				H9EU 					 
1995081100244	19950811	00244	EU 	1995	8	11	F6LM9584 	1	19950314	G	6520	350A33200403	SPIDER 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	DEFECTIVE 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	969 				2670				SLIPPAGE MARK ON OUTER BAFFLE NO LONGER ALIGNED, SUSPECT THAT NUT HAS LOST TORQUE. REPLACED CONTROL PLATE ASSY.						1	G	7	1 	3U				H9EU 					 
1995081100245	19950811	00245	EU 	1995	8	11	F6LM9586 	1	19950331	G	6730	SC50811	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	LEAKS 	H			F6LM	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	6093B	493 				2670				LEAKS FLUID FROM BODY EXTENSION WEEP HOLE.						1	G	7	1 	3U				H9EU 					 
1995081100246	19950811	00246	EU 	1995	8	11	F6LM9587 	1	19950407	G	6220	RL12R	BALL JOINT 		350A31003306	SNIAS 	350 	AS350B2 	8680813	EU 										ANTIVIBRATOR	WORN 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	998 			M763	2670				FELT PLAY IN PIVOT BEARING, DISASSEMBLED TO REPLACE, FOUND THAT THE LEAD WEIGHT WAS RUBBING ON THE SUPPORT DUE TO THE PL	AY IN THE BEARING . THAT ALLOWED THE WEIGHT TO DROP DOWN ONTO THE SUPPORT. THE INSPECTION INTERVAL FOR THE ANTIVIBRATOR	 IS 2400HRS. REPLACED BEARING , ALSO C/W SB 62-22, AMS 350A07-6199. TOUCHED UP COATING ON SUPPORT. THE INSPECTION INTER	VAL SHOULD BE REDUCED TO 1000 HRS UNTILL A BETTER BEARING IS INTRODUCED			1	G	7	1 	3U				H9EU 					 
1995081100247	19950811	00247	EU 	1995	8	11	F6LM9588 	1	19950407	G	6220	704A3363310951	STOP ASSY 		355A31000106	SNIAS 	350 	AS350B2 	8680813	EU 										M/R	BLISTERS 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	998 			M1082	2670				BLISTERS FORMING ON UPPER SURFACE. REPLACED SPHERICAL STOP						1	G	7	1 	3U				H9EU 					 
1995081100248	19950811	00248	EU 	1995	8	11	F6LM9589 	1	19950407	G	6220	704A3363310951	STOP ASSY 		355A31000106	SNIAS 	350 	AS350B2 	8680813	EU 										M/R	BLISTERS 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	988 			M1082	2670				BLISTERS FORMING ON TOP SURFACE. REPLACED SPHERICAL STOP						1	G	7	1 	3U				H9EU 					 
1995081100249	19950811	00249	EU 	1995	8	11	F6LM9590 	1	19950407	G	6220	704A3363310951	STOP ASSY 		355A31000106	SNIAS 	350 	AS350B2 	8680813	EU 										M/R	BLISTER 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	998 			M1082	2670				BLISTER FORMING ON TOP SURFACE. REPLACED SPHERICAL STOP						1	G	7	1 	3U				H9EU 					 
1995081100250	19950811	00250	EU 	1995	8	11	F6LM9591 	1	19950413	G	6410	355A09103600	BEARINGS 		355A12004008	SNIAS 	350 	AS350B2 	8680813	EU 										T/R HALFSHELL	TORN 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	633 			5060	2670				HALFSHELL BEARINGS TORN BEYOND LIMITS AT CORNERS REPLACED BEARINGS. NOTE: BEARING LIFE HAS IMPROVED SINCE INCORPERATION 	OF MOD 07-5588					1	G	7	1 	3U				H9EU 					 
1995081100251	19950811	00251	EU 	1995	8	11	F6LM9592 	1	19950413	G	7922	9696	MOTOR 			SNIAS 	350 	AS350B2 	8680813	EU 										TEMP REG	SEIZED 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	998 				2670				MOTOR WILL NOT SPIN. BEARINGS FEEL SEIZED. CURRENT LIMITER BLOWN. THE MOTOR HAS OPEN VENT SCREENS WHICH ALLOWS WATER INS	IDE THE MOTOR. REPLACED THE MOTOR. NEW MOTOR IS POST MOD 07-2515 WHICH HAS BETTER COVERING OF THE VENT HOLES. REPLACED 	CURRENT LIMITER				1	G	7	1 	3U				H9EU 					 
1995081100252	19950811	00252	EU 	1995	8	11	F6LM9593 	1	19950413	G	6730	123668P	BEARINGS 			SNIAS 	350 	AS350B2 	8680813	EU 										BALLJOINT	WORN 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	998 				2670				BEARINGS WORN PAST THE .002" WEAR LIMIT. REPLACED BEARINGS						1	G	7	1 	3U				H9EU 					 
1995081100253	19950811	00253	EU 	1995	8	11	F6LM9594 	1	19950413	G	5410	350A5801100801	FIREWALL 			SNIAS 	350 	AS350B2 	8680813	EU 										TOP CORNER	CRACKED 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6093B	94 				2670				CRACKED AT THE UPPER SUPPORT CORNERS. THIS FIREWALL WAS INSTALLED FOR 93 HOURS REPLACED THE FIRE WALL. ON INSTALLATION 	WE HAD TO SHIM THE LEGS TO GET A STRESS FREE INSTALLATION, USED MGB UPPER COWLS TO POSITION FIREWALL PRIOR TO FINAL TIGH	TENING AJUSTED ENGINE COWL LATCHES TO NOT PULL VERY TIGHT ON THE RUBBER STOPS AS TO NOT LOAD THE FIREWALL.				1	G	7	1 	3U				H9EU 					 
1995081100254	19950811	00254	NE 	1995	8	11	F6LM9595 	2	19950502	G	7321	0164248690	FUEL CONTROL 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					ENGINE	MALFUNCTION 	H			F6LM	K				NONE 				O			OTHER 			CR	CRUISE 	1			SO	19	6093B	984 				2670	9253			NG/TQ OCCILLATIONS DURING CRUSE. SUBSTITUTED FCU WITH ANOTHER AIRCRAFT, PROBLEM FOLLOWED FCU. INSTALLED RENTAL FCU.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995081100255	19950811	00255	EU 	1995	8	11	F6LM9597 	1	19950511	G	6730	SC50811	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	LEAK 	H			F6LM	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SO	19	6093B	535 				2670				EXCESSIVE LEAK FROM WEEP HOLE, JUST HAD SERVO REAIRED FOR SAME LEAK. INSTALLED LOANER SERVO						1	G	7	1 	3U				H9EU 					 
1995081100256	19950811	00256	EU 	1995	8	11	F6LM9598 	1	19950517	G	6520	350A33215300	HINGE LAMINATE 		350A33020005	SNIAS 	350 	AS350B2 	8680813	EU 										T/R	TORN 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	404 			MA0129	2671				TORN BEYOND LIMITS, (LOW LIFE ON THIS PART, SUBMITTER SUGGESTS DUE TO THE HEAT FROM THE EXHAUST.) REPLACED BEARINGS						1	G	7	1 	3U				H9EU 					 
1995081100257	19950811	00257	EU 	1995	8	11	F6LM9599 	1	19950517	G	6720	350A33214501	ROD BEARING 		350A33020005	SNIAS 	350 	AS350B2 	8680813	EU 										PITCH CONTROL	WORN 	H			F6LM	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	6095T	908 			MA0129	2671				SPHERICAL BEARINGS HAVE PLAY REPLACED CONTROL RODS						1	G	7	1 	3U				H9EU 					 
1995041400077	19950414	00077	SW 	1995	4	14	GCHA951 	1	19950405	G	3211	206033108001	FITTING 			BELL 	206 	206L1 	1182107	SW 										CROSS TUBE	CHAFED 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	177PA	2962 				45194				SIDE OF FITTING WORN FROM CHAFING AGAINST STOPS ON CROSS TUBE. REMOVED AND REPLACED FITTING.						1	G	7	1 	3U				H2SW 					 
1995060900106	19950609	00106	SW 	1995	6	9	GCHA9510 	1	19950428	G	6230	206040532005	CASE ASSY 			BELL 	206 	206L1 	1182107	SW 										M/R MAST	BELOW SPECS 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	177PA					45194				P/N 206-040-532-005 S/N A-27 THE SPINDLE MT. BORES ARE BELOW MFG'S MINIMUM NEW DIMENSION. AVG. .003" INTERFERENCE FIT	 BETWEEN SPINDLE AND CASE. ALSO NOTED 1 STUD FOR COLLECTIVE BELL CRANK SUPPORT HAS BEEN AND OVERSIZED REPAIR. REMOVED A	ND REPLACED S/N A-27 WITH P/N 206-040-532-005 S/N A-22.				1	G	7	1 	3U				H2SW 					 
1995060900107	19950609	00107	SW 	1995	6	9	GCHA9512 	1	19950601	G	7120	206064105002	LEG ASSY 			BELL 	206 	206L1 	1182107	SW 										ENG MOUNT	BROKEN 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	2072M	13747				45720				THE ENGINE MOUNT LEG WAS BROKEN DIRECTLY ABOVE PORTION OF LOWER EYELET THAT IS BONDED INSIDE THE LEG. THIS WAS DUE TO 	INTERNAL CORROSION. MOSTLY CAUSED BY CREVICE CORROSION. CREVICE CORROSION USUALLY STARTS BETWEEN TWO PIECES OF MATERI	AL THAT ARE IN CONTACT. THE CREVICE ALLOWS AN ELECTROLYTE TO ACCUMULATE AND STAGNATE, THUS CREATING A CONCENTRATION CEL	L. THE LEG WAS BROKEN IN THE AREA BENEATH THE ADEL CLAMP. THERE WAS NO VISIBLE SIGNS OF CORROSION ON THE OUTER SURFACE.	 REMOVED AND REPLACED ENGINE MOUNT LEG. THE BREAK WAS DISCOVERED DURING A ROUTINE 100 HOUR MAINTENANCE INSPECTION.		1	G	7	1 	3U				H2SW 					 
1995062300604	19950623	00604	SW 	1995	6	23	GCHA9513 	1	19950614	G	5320	206033110239	STIFFENER 			BELL 	206 	206L3 	1182108	SW 										FUSELAGE	CRACKED 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	3893U	7871 				51020				DURING A SCHEDULED 100 HOUR INSPECTION CRACKS WERE FOUND ON STRUCTURAL STIFFENER, APPROX. 4" FROM UPPER END. A/CTT: 107	82.7 REMOVED AND REPLACED STIFFENER , P/N 206-033-110-239 WITH LIKE PART NUMBER.					1	G	7	1 	3U				H2SW 					 
1995081100258	19950811	00258	SW 	1995	8	11	GCHA9514 	1	19950614	G	6320	206040004101	TRANSMISSION 		206040004101	BELL 	206 	206L1 	1182107	SW 										M/R GR BOX	GEAR FAILED 	I			GCHA	A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			WP	19	27694	6930 			BMC45077	45282				DURING FLIGHT A/C REGISTERED TRANSMISSION CHIP LIGHT. PERFORMED AN UNSCHEDULED LANDING. IT WAS FOUND TO HAVE METAL IN 	OIL CAUSED BY A BEVEL GEAR FAILURE. ACTT 6002.6. REMOVED AND REPLACED TRANSMISSION .					1	G	7	1 	3U				H2SW 					 
1995081100259	19950811	00259	SW 	1995	8	11	GCHA9518 	1	19950801	G	6320	206040004101	TRANSMISSION 		206040004101	BELL 	206 	206L1 	1182107	SW 										M/R GR BOX	BEARING FAILED 	I			GCHA	A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			WP	19	57491	9794 			BMC00503	45505				DURING FLIGHT A/C REGISTERED TRANSMISSION CHIP LIGHT. PERFORMED AN UNSCHEDULED LANDING . IT WAS FOUND TO HAVE , METAL 	IN OIL, DUE TO DUPLEX BEARING FAILURE. ACTT 7243.3. REMOVED AND REPLACED TRANSMISSION BMC 00503 WITH S/N BMC 45364.					1	G	7	1 	3U				H2SW 					 
1995060900108	19950609	00108	SW 	1995	6	9	GCHA952 	1	19950404	G	6230	206010452005	SUPPORT 			BELL 	206 	206L1 	1182107	SW 										M/R	REQ REPLACEMENT 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	177PA	2962 				45194				SPECIAL WARRANTY CREDIT. SATISFIES AD94-19-02 PAR. F. IT ALSO SATISFIES ASB206-93-74 REV. B AS PUBLISHED IN ROTORBREEZE	 VOL 44, NO. 5 REMOVED AND REPLACED SUPPORT. REMOVED AND REPLACED SUPPORT.					1	G	7	1 	3U				H2SW 					 
1995060900109	19950609	00109	SW 	1995	6	9	GCHA953 	1	19950404	G	6230	206010452109	SUPPORT 			BELL 	206 	206L1 	1182107	SW 										M/R	REQ REPLACEMENT 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	5745Y	2253 				45531				SPECIAL WARRANTY CREDIT. SATISFIES AD94-19-02 PAR. F. ALSO SATISFIES ASB206-93-74 REV. B. AS PUBLISHED IN ROTORBREEZE 	VOL. 44, NO. 5. REMOVED AND REPLACED. REMOVED AND REPLACED.					1	G	7	1 	3U				H2SW 					 
1995060900110	19950609	00110	SW 	1995	6	9	GCHA954 	1	19950413	G	5311	206033110151	STIFFENER 			BELL 	206 	206L1 	1182107	SW 										ROOF BEAM	CRACKED 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	27694	5818 				45282				DURING SCHEDULED ANNUAL INSPECTION CRACKS WERE FOUND AT THE STRUCTURAL ATTACHMENT OF CENTER POST TO THE ROOF BEAM ASSY	. A/C TOTAL TIME: 5818.3 C/W TB 206L-79-41 STRUCTURAL ATTACHMENT OF CENTER POST INSTALLATION, P/N 206-033-110-003 OR -	005, TO ROOF BEAM ASSY, P/N 206-033-210-001, INSPECTION AND MODIFICATION OF.				1	G	7	1 	3U				H2SW 					 
1995060900111	19950609	00111	SW 	1995	6	9	GCHA955 	1	19950413	G	2810	206064611001	FUEL CELL 			BELL 	206 	206L1 	1182107	SW 										FILLER NECK	DEFECTIVE 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	27694	5818 				45282				DURING SCHEDULED ANNUAL INSPECTION, THE FUEL CELL WAS INSPECTED AND FOUND TO HAVE FUNGAL GROWTH IN THE FUEL FILLER NECK	 AREA. FUEL CELL WAS REMOVED AND REPLACED. OLD CELL WAS CLEANED AND SHIPPED TO MANUFACTURER FOR RECERTIFICATION.					1	G	7	1 	3U				H2SW 					 
1995060900112	19950609	00112	SW 	1995	6	9	GCHA956 	1	19950413	G	5311	206033210001	BEAM 			BELL 	206 	206L1 	1182107	SW 										CABIN ROOF	CRACKED 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	177PA	2962 				45194				DURING SCHEDULED ANNUAL INSPECTION, CRACKS WERE FOUND ON THE FWD ROOF BEAM, STA. 83 , AT INTERSECTION OF VERTICAL TUNN	EL. CRACKS WERE FOUND IN THE INSIDE LEFT HAND SIDE AND THE RIGHT HAND CORNER.					1	G	7	1 	3U				H2SW 					 
1995060900113	19950609	00113	GL 	1995	6	9	GCHA957 	2	19950413	G	7230	23005250	COMPRESSOR 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C30P 	03013	GL 					SCROLL	CRACKED 	I			GCHA	K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			WP	19	4227E	7600 				45702	CAE890233			REMOVED COMPRESSOR DUE TO CRACKED COMPRESSOR SCROLL AND LOW POWER. REMOVED COMPRESSOR S/N CAC-90608, AND REPLACED I	T WITH COMPRESSOR S/N CAC-90095.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995060900114	19950609	00114	SW 	1995	6	9	GCHA958 	1	19950419	G	6420	206011819101	YOKE 			BELL 	206 	206L1 	1182107	SW 										T/R	WORN 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19	2072M	2500 				45720				TAIL ROTOR YOKE REMOVED DUE TO EXCESSIVE FLAP RESTRAINT BUMPER WEAR. A REPLACEMENT YOKE HAS NOT YET BEEN ORDERED FOR T	AIL ROTOR HUB 206-011-810-125 S/N A-5332.					1	G	7	1 	3U				H2SW 					 
1995060900115	19950609	00115	SW 	1995	6	9	GCHA959 	1	19950420	G	6220	206010101129	YOKE 			BELL 	206 	206A 	1181508	SW 										M/R	CORRODED 	I			GCHA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	19		2400 								M/R YOKE P/N 206-010-101-129 S/N A2744 WAS EVALUATED , CPR # 064540, AND WAS FOUND TO HAVE CORROSION ON BEARING JOURNAL	S BEYOND ACCEPTABLE LIMITS. THE YOKE WAS REMOVED AND REPLACED.					1	G	7	1 	3U				H2SW 					 
1995070700354	19950707	00354	SW 	1995	7	7	GJQA9520870 	1	19950505	G	6520	206340103101	SEAL 			BELL 	206 	206L4 	1182110	SW 										T/R GR BOX	LEAKING 	E			GJQA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			NM	01	404W	340 				52055				T/R GEARBOX INPUT SEAL LEAKING, ALSO USED 1 EACH M8348/1-230						1	G	7	1 	3U			NC	H2SW 					 
1995090800156	19950908	00156	SW 	1995	9	8	GJQR9513 	1	19950616	G	7714	206075682107	INDICATOR 			BELL 	206 	206L 	1181522	SW 										GAS PRODUCER	INOPERATIVE 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W					52055				INDICATOR INOP. REPLACED WITH NEW INDICATOR.						1	G	7	1 	3U				H2SW 					 
1995090800157	19950908	00157	SW 	1995	9	8	GJQR9524 	1	19950713	G	3211	206033108001	FITTING 			BELL 	206 	206L 	1181522	SW 										MLG	WORN 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	805 				52055				CROSS TUBE RUBBED AGAINST FITTING CREATING TOO MUCH WEAR ON FITTING. REPLACED WITH NEW PARTS						1	G	7	1 	3U				H2SW 					 
1996121200108	19961212	00108	SW 	1996	12	12	GJQR9542 	1	19951012	G	6230	206340101101	SEAL 			BELL 	206 	206L 	1181522	SW 										M/R MAST	CORRODED 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	980 				52055				MAIN ROTOR MAST SEAL HAD HEAVY CORROSION ON SEAL METAL HOUSING. REPLACED SEAL FROM CSF STOCK. REMOVED SEAL AND SENT TO	 NOEL PAQUETTE, PRODUCT SUPPORT IN QUEBEC.					1	G	7	1 	3U				H2SW 					 
1996121200109	19961212	00109		1996	12	12	GJQR9543 	4	19951012	G	3120	206070275005	CLOCK 			BELL 	206 	206B3 	1181506	SW 										COCKPIT	FAILED 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	995PM	30 				4121				WHEN WINDING UP CLOCK, UNIT COMES UNWOUND, SPRING BROKEN.						1	G	7	1 	3U				H2SW 					 
1996121200110	19961212	00110	SW 	1996	12	12	GJQR9553 	1	19951117	G	6230	206010443001	DUPLEX BEARING 			BELL 	206 	206L 	1181522	SW 										M/R	ROUGH 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	980 				52055				BEARING FEELS ROUGH & HAS SURFACE CORROSION REPLACED						1	G	7	1 	3U				H2SW 					 
1996121200111	19961212	00111	SW 	1996	12	12	GJQR9554 	1	19951117	G	6230	206010459001	BEARING 			BELL 	206 	206L 	1181522	SW 										SWASHPLATE	WORN 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	980 				52055				BEARING WORN & ROTATION. REPLACED						1	G	7	1 	3U				H2SW 					 
1996121200112	19961212	00112	SW 	1996	12	12	GJQR9555 	1	19951117	G	6230	206010441001	BEARING ASSY 			BELL 	206 	206L 	1181522	SW 										M/R	WORN 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	980 				52055				BEARING WORN. REPLACED						1	G	7	1 	3U				H2SW 					 
1996062700388	19960627	00388	SW 	1996	6	27	GJQR9561 	1	19951220	G	6220	206011139001	ARM ASSY 			BELL 	206 	206B3 	1181506	SW 										M/R	STICKING 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	86W	350 				4142				ARM STARTED STICKING IN FLIGHT POSITION AFTER SHUTTING DOWN AIRCRAFT. AFTER REPEATED ATTEMPTS TO FREE UP ARM, REPLACED	 IT.					1	G	7	1 	3U				H2SW 					 
1996010500036	19960105	00036	SW 	1996	1	5	GMAL9509141 	1	19950914	G	6210	K911001004	BLADE 			KAMAN 	K1200 	K1200 	05625F6	SW 										MAIN ROTOR	CRACKED 	G		A	GMAL	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	134KA	354 			0027A	A940006				MAIN ROTOR BLADE FOUND CRACKED. CRACK LOCATED AT STA 174, CORDWISE ON BOTTOM OF BLADE AT 10 INCHES LONG, 5 INCHES AFT O	F LEADING EDGE. ONLY 4 HOURS OF FLIGHT SINCE LAST INSPECTION. AIRCRAFT TOTAL TIME 566 HOURS. THREE BLADES FOUND CRACK	ED AT SAME TIME. (X)				1	G	7	1 	4F			NT	TR7BO 					 
1996010500037	19960105	00037	SW 	1996	1	5	GMAL9509142 	1	19951207	G	6210	K911001005	BLADE 			KAMAN 	K1200 	K1200 	05625F6	SW 										MAIN ROTOR	CRACKED 	G		A	GMAL	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	134KA	298 			0034A	A940006				MAIN ROTOR BLADE FOUND CRACKED, CRACK LOCATED BETWEEN STA 172 AND STA 180, CORDWISE ON BOTTOM OF BLADE AT 13 INCHES LONG	, 5 INCHES FROM LEADING EDGE. ONLY 4 HOURS OF FLIGHT SINCE LAST INSPECTION. AIRCRAFT TOTAL TIME 566 HOURS, 3 BLADES FO	UND CRACKED AT SAME TIME. (X)				1	G	7	1 	4F			NT	TR7BO 					 
1996010500038	19960105	00038	SW 	1996	1	5	GMAL9509143 	1	19950914	G	6210	K911001003	BLADE 			KAMAN 	K1200 	K1200 	05625F6	SW 										MAIN ROTOR	CRACKED 	G		A	GMAL	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	134KA	298 			0034B	A940006				MAIN ROTOR BLADE FOUND CRACKED. CRACK LOCATED AT STA 172 AND STA 180, CORDWISE ON BOTTOM OF BLADE AT 13 INCHES LONG, 5 	INCHES FROM LEADING EDGE. ONLY 4 HOURS OF FLIGHT SINCE LAST INSPECTION. ACFT TOTAL TIME, 566 HOURS, 3 BLADES FOUND CRA	CKED AT SAME TIME. (X)				1	G	7	1 	4F			NT	TR7BO 					 
1996010500039	19960105	00039	SW 	1996	1	5	GMAL951207 	1	19951207	G	6210	K911001005	BLADE 			KAMAN 	K1200 	K1200 	05625F6	SW 										M/R	CRACKED 	G		A	GMAL	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	134KA	422 			0033B	A940006				MAIN ROTOR BLADE CRACKED. CRACK LOCATED AT STA 109.5, CORDWISE, TOP 10.25 INCHES LONG, 4.5 INCHES AFT OF LEADING EDGE. 	 ONLY 10 HOURS OF FERRY FLIGHT SINCE LAST INSPECTION. AIRCRAFT TOTAL TIME 985 HOURS. (X)					1	G	7	1 	4F			NT	TR7BO 					 
1996041800141	19960418	00141	SW 	1996	4	18	GMAL9601251 	1	19950602	G	6210	K911001004	BLADE 			KAMAN 	K1200 	K1200 	05625F6	SW 										M/R	CRACKED 	H		A	GMAL	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	135KA	234 			0042B	0007				MAIN ROTOR BLADE CRACKED. CRACK AT BLADE STA 124, 2.9345 INCHES LONG. (X)						1	G	7	1 	4F			NT	TR7BO 					 
1996041800142	19960418	00142	SW 	1996	4	18	GMAL9601252 	1	19951128	G	6210	K911001005	BLADE 			KAMAN 	K1200 	K1200 	05625F6	SW 										M/R	CRACKED 	H			GMAL	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	135KA		752 			0007				MAIN ROTOR BLADE CRACKED. LOCATION UNKNOWN AT THIS TIME. BLADE RETURNED TO MANUFACTURER. (X)						1	G	7	1 	4F			NT	TR7BO 					 
1995092900397	19950929	00397	WP 	1995	9	29	GMCR95006 	1	19950831	G	7921	40D8053	VALVE 			CVAC 	440 	440 	2422902	WP 										OIL COOL EJECTOR	FAILED 	B			GMCR	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			J			WARNING INDICATION 			TO	TAKEOFF 	1			GL	23	5126		1147 			508				DURING TAKEOFF ROLL, RIGHT ENGINE INDICATED LOW HORSEPOWER. ABORTED TAKEOFF. REPLACED DEFECTIVE OIL COOLER EJECTOR VAL	VE. (X)					2	L	7	2 	4R				6A6 					 
1996010500610	19960105	00610	WP 	1996	1	5	GMCR95008 	1	19951208	G	7712	SRT314A	INDICATOR 			CVAC 	440 	440 	2422902	WP 										COCKPIT	DEFECTIVE 	B			GMCR	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			R			PARTIAL RPM/PWR LOSS 			TO	TAKEOFF 	1			GL	23	5122	3269 			810	501				ON TAKEOFF ROLL, PILOT NOTED LOW HP INDICATION ON RT ENGINE. ABORTED TAKEOFF. REPLACED TORQUE INDICATOR, OPS CHECK NOR	MAL. (X)					2	L	7	2 	4R				6A6 					 
1995090800154	19950908	00154	EU 	1995	9	8	GQRR431E 	1	19950816	G	2820		BREAKER 			AMD 	FALC10	FALCON10 	2730101	EU 										NR 1 FUEL XFER	TRIPPED 	B		A	GQRR	O				OTHER 				K			FLUID LOSS 			CR	CRUISE 	1			SW	05	12TX					90				NR 1 FUEL TRANSFER CIRCUIT BREAKER 'POPPED' IN-FLIGHT, CAUSE UNKNOWN. THIS CIRCUIT BREAKER CONTROLS THE FUEL SOLENOID F	ROM THE LEFT WING AS WELL AS THE TIMER THAT CONTROLS THE SOLENOID. UNREGULATED FUEL OVERFILLED BOTH FEEDER TANKS THEN W	AS PIPED, UNDER PRESSURE (FROM THE PRESSURIZATION IN THE WINGS), UP THROUGH THE FEEDER TANK VENT TO THE VERTICAL STABILI	ZER JUST BELOW THE STAB JACK. HERE, FUEL WASHED OVERBOARD, SOME OF WHICH DRAINED DOWN INTO THE TAIL CONE AREA WHERE IT 	PRESENTED A FIRE HAZARD. SB F10-259 ADDRESSES THIS PROBLEM, BUT IS NOT AN AD. THE SYSTEM DOES NOT EASILY ALLOW DETECTI	ON BY THE CREW. SB F10-259 WAS NOT FULLY ACCOMPLISHED. (X)	2	L	7	2 	4F				A33EU 					 
1995040700307	19950407	00307	NM 	1995	4	7	HAC000001 	1	19950125	G	5743	6599909172	SUPPORT FITTING 			BOEING	727 	727281 	138408N	NM 										RT MLG	CRACKED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	902PG					20725				TRUNNION SUPPORT FITTING REMOVED DUE TO CORROSION ON RIGHT WING LOWER REAR SPAR. DURING INSPECTION, A CRACK WAS FOUND I	N BOLT HOLE. THE CRACK WAS 1 INCH LONG AND .3750 INCH DEEP. THE CRACK COULD HAVE BEEN CAUSED BY HARD LANDING OR FLAW I	N CASTING. (X)				2	L	7	3 	4F				A3WE 					 
1998042400254	19980424	00254		1998	4	24	HAI00000046 	1	19951117	G	6220	204011404125	SUPPORT 																	M/R	MIS MFG 	H				K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			FS	01										ONE SET OF GIMBAL RING ATTACHMENT TANGS ARE DISPLACED OR POSITION TOO CLOSE TOGETHER NOT ALLOWING INSERTION OF BEARING B	ETWEEN TANGS AND BUSHINGS WITHOUT EXCESSIVE FORCE OR STRESSING TANGS APART, DEFECT WAS NOTED ON INITIAL RECEIPT OF PART 	INTO STOCK. REPLACED WITH CSF STOCK.																	 
1998042400264	19980424	00264	SW 	1998	4	24	HAIGJQR0053 	1	19951117	G	6230	206010443001	BEARING 			BELL 	206 	206L 	1181522	SW 										M/R MAST	CORRODED 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	980 				52055				FEELS ROUGH & HAS SURFACE CORROSION REPLACED WITH CSF STOCK.						1	G	7	1 	3U				H2SW 					 
1998042400265	19980424	00265	SW 	1998	4	24	HAIGJQR0054 	1	19951117	G	6230	206010459001	BEARING 			BELL 	206 	206L 	1181522	SW 										SWASHPLATE	WORN 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	980 				52055				BEARING WORN & ROTATION. REPLACED WITH CSF STOCK.						1	G	7	1 	3U				H2SW 					 
1998042400266	19980424	00266	SW 	1998	4	24	HAIGJQR0055 	1	19951117	G	6230	206010441001	BEARING 			BELL 	206 	206L 	1181522	SW 										SWASHPLATE	WORN 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	980 				52055				BEARING WORN REPLACED WITH CSF STOCK.						1	G	7	1 	3U				H2SW 					 
1998042400267	19980424	00267	SW 	1998	4	24	HAIGJQR0056 	1	19951117	G	6510	406040340101	DISK PACK 			BELL 	206 	206L 	1181522	SW 										T/R DRIVE	WORN 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	404W	980 				52055				DISC PAC REPLACEMENT DUE TO EXCESSIVE GAP. REPLACED WITH CSF STOCK.						1	G	7	1 	3U				H2SW 					 
1998042400268	19980424	00268	SW 	1998	4	24	HAIGJQR0061 	1	19951220	G	6220	206011139001	ARM 			BELL 	206 	206B3 	1181506	SW 										M/R	STICKING 	H			GJQR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			FS	01	86W	350 				4142				ARM STARTED STICKING IN FLIGHT POSITION AFTER SHUTTING DOWN AIRCRAFT. AFTER REPEATED ATTEMPTS TO FREE UP ARM, REPLACED 	IT WITH CSF STOCK					1	G	7	1 	3U				H2SW 					 
1995070700355	19950707	00355	EU 	1995	7	7	HCMA9520872 	1	19950505	G	6730	SC50821	SERVO 			SNIAS 	350 	AS350B 	8680801	EU 	TMECA 	ARRIEL	ARRIEL1B 	6OO30	NE 					M/R	LEAKAGE 	E			HCMA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			WP	13	862BH	1496 				2713	4465			EXCESSIVE LEAKAGE FROM UPPER SEAM SERVO BODY TO RAM.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995022100102	19950221	00102	SW 	1995	2	21	HEEA954073 	1	19950104	G	6320	L15231487	PACKING 		206040004111	BELL 	206 	206L1 	1182107	SW 										GR BOX	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03					BMC45017					GR BOX LEAKED EXCESSIVELY AFTER INSTALLATION. (APPEARS SEAL TO BE TOO THIN)						1	G	7	1 	3U				H2SW 					 
1995022100103	19950221	00103	SW 	1995	2	21	HEEA954084 	1	19950109	G	6220	206010110105	WASHER 		206011100151	BELL 	206 	206L1 	1182107	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50046	1192 			A101893	45173				EXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO DETERIORATE. SCRAPPED LOCALLY. LOWER TORQUE ON ADJUSTING SCREWS. LOWER PRE	LOAD ON PLUGS.					1	G	7	1 	3U				H2SW 					 
1995022100104	19950221	00104	SW 	1995	2	21	HEEA954085 	1	19950103	G	6220	214010133001	SEAL 		214010100207	BELL 	214 	214ST 	1182106	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M				A380	28102				UNBONDING ON RUBBER PORTION OF SEAL TO METAL PORTION OF SEAL.						2	G	7	2 	4U				H10SW 					 
1995022100105	19950221	00105	SW 	1995	2	21	HEEA954086 	1	19950109	G	6410	206010765001	BEARING 		206011810135	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y	906 			AFS6908	45751				PAINT PEELING OFF BLADES. BLADE S/N CS6278 & CS6296, T.T. 906:40. INBOARD BEARINGS CRACKED. COMPLY WITH 206L-94-TBD. 	SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995022100106	19950221	00106	SW 	1995	2	21	HEEA954105 	1	19950102	G	6520	206340103101	SEAL 			BELL 	206 	206L 	1181522	SW 										T/R GR BOX	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	7074W	1092 				52033				GEARBOX LEAKING OIL.						1	G	7	1 	3U				H2SW 					 
1995022100107	19950221	00107	SW 	1995	2	21	HEEA954106 	1	19950102	G	6420	NAS14437P	WASHER 			BELL 	206 	206L 	1181522	SW 										T/R GR BOX	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W	1092 				52033				REMOVED FOR GEARBOX SEAL REPLACEMENT.						1	G	7	1 	3U				H2SW 					 
1995022100108	19950221	00108	SW 	1995	2	21	HEEA954107 	1	19950102	G	6420	206040420001	SPACER 			BELL 	206 	206L 	1181522	SW 										T/R GR BOX	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W	1092 				52033				REMOVED WITH GEARBOX SEAL FOR LEAKING.						1	G	7	1 	3U				H2SW 					 
1995022100109	19950221	00109	SW 	1995	2	21	HEEA954112 	1	19950108	G	6220	222310460103	BEARING 			BELL 	230 	230 	1182149	SW 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	1836 				23009				YELLOW M/R P/C LINK TRUNNION BEARING WORN; MAKING A BLACK PASTE.						1	G	7	2 	3U			NC	H9SW 					 
1995022100110	19950221	00110		1995	2	21	HEEA954117 	4	19950111	G	2211	4033089901	COMPUTER 		FZ702 	BELL 	214 	214ST 	1182106	SW 										AUTO FLIGHT	FAILS TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5748M					28102				FAILS SPERRY SST TEST. PART RECEIVED WITH N5748M ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100111	19950221	00111	EU 	1995	2	21	HEEA954164 	1	19950105	G	3213	1055000134	SKID PROTECTIVE 			BOLKMS	105 	BO105S 	5626006	EU 										SKID	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	105WK	1652 				S812				WORN SKID UNITS.						1	G	7	2 	3U				H3EU 					 
1995022100112	19950221	00112	SW 	1995	2	21	HEEA954166 	1	19950111	G	7714	214175251107	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										TRIPLE TACH	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				NO. 2 NEEDLE INOPERATIVE.						2	G	7	2 	4U				H10SW 					 
1995022100113	19950221	00113	SW 	1995	2	21	HEEA954167 	1	19950120	G	6330	222331618105	ISOLATION MOUNT 			BELL 	230 	230 	1182149	SW 										M/R XMSN	SEPARATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	407 				23009				ELASTOMERIC BEARING SEPARATED.						1	G	7	2 	3U			NC	H9SW 					 
1995022100114	19950221	00114	SW 	1995	2	21	HEEA954168 	1	19950120	G	6720	222312702101	PITCH LINKS 			BELL 	230 	230 	1182149	SW 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	140 				23009				BEARING WORN BEYOND LIMITS.						1	G	7	2 	3U			NC	H9SW 					 
1995022100115	19950221	00115	SW 	1995	2	21	HEEA954169 	1	19950120	G	6720	222312702101	PITCH LINKS 			BELL 	230 	230 	1182149	SW 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	169 				23009				BEARING WORN BEYOND LIMITS.						1	G	7	2 	3U			NC	H9SW 					 
1995022100116	19950221	00116	SW 	1995	2	21	HEEA954171 	1	19950120	G	6220	206010110105	WASHER 		206011100159	BELL 	206 	206L 	1181522	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7077B	1188 			A541	52037				EXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO BE DETERIORATED. SCRAPPED LOCALLY. APPLIED LOWER TORQUE ON ADJUSTING SCREWS	 AND LOWER PRELOAD ON THRUST PLUGS.					1	G	7	1 	3U				H2SW 					 
1995022100117	19950221	00117	SW 	1995	2	21	HEEA954172 	1	19950101	G	3320	1009521	READING LIGHT 			BELL 	206 	206L 	1181522	SW 										AFT CABIN	BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	62127	1654 				52023				AFT PASSENGER OVERHEAD LIGHT LENS ASSEMBLY BROKEN.						1	G	7	1 	3U				H2SW 					 
1995022100118	19950221	00118	SW 	1995	2	21	HEEA954173 	1	19950113	G	5610	214031012104	WINDSHIELD 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	SEPARATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				WINDSHIELD SEPARATED. RECEIVED WITH AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100119	19950221	00119	SW 	1995	2	21	HEEA954174 	1	19950113	G	3320	204075527101	LIGHT ASSY 			BELL 	214 	214ST 	1182106	SW 										CABIN	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				LENS CRACKED. RECEIVED ON AIRCRAFT 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100120	19950221	00120	SW 	1995	2	21	HEEA954175 	1	19950113	G	7603	214060327101	CONTROL CABLE 			BELL 	214 	214ST 	1182106	SW 										ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				CABLE RATCHETY. RECEIVED ON AIRCRAFT N5748M ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100121	19950221	00121	SW 	1995	2	21	HEEA954176 	1	19950110	G	7712	222375077111	TRANSMITTER 			BELL 	214 	214ST 	1182106	SW 										ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				PEGS NEEDLE ON INDICATOR. TRANSMITTER RECEIVED ON AIRCRAFT N5748M ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100122	19950221	00122	SW 	1995	2	21	HEEA954177 	1	19950113	G	3340	209175309001	SHOCKMOUNT ASSY 			BELL 	214 	214ST 	1182106	SW 										LIGHT ASSY	TORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				TORN. PART RECEIVED WITH N5748M ON 12-26-94. AIRCRAFT IN WARRANTY FOR 500 HOUR HOURS OR 6 MONTHS.						2	G	7	2 	4U				H10SW 					 
1995022100123	19950221	00123	SW 	1995	2	21	HEEA954180 	1	19950103	G	6220	214010435003	BEARING 			BELL 	214 	214ST 	1182106	SW 										M/R	COVER MISSING 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5748M					28102				DUST COVERS MISSING. RECEIVED ON N5748M ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100124	19950221	00124	SW 	1995	2	21	HEEA954181 	1	19950112	G	6220	3014712	COUPLING 			BELL 	214 	214ST 	1182106	SW 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				CRACKED. RECEIVED ON N5748M ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100125	19950221	00125	SW 	1995	2	21	HEEA954182 	1	19950118	G	2432	S106	BATTERY 			BELL 	214 	214ST 	1182106	SW 										DC SYS	DEAD 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				BATTERIES DEAD. UNITS RECEIVED ON N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100126	19950221	00126	GL 	1995	2	21	HEEA954184 	2	19950121	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50293	683 			CAT34974	S677	CAE836476			ENGINE REMOVED DUE TO COMBUSTION CASE BAFFLE BROKEN AND ERODED 1ST STAGE NOZZLE. UPON INSPECTION OF TURBINE PARTS NOTED	 THE FOLLOWING: MINOR SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995022100127	19950221	00127	SW 	1995	2	21	HEEA954185 	1	19950112	G	7714	214175249101	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				NEEDLE STICKS DURING START AND SHUTDOWN. INDICATOR RECEIVED ON AIRCRAFT N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100128	19950221	00128	SW 	1995	2	21	HEEA954186 	1	19950122	G	6220	206010110105	WASHER 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3892R	1194 			A1280	45594				EXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO BE DETERIORATED. SCRAPPED LOCALLY. APPLIED LOWER TORQUE ON ADJ. SCREWS AND 	LOWER PRELOAD ON THRUST PLUGS.					1	G	7	1 	3U				H2SW 					 
1995022100129	19950221	00129	SW 	1995	2	21	HEEA954187 	1	19950123	G	6410	206010765001	BEARING 		206011810013	BELL 	206 	206B 	1181511	SW 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2275Q	859 			AFS5102	3625				FEATHERING BEARING ONE EACH OUTBOARD DEFECTIVE, ONE EACH OUTBOARD WORN. PAINT PEELING FROM BLADES. ALSO REPLACED 4 EAC	H SLEEVES P/N 206-010-733-003. BLADES S/N CS-6053, T.T. 859:05, BLADES CS-6017, T.T. 859:05. BOTH BLADES WERE RECEIVED	 2-1-94,				1	G	7	1 	3U				H2SW 					 
1995022100130	19950221	00130	SW 	1995	2	21	HEEA954188 	1	19950123	G	6410	206010765001	BEARING 		206011810013	BELL 	206 	206B 	1181511	SW 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2275Q	691 			AFS5102	3625				FEATHERING BEARING ONE EACH OUTBOARD DEFECTIVE, ONE EACH OUTBOARD WORN. PAINT PEELING FROM BLADES. ALSO REPLACED 4 EAC	H SLEEVES P/N 206-010-733-003. BLADES S/N CS-6053, T.T. 859:05, BLADES CS-6017, T.T. 859:05. BOTH BLADES WERE RECEIVED	 2-1-94				1	G	7	1 	3U				H2SW 					 
1995022100131	19950221	00131	EU 	1995	2	21	HEEA954200 	1	19950109	G	7160	CD002792D9	CHECK VALVE ASSY			BOLKMS	117 	BK117B2 	5626013	EU 										INTAKE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	915 				7234				#2 SAND FILTER BLOWER CHECK VALVE DOOR MISSING. #1 SAND FILTER BLOWER DOOR AND HINGE WEARING MOUNT AREA.						1	G	7	2 	3U			NC	H13EU 					 
1995022100132	19950221	00132	EU 	1995	2	21	HEEA954201 	1	19950115	G	3310	704A46814049	GRADUATOR LIGHT 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6097Z	195 				2820				#1 INSTRUMENT LIGHT FUSE BLOWN. #2 INSTRUMENT LIGHT ONLY WORKS GAUGE PANEL LIGHTS, NOT ANY PUSH BUTTONS.						1	G	7	1 	3U				H9EU 					 
1995022100133	19950221	00133	EU 	1995	2	21	HEEA954202 	1	19950108	G	6220	117775P	BALL JOINT 			SNIAS 	350 	AS350B 	8680801	EU 										STARFLEX	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	747 				2771				BEARING WORN AND TEFLON COATING COMING OFF ON INNER RACE.						1	G	7	1 	3U				H9EU 					 
1995022100134	19950221	00134	SW 	1995	2	21	HEEA954203 	1	19950113	G	7110	A23373	STRUT ASSY 			BELL 	214 	214ST 	1182106	SW 										COWLING	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				END LATCH WILL NOT HOLD COWLING PIN SECURELY. RECEIVED ON N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100135	19950221	00135	SW 	1995	2	21	HEEA954204 	1	19950113	G	7110	A23374	STRUT ASSY 			BELL 	214 	214ST 	1182106	SW 										COWLING	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				END LATCH WILL NOT HOLD COWLING PIN SECURELY. RECEIVED ON N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100136	19950221	00136		1995	2	21	HEEA954205 	4	19950102	G	3416	066306405	ALTIMETER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	FRICTION ERROR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				NEEDLE HAS EXCESSIVE FRICTION ERROR.						2	G	7	2 	4U				H10SW 					 
1995022100137	19950221	00137		1995	2	21	HEEA954206 	4	19950102	G	3416	066306405	ALTIMETER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	STICKY 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				NEEDLE HAS A STICKY OPERATION.						2	G	7	2 	4U				H10SW 					 
1995022100138	19950221	00138	SW 	1995	2	21	HEEA954207 	1	19950123	G	5210	214031916101	GAS SPRING ASSY 			BELL 	214 	214ST 	1182106	SW 										DOOR	WEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				WEAK; WILL NOT KEEP DOOR OPEN. INSTALLED ON N5748M, S/N 28102 WHEN RECEIVED AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100139	19950221	00139	SW 	1995	2	21	HEEA954208 	1	19950104	G	6710	206001343001	ELBOW 			BELL 	206 	206L1 	1182107	SW 										CYCLIC	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2246Q					45752				CORROSION BEYOND LIMITS. SCRAPPED ELBOW.						1	G	7	1 	3U				H2SW 					 
1995022100140	19950221	00140	EU 	1995	2	21	HEEA954221 	1	19950107	G	3340	G62504	SEARCH LIGHT 			BOLKMS	117 	BK117B2 	5626013	EU 										FUSELAGE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911LK					7168				LIGHT BULB HOUSING SPINS FREELY AND BULB GOES OUT INTERMITTENTLY ON WAY DOWN. REPLACED WITH SERVICEABLE LIGHT ASSEMBLY.						1	G	7	2 	3U			NC	H13EU 					 
1995022100141	19950221	00141		1995	2	21	HEEA954233 	4	19950109	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5444X					760174				CVR WILL NOT TEST.						1	G	7	2 	3U				H1NE 					 
1995022100142	19950221	00142	SW 	1995	2	21	HEEA954234 	1	19950112	G	6300	60003	TEMPLATES 		206040015103	BELL 	206 	206B 	1181511	SW 										DRIVE SHAFT	OVERTEMP 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3181J	8 			A2000707	3771				OVERTEMP INDICATIONS. OPPOSITE SIDE OF DISC - 2 EACH TEMP PLATES OVERTEMP.						1	G	7	1 	3U				H2SW 					 
1995022100143	19950221	00143		1995	2	21	HEEA954235 	4	19950110	G	2312	069102525	TRANSCEIVER 		KX165 	BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	134AE					7237				NO DISPLAY/WEAK TRANSMITT. VERIFIED PROBLEM. REPLACED F401 (FUSE), REPAIRED. ADJUSTED FREQUENCY AND SIDETONES. BENCH 	CHECK GOOD.					1	G	7	2 	3U			NC	H13EU 					 
1995022100144	19950221	00144		1995	2	21	HEEA954236 	4	19950110	G	2312	064102300	TRANSCIEVER 			BELL 	412 	412 	1182202	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				INOPERATIVE. VERIFIED. FOUND ALL POWER SUPPLY VOLTAGES TO BE BAD. REPLACED TRANSFORMER T101. REPAIRED. ADJUSTED MIC 	GAIN, SIDETONE, AND TRANSMIT COMPRESSOR. BENCH CHECK GOOD..					1	G	7	2 	4U				H4SW 					 
1995022100145	19950221	00145	SW 	1995	2	21	HEEA954237 	1	19950121	G	3340	A469B	LAMP 			BELL 	206 	206L 	1181522	SW 										LIGHTING	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W					52033				BULB BURNT. REPLACED WITH SERVICEABLE BULB.						1	G	7	1 	3U				H2SW 					 
1995022100146	19950221	00146		1995	2	21	HEEA954238 	4	19950107	G	3457	0845000000	SKYNAV 5000 			BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911LK					7168				INTERMITTENTLY DUMPS PROGRAMMED INFORMATION. INSPECTED AND TESTED. FUNCTION CHECKS GOOD.						1	G	7	2 	3U			NC	H13EU 					 
1995022100147	19950221	00147		1995	2	21	HEEA954240 	4	19950114	G	2200	2593996333	TARSYN 333 			BELL 	412 	412 	1182202	SW 										AUTO FLIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2298Z					33077				UNIT KICKS IN PITCH AS REPORTED.						1	G	7	2 	4U				H4SW 					 
1995022100148	19950221	00148	EU 	1995	2	21	HEEA954241 	1	19950115	G	6210	355A11002011	BLADE 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5786D	636 				5113				CRACK IN THE SKIN OF THE LOWER SIDE LOCATED AT STATION 2228MM. THE CRACK STARTS 45MM FROM THE TRAILING EDGE AND EXTENDS	 TO 96MM FROM THE TRAILING EDGE.					1	G	7	2 	3U				H11EU 					 
1995022100149	19950221	00149		1995	2	21	HEEA954242 	4	19950102	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	2149S	3429 				36002				UNIT WILL NOT TEST WITH PILOT/COPILOT SWITCH.						1	G	7	2 	4U				H4SW 					 
1995022100150	19950221	00150		1995	2	21	HEEA954244 	4	19950105	G	3454	066401010	RECEIVER 		KNS81 	BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				NOISE ON ALL FREQUENCIES.						2	G	7	2 	4U				H10SW 					 
1995022100151	19950221	00151	SW 	1995	2	21	HEEA954248 	1	19950116	G	2810	206033099171A	SHELL 			BELL 	206 	206L1 	1182107	SW 										FUEL CELL	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50034					45167				SHELL HAS IMPROPER CONTOUR ALONG LOWER AFT EDGE AND SHORT EDGE DISTANCE ON TOP L/H SIDE. TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW 					 
1995022100152	19950221	00152	EU 	1995	2	21	HEEA954249 	1	19950112	G	7722	50061036	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT TOT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3535T					S113				TOT CANNOT BE CALIBRATED. (NOT ENOUGH ADJUSTMENT) TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H3EU 					 
1995022100153	19950221	00153	EU 	1995	2	21	HEEA954250 	1	19950112	G	7722	TM42739	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT TOT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3535T					S113				NEEDLE STICKS AT 840 DEGREES CELSIUS AND ABOVE.						1	G	7	2 	3U				H3EU 					 
1995022100154	19950221	00154	NE 	1995	2	21	HEEA954251 	1	19950123	G	5321	7620402002043	PANELS 			SKRSKY	S76 	S76A 	8143006	NE 										LT FLOOR	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4253S					760035				CORROSION ON OUTER SURFACE OF FLOOR PANEL IN SEVERAL AREAS.						1	G	7	2 	3U				H1NE 					 
1995022100155	19950221	00155	SW 	1995	2	21	HEEA954252 	1	19950126	G	3310	4596	LAMP 			BELL 	206 	206L 	1181522	SW 										LIGHTING	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	62127					52023				LAMP BURNED OUT. REPLACED WITH SERVICEABLE LAMP.						1	G	7	1 	3U				H2SW 					 
1995022100156	19950221	00156		1995	2	21	HEEA954253 	4	19950123	G	3460	0845000000	SKYNAV 5000 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911NC					7026				NOT HOLDING PROGRAMMABLE WAYPOINTS. ENTERED EXTRA WAYPOINTS INTO USER WAYPOINTS. ENTERED "DIRECT TO" FUNCTION AND PULLE	D POWER PLUG FROM TEST PANEL. AFTER TURNING UNIT BACK ON, FOUND UNIT DROPPED ALL USER WAYPOINTS.					1	G	7	2 	3U				H13EU 					 
1995022100157	19950221	00157	EU 	1995	2	21	HEEA954254 	1	19950112	G	2840	81141010010	TRANSMITTER 			AEROSP	AS355 	AS355F1 	8680810	EU 										FUEL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y					5141				NO OUTPUT. TIME SINCE REPAIR 31:10.						1	G	7	2 	3U				H11EU 					 
1995022100158	19950221	00158		1995	2	21	HEEA954255 	4	19950103	G	3450	066401018	RNAV 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				VOR/LOC OFF.						2	G	7	2 	4U				H10SW 					 
1995022100159	19950221	00159		1995	2	21	HEEA954256 	4	19950124	G	3453	4530103	RECEIVER 		ARNAV21 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31801					51074				WILL NOT HOLD ANTENNA SIGNAL.						1	G	7	1 	3U				H2SW 					 
1995022100160	19950221	00160		1995	2	21	HEEA954259 	4	19950122	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	1545X	2610 				760050				WILL NOT TEST AUDIO-NO 400 HZ TONE. FIVE YEAR INSPECTION DUE 8/96.						1	G	7	2 	3U				H1NE 					 
1995022100161	19950221	00161		1995	2	21	HEEA954260 	4	19950124	G	3451	066107001	TRANCEIVER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	INOP 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	9190F					S668				UPON INSTALLATION IN AIRCRAFT FOUND NEW UNIT INOPERATIVE. NO TRANSMIT. FOUND NO SEARCH ON TRACK. TROUBLESHOT AND REPLA	CED C625 (CAP).					1	G	7	2 	3U				H3EU 					 
1995022100162	19950221	00162	SW 	1995	2	21	HEEA954262 	1	19950118	G	8010	214175171101	RELAY 			BELL 	214 	214ST 	1182106	SW 										START SYS	FAULTY 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				STARTER NOT GOING INTO SERIES..						2	G	7	2 	4U				H10SW 					 
1995022100163	19950221	00163	SW 	1995	2	21	HEEA954263 	1	19950128	G	6240	214074280105	DETECTOR RPM 			BELL 	214 	214ST 	1182106	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				LOW ROTOR RPM WON'T STAY MUTED BELOW 80%. RECEIVED INSTALLED ON AIRCRAFT N5748M ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100164	19950221	00164		1995	2	21	HEEA954264 	4	19950111	G	2340	A3016W	INTERPHONE BOX 			BELL 	214 	214ST 	1182106	SW 										COMM SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				WHEN COMM CONTROL IS PLUGGED INTO HARNESS IN CABIN EITHER 3RD OR 4TH STATION , IT CAUSES TO SQUELCH LIGHT ON THE C117 CO	NTROL OF THE FF40 SYSTEM TO ILLUMINATE. COMM 4 IS THE POSITION BEING USED FOR THE FF40 SYSTEM					2	G	7	2 	4U				H10SW 					 
1995022100165	19950221	00165	SW 	1995	2	21	HEEA954272 	1	19950109	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6610Y	850 			CS5239	51419				CRACKED INBOARD BEARINGS . ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N AFS-5499, T.	T. 2483:00. SCRAPPED BEARINGS AND SLEEVES LOCALLY. BLADE S/N CS5239 & CS4665					1	G	7	1 	3U				H2SW 					 
1995022100166	19950221	00166	SW 	1995	2	21	HEEA954273 	1	19950109	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6610Y	1474 			CS5239	51419				CRACKED OUTBOARD BEARINGS . ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N AFS-5499, 	T.T. 2483:00. SCRAPPED BEARINGS AND SLEEVES LOCALLY. BLADE S/N CS5239 & CS4665					1	G	7	1 	3U				H2SW 					 
1995022100167	19950221	00167	SW 	1995	2	21	HEEA954274 	1	19950116	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2251A	483 			CS6536	45755				CRACKED INBOARD AND OUTBOARD BEARING. ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N AF	S-5896, T.T. 2232:00. SCRAPPED BEARINGS AND SLEEVES LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995022100168	19950221	00168	SW 	1995	2	21	HEEA954275 	1	19950120	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206B3 	1181506	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268W	1826 			CS3073	3606				CRACKED INBOARD BEARINGS. ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N AFS-5985, T.T	. 1582:35. SCRAPPED BEARINGS AND SLEEVES LOCALLY. BLADE S/N CS3073 & CS3064					1	G	7	1 	3U				H2SW 					 
1995022100169	19950221	00169	SW 	1995	2	21	HEEA954276 	1	19950120	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206B3 	1181506	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268W	1967 			CS30733064	3606				CRACKED OUTBOARD BEARINGS. ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N AFS-5985, T.	T. 1582:35. SCRAPPED BEARINGS AND SLEEVES LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995022100170	19950221	00170	SW 	1995	2	21	HEEA954277 	1	19950124	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8593X	634 			CS42354315	51509				CRACKED INBOARD (2 EACH) AND OUTBOARD BEARING (1 EACH) . ALSO REPLACED THREE EACH SLEEVES P/N 206-010-733-003. REM	OVED FROM T/R HUB S/N AFS-6091, T.T. 2040:20. SCRAPPED BEARINGS AND SLEEVES LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995022100171	19950221	00171	SW 	1995	2	21	HEEA954278 	1	19950124	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8593X	2040 			CS4315	51509				CRACKED OUTBOARD BEARING (1 EACH) . ALSO REPLACED ONE EACH SLEEVE P/N 206-010-733-003. REMOVED FROM T/R HUB S/N AF	S-6091, T.T. 2040:20. SCRAPPED BEARINGS AND SLEEVES LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995022100172	19950221	00172	SW 	1995	2	21	HEEA954279 	1	19950126	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3116P	736 			CS60916054	51530				CRACK INBOARD BEARINGS (2 EA). ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N HB213, 	T.T. 3565:50. SCRAPPED BEARINGS AND SLEEVES LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995022100173	19950221	00173	SW 	1995	2	21	HEEA954280 	1	19950126	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3116P	1074 			CS60916054	51530				CRACKED OUTBOARD BEARINGS (2 EA) ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N HB21	3, T.T. 3565:50. SCRAPPED BEARINGS AND SLEEVES LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995022100174	19950221	00174	SW 	1995	2	21	HEEA954281 	1	19950127	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5737T	981 			CS54805518	45454				CRACKED INBOARD AND OUTBOARD BEARINGS (2 EA) ALSO REPLACED FOUR EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/	R HUB S/N AFS6845, T.T. 981:20. SCRAPPED BEARINGS AND SLEEVES LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995022100175	19950221	00175	EU 	1995	2	21	HEEA954282 	1	19950128	G	6310	4638202007	CLUTCH 		4638001004 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	105WK	1725 			1273	S812				INNER CAGE WORN BEYOND LIMITS.						1	G	7	2 	3U				H3EU 					 
1995022100176	19950221	00176	EU 	1995	2	21	HEEA954283 	1	19950119	G	7810	1176513502	EJECTOR DUCT 			BOLKMS	117 	BK117B2 	5626013	EU 										RT EXH	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	925 				7234				R/H EXHAUST EJECTOR WORN AT CUSHION MOUNT AREAS.						1	G	7	2 	3U			NC	H13EU 					 
1995022100177	19950221	00177	EU 	1995	2	21	HEEA954284 	1	19950120	G	7810	1176506301	BRACKET UPPER 			BOLKMS	117 	BK117B2 	5626013	EU 										RT EJECTOR	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	927 				7234				BRACKET CRACKED AT R/H EJECTOR CUSHION MOUNTS.						1	G	7	2 	3U			NC	H13EU 					 
1995022100178	19950221	00178	EU 	1995	2	21	HEEA954285 	1	19950120	G	7722	1179405107	INDICATOR 			BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT TOT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	927 				7234				NEEDLE STICKS ON START WHEN IDLED FOR OVER 8 HOURS APPROXIMATELY.						1	G	7	2 	3U			NC	H13EU 					 
1995022100179	19950221	00179	EU 	1995	2	21	HEEA954286 	1	19950120	G	7810	1176506401	BRACKET 			BOLKMS	117 	BK117B2 	5626013	EU 										RT EJECTOR	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	927 				7234				BRACKET CRACKED AT RH EJECTOR CUSHION MOUNTS.						1	G	7	2 	3U			NC	H13EU 					 
1995022100180	19950221	00180	EU 	1995	2	21	HEEA954287 	1	19950106	G	7400	355A72302300	SENSOR ASSY 			AEROSP	AS355 	AS355F1 	8680810	EU 										AUTO RELIGHT	BROKEN PLUG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6040U					5474				AUTO RELIGHT COMES ON DURING FLIGHT. FOUND BROKEN CANNON PLUG.						1	G	7	2 	3U				H11EU 					 
1995022100181	19950221	00181		1995	2	21	HEEA954289 	4	19950110	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2764F					45279				IDENT AND REPLY LIGHT WEAK. REPLACED V301 PHOTOCELL THAT WAS INOPERATIVE. ALSO REPLACED WEAK CAVITY OSCILLATOR V101, DE	TERIORATED RESISTOR R477 AND INSTALLED Q415 HEAT SINK. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995022100182	19950221	00182		1995	2	21	HEEA954290 	4	19950110	G	3416	8140B15LW	ALTIMETER 	AEROMECH 		SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	CASE LEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										UNIT HAS EXCESSIVE CASE LEAK AT KOLLSMAN KNOB (WHEN ADJUSTED TO 29.98)						1	G	7	2 	3U				H1NE 					 
1995022100183	19950221	00183	EU 	1995	2	21	HEEA954291 	1	19950112	G	6220	117775P	BALL JOINT 			AEROSP	AS355 	AS355F1 	8680810	EU 										STARFLEX	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5785Y					5105				BALLJOINT ON BLUE BLADE HAS LINING WORN OFF OF THE INSIDE DIAMETER. REPLACED WITH SERVICEABLE BALL JOINT.						1	G	7	2 	3U				H11EU 					 
1995022100184	19950221	00184		1995	2	21	HEEA954294 	4	19950111	G	2312	4000103000	TRANSCEIVER 		RT45 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7161J					S834				TRANSCEIVER HAS TO WARM UP BEFORE UNIT COMES ON.						1	G	7	2 	3U				H3EU 					 
1995022100185	19950221	00185	SW 	1995	2	21	HEEA954296 	1	19950114	G	7810	206064300005	EXHAUST ASSY 			BELL 	206 	206L1 	1182107	SW 										ENGINE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y					45751				ON DAILY INSPECTION, FOUND EXHAUST STACK CRACKED IN THE MIDDLE OF THE BACK SIDE. REPLACED WITH SERVICEABLE EXHAUST STACK	.					1	G	7	1 	3U				H2SW 					 
1995022100186	19950221	00186	EU 	1995	2	21	HEEA954297 	1	19950119	G	6520	350A33200403	SPIDER 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	WORN BEARING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	808 				2771				BEARING (350A33-1097-00) WORN.						1	G	7	1 	3U				H9EU 					 
1995022100187	19950221	00187	NE 	1995	2	21	HEEA954298 	1	19950107	G	6321	7665009803103	POWER PAC 			SKRSKY	S76 	S76A 	8143006	NE 										ROTOR BRAKE HYD	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122G					760232				WITH THE POWER PAC IN THE "ON" POSITION ROTOR BRAKE CYCLES CONTINUOUSLY. REPLACED POWER PACK.						1	G	7	2 	3U				H1NE 					 
1995022100188	19950221	00188	SW 	1995	2	21	HEEA954300 	1	19950201	G	6220	206010110105	WASHER 		206011100149	BELL 	206 	206B3 	1181506	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268W	905 			A807	3606				EXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO DETERIORATE. PARTS SCRAPPED LOCALLY. APPLIED TORQUE ON ADJUSTING SCREWS AND	 LOWERED PRELOAD ON THRUST PLUGS.					1	G	7	1 	3U				H2SW 					 
1995022100189	19950221	00189	GL 	1995	2	21	HEEA954303 	2	19950206	G	7230	230052712	SPLINE ADAPTER 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					COMPRESSOR	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	31217	266 			CAC90779	760229	CAE890460S			ENGINE REMOVED DUE TO N1 SHAFTING INSPECTION AND 4 EACH COMPRESSOR MOUNT STUDS PULLED. UPON INSPECTION OF COMPRESSOR PA	RTS NOTED THE FOLLOWING: WEAR ON THE SPLINE ADAPTER RETAINING RING GROOVE AFT FACE. INTERFERENCE FIT BETWEEN I.D. OF S	PLINEADAPTER GROOVE AND RETAINING RING O.D. WAS .016" AT TIME OF NEW PART INSTALLATION. INSTALLED NEW SPLINE ADAPTER.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995022100190	19950221	00190	GL 	1995	2	21	HEEA954304 	2	19950206	G	7230	23034784	GEARSHAFT 		6890550 	BELL 	206 	206B3 	1181506	SW 	ALLSN 	250C 	250C20B 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22751	977 			CAC41827	3627	CAE836413			ENGINE REMOVED DUE TO COMPRESSOR OVERHAUL AND TURBINE 1750 HOUR INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED T	HE FOLLOWING: STEP WEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEA	RSHAFT. AFA# 17920A.				1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995022100191	19950221	00191	GL 	1995	2	21	HEEA954305 	2	19950206	G	7230	23008090	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122G	915 			CAC90857	760232	CAE890735S			ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMI	TS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEARSHAFT. SEE MMIR# 4306 FOR ADAPTER W	HICH WAS ALSO REPLACED.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995022100192	19950221	00192	GL 	1995	2	21	HEEA954306 	2	19950206	G	7230	230052711	SPLINE ADAPTER 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					COMPRESSOR	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122G	915 			CAC90857	760232				ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMI	TS ON SPLINE ADAPTER INNER SPLINES. INSTALLED NEW ADAPTER. SEE MMIR# 4305 FOR SPUR ADAPTER GEARSHAFT WHICH WAS ALSO	 REPLACED.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995022100193	19950221	00193	SW 	1995	2	21	HEEA954307 	1	19950206	G	6240	222375021113	INDICATOR 			BELL 	230 	230 	1182149	SW 										ROTOR	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	1866 				23009				ROTOR NEEDLE WORKS INTERMITTENTLY, STAYS ON ZERO ON FIRST START OF THE DAY.						1	G	7	2 	3U			NC	H9SW 					 
1995022100194	19950221	00194	SW 	1995	2	21	HEEA954308 	1	19950206	G	2432	214175379103	BATTERY CHARGER 			BELL 	214 	214ST 	1182106	SW 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				TROUBLESHOOTING CROSS STARTING PROBLEM. PART RECEIVED INSTALLED ON N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100195	19950221	00195	SW 	1995	2	21	HEEA954312 	1	19950206	G	2510	501719405	SEAT BELT 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				UNITS SENT FOR REWEB. BELTS RECEIVED WITH N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022100196	19950221	00196	SW 	1995	2	21	HEEA954313 	1	19950206	G	6220	206011111001	BEARING ASSY 			BELL 	206 	206L3 	1182108	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										NO INNER RACE IN COMPLETE ASSEMBLY.						1	G	7	1 	3U				H2SW 					 
1995022100197	19950221	00197		1995	2	21	HEEA954315 	4	19950206	G	2312	064102300	TRANSCIEVER 			BELL 	412 	412 	1182202	SW 										COCKPIT VHF	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				RECEIVES AND TRANSMITS WITH A SQUEAL.						1	G	7	2 	4U				H4SW 					 
1995022100198	19950221	00198	SW 	1995	2	21	HEEA954316 	1	19950206	G	7722	206375006101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5745N					45489				OVERTEMP LIGHT WILL NOT LIGHT AT 930 DEGREES.						1	G	7	1 	3U				H2SW 					 
1995022100199	19950221	00199		1995	2	21	HEEA954317 	4	19950206	G	3453	4530103	LORAN 		ARNAV21 	AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5785Y					5105				STATION OFF TWO MILES.						1	G	7	2 	3U				H11EU 					 
1995022100200	19950221	00200		1995	2	21	HEEA954318 	4	19950206	G	3453	4530103	LORAN 		ARNAV21 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31801					51074				LORAN FLASHES OSCILLATOR WARNING.						1	G	7	1 	3U				H2SW 					 
1995022100201	19950221	00201		1995	2	21	HEEA954319 	4	19950206	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2271V					3615				NO ACTIVITY FROM LIGHT AND LIGHT OPERATIONAL. NO ACTIVITY WHEN LANDING LIGHT CYCLED. FOUND UNIT INOPERATIVE. REPLACED 	OPEN TRANSISTOR Q415. REPAIRED. ALSO REPLACED CRACKED FACEPLATE, BAD PHOTOCELL V301, DETERIORATED RESISTOR R477 AND PU	T HEATSINK BEHIND Q415 FOR MOD 6. REPAIRED.				1	G	7	1 	3U				H2SW 					 
1995022100202	19950221	00202		1995	2	21	HEEA954320 	4	19950206	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	134AE					7237				REPLY LIGHT WILL NOT COME ON; INTERMITTENT. REPLACED PHOTOCELL V301. REPAIRED.						1	G	7	2 	3U			NC	H13EU 					 
1995022100203	19950221	00203	SW 	1995	2	21	HEEA954321 	1	19950206	G	5311	206032308103S	FRAME 			BELL 	206 	206L1 	1182107	SW 										TAIL BOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5007N					45184				T/B FRAME CRACKED L/H MOUNT AREA, LONGERON L/H AND L/H CASTING CRACKED AT OUTBOARD RIVET ON FLANGE AND CASTING. REPLACED	 FRAME AND LONGERON P/N 206-031-314-037S, AND FITTING P/N 206-031-392-101S.					1	G	7	1 	3U				H2SW 					 
1995022100204	19950221	00204	EU 	1995	2	21	HEEA954323 	1	19950206	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5418A	6973 				S800				NOSE AND NECK SHELL CRACKED NEAR THE CUFF AREA.						1	G	7	2 	3U				H3EU 					 
1995022100205	19950221	00205	EU 	1995	2	21	HEEA954324 	1	19950206	G	6210	10587214	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5418A	9396 				S800				NOSE AND NECK SHELL CRACKED NEAR THE CUFF AREA. THE INBOARD LEADING EDGE STRIP HAS SOME SEPARATION BUT WITHIN LIMITS.						1	G	7	2 	3U				H3EU 					 
1995022100206	19950221	00206	EU 	1995	2	21	HEEA954325 	1	19950209	G	3310	1179203103	CONTROL UNIT 			BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	134AE	1037 				7237				LIGHTS INTERMITTENTLY.						1	G	7	2 	3U			NC	H13EU 					 
1995022100207	19950221	00207	SW 	1995	2	21	HEEA954326 	1	19950209	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M	1049 				28102				START TIME SLOW. APPROXIMATELY 45-50 SECONDS. AFTER CHARGE, DOWN TO 20-25 SECONDS. RECEIVED INSTALLED ON N5748M ON 12-	26-94.					2	G	7	2 	4U				H10SW 					 
1995022100208	19950221	00208	EU 	1995	2	21	HEEA954328 	1	19950210	G	7170	454C01	VALVE 			BOLKMS	105 	BO105S 	5626006	EU 										DRAIN	LEAKING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	105WK	1727 				S812				VALVES LEAKING.						1	G	7	2 	3U				H3EU 					 
1995022100209	19950221	00209	EU 	1995	2	21	HEEA954329 	1	19950210	G	2435	150SG122Q	GENERATOR 			SNIAS 	350 	AS350B 	8680801	EU 										START/GEN	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	504 				2777				STARTER GENERATOR INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995022100210	19950221	00210		1995	2	21	HEEA954330 	4	19950210	G	2350	PA1120NVPHI	HEADSET 			SKRSKY	S76 	S76A 	8143006	NE 										MIC ATTACH	BROKEN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3122G					760232				MICROPHONE ATTACH POINT BROKEN. REPLACED WITH SERVICEABLE HEADSET.						1	G	7	2 	3U				H1NE 					 
1995022100211	19950221	00211	EU 	1995	2	21	HEEA954331 	1	19950210	G	6310	4638202007	CLUTCH 		4638001001 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	91070	1109 			748	S145				UPON 1200 HOUR INSPECTION FOUND SPRAG RETAINER CRACKED AND WORN BEYOND LIMITS. REPLACED WITH SERVICEABLE CLUTCH ASSEMBLY	.					1	G	7	2 	3U				H3EU 					 
1995022100212	19950221	00212		1995	2	21	HEEA954332 	4	19950210	G	3454	066400700	RECEIVER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31217					760229				RECEIVER UNRELIABLE.						1	G	7	2 	3U				H1NE 					 
1995022100213	19950221	00213		1995	2	21	HEEA954333 	4	19950210	G	3416	5035P2P44	ALTIMETER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ENCODER	ERROR 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	9190F					S668				ENCODER IS 80 FEET OFF AT 16,000 FEET AND NEEDLE HAS EXCESSIVE FRICTION ERROR. TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H3EU 					 
1995022100214	19950221	00214		1995	2	21	HEEA954334 	4	19950210	G	3454	071105404	CONTROL 		KFS5608 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546K					760082				THIRD NUMBER WILL NOT LINE UP HARD TO TURN.						1	G	7	2 	3U				H1NE 					 
1995022100215	19950221	00215		1995	2	21	HEEA954335 	4	19950210	G	3442	MI585200	TRANSCEIVER 			SKRSKY	S76 	S76A 	8143006	NE 										RADAR	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2743E					760155				UNIT SHUTS DOWN DURING WARM UP PERIOD.						1	G	7	2 	3U				H1NE 					 
1995022100216	19950221	00216		1995	2	21	HEEA954336 	4	19950210	G	3457	0845000000	SKYNAV 5000 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT GPS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911NC					7026				AUTO DIM NOT WORKING, NOT HOLDING PROGRAMMABLE WAYPOINTS AND KEEPS CYCLING THROUGH SELF TEST. TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H13EU 					 
1995022100217	19950221	00217		1995	2	21	HEEA954337 	4	19950210	G	2370	9806019001	CVR 			BEECH 	200 	200CBEECH 	1152926	CE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	500PH	2105 				BL29				CVR WILL NOT TEST.						1	L	7	2 	4T				A24CE 					 
1995022100218	19950221	00218	NE 	1995	2	21	HEEA954338 	2	19950210	G	7323	25249994	GOVERNOR 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					TURBINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2014K	12919				33020				UNABLE TO GET NG TOPPING SET.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995022400212	19950224	00212	GL 	1995	2	24	HEEA954339 	2	19950214	G	7230	23008090	GEARSHAFT 		23033193 	BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					SPUR ADAPTER	STEP WEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8587X	823 			CAC90071	51464	CAE890177			ENGINE REMOVED DUE TO 1750 HOUR OVERHAUL AND INSPECTION. UPON INSPECTTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STE	PWEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEARSHAFT.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995022400213	19950224	00213	GL 	1995	2	24	HEEA954340 	1	19950214	G	6710	206062721109	ACTUATOR 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	21240	69 				45647				INTERMITTENT OPERATION. INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND WATER IN UNIT. CLEANED AND REPLACED O-RINGS. AS	SEMBLED, TESTED AND RETURNED LINEAR ACTUATOR TO SERVICE.					1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995022400214	19950224	00214	SW 	1995	2	24	HEEA954341 	1	19950214	G	2822	214066298101	FUEL PUMP 			BELL 	214 	214ST 	1182106	SW 										FUEL SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										INCOMPLETE ASSEMBLY, RECEIVED WITH NO CARTRIDGE.						2	G	7	2 	4U				H10SW 					 
1995022400215	19950224	00215	NE 	1995	2	24	HEEA954342 	2	19950214	G	7412	9560136490	IGNITER 			SNIAS 	350 	AS350B 	8680801	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					ENGINE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	877 				2771	9281			IGNITER SOLID STATE CRATERED AND LEAD FRAYED. PART SCRAPPED LOCALLY.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995022400216	19950224	00216	SW 	1995	2	24	HEEA954343 	1	19950214	G	6420	214011819101	BEARING 		214011801117	BELL 	214 	214ST 	1182106	SW 										T/R HUB	UNBONDED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	UHLHQ	664 			A53	28101				TEFLON UNBONDED IN BEARING.						2	G	7	2 	4U				H10SW 					 
1995022400217	19950224	00217	NE 	1995	2	24	HEEA954344 	2	19950214	G	7250	3017600	ENGINE 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					POWER SECTION	MALFUNCTION 	E			HEEA	K				NONE 				R	M		PARTIAL RPM/PWR LOSS 	OVER TEMP 		IN	INSP/MAINT 	1			SW	03	3911L	12584				33023				COMPRESSOR STALL FOLLOWED BY RISE IN ITT TO NEAR 900 DEGREES N1 ABOUT 80-84%.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995022400218	19950224	00218	NE 	1995	2	24	HEEA954345 	2	19950214	G	7210	3024780	GEARBOX 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					COMBINING BOX	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3911L	10673				33023				MAKING METAL ON #1 SIDE.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995033100143	19950331	00143	NE 	1995	3	31	HEEA954346 	2	19950214	G	7261	0292005220	OIL RETURN 			SNIAS 	350 	AS350B 	8680801	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					TURBINE	BLOCKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	846 				2653				FREE TURBINE OIL RETURN RESTRICTED.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995022400219	19950224	00219	EU 	1995	2	24	HEEA954347 	1	19950214	G	3340	A7151	LAMP 			BOLKMS	117 	BK117B2 	5626013	EU 										LANDING LIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	847 				7234				FIXED LANDING LIGHT HOUSING ASSEMBLY CRACKED AND BROKEN AT MOUNTING BRACKET.						1	G	7	2 	3U			NC	H13EU 					 
1995022400220	19950224	00220	EU 	1995	2	24	HEEA954349 	1	19950214	G	7920	174000103	FILTER ASSEMBLY 			BOLKMS	105 	BO105S 	5626006	EU 										BY PASS	BUTTON POPS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7136J	267 				S830				BY-PASS BUTTON POPS OUT AFTER RUNNING AIRCRAFT APPROXIMATELY 5 MINUTES.						1	G	7	2 	3U				H3EU 					 
1995022400221	19950224	00221		1995	2	24	HEEA954350 	4	19950214	G	3420	6220876001	VIR 30AGM 			BEECH 	200 	200CBEECH 	1152926	CE 										CO PILOT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	500PH					BL29				WILL NOT RUN CO-PILOTS HSI. GIVES WRONG SIGNAL. TIME SINCE REPAIR 1298:25.						1	L	7	2 	4T				A24CE 					 
1995022400222	19950224	00222	NE 	1995	2	24	HEEA954351 	1	19950214	G	6320	7635109023101	LINER 			SKRSKY	S76 	S76A 	8143006	NE 										M/R GR BOX	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										NEW PART RECEIVED MISMANUFACTURED. ID OF LINER IS OUT OF LIMITS 6.222 AND 6.230.						1	G	7	2 	3U				H1NE 					 
1995022400223	19950224	00223		1995	2	24	HEEA954352 	4	19950214	G	2562	ELT910	ELT 	NARCO 		BELL 	206 	206L3 	1182108	SW 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3207Q	2415 				50540				TRIGGERED AND WOULD NOT RESET. TIME SINCE REPAIR 741:30.						1	G	7	1 	3U				H2SW 					 
1995022400224	19950224	00224	EU 	1995	2	24	HEEA954353 	1	19950214	G	3340	A413AHDADF1428	POWER SUPPLY 			BOLKMS	105 	BO105S 	5626006	EU 										STROBE	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	54191					S804				INOPERATIVE. TIME SINCE REPAIR 21:15.						1	G	7	2 	3U				H3EU 					 
1995022400225	19950224	00225	SW 	1995	2	24	HEEA954354 	1	19950214	G	2810	206064611001	CELL 			BELL 	206 	206L1 	1182107	SW 										FILLER NECK	LEAKAGE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5753D					45529				PIN-HOLE LEAKAGE AND UNBONDED FILLER NECK FLANGE DUE TO CORROSION.						1	G	7	1 	3U				H2SW 					 
1995022400226	19950224	00226	CE 	1995	2	24	HEEA954355 	1	19950214	G	7334	1013890233	TRANSDUCER 			BEECH 	200 	200CBEECH 	1152926	CE 	PWA 	PT6 	PT6A41 	52043	EA 					FUEL PRESS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	39PH					BL3				ZERO OUTPUT WITH POWER AND PRESSURE APPLIED.						1	L	7	2 	4T	4	T		A24CE 	E4EA				 
1995022400227	19950224	00227		1995	2	24	HEEA954356 	4	19950214	G	3442	MI585200	RADAR RT 	SPERRY 																ANTENNA	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										WITH ONE VOLT RMS PITCH, ANT PITCHES 28 DEGREES INSTEAD OF 20 DEGREES, ROLL SAME.																			 
1995022400228	19950224	00228	SW 	1995	2	24	HEEA954358 	1	19950214	G	2824	L88010491	VALVE 			BELL 	412 	412 	1182202	SW 										FUEL SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				CYCLES ALL THE TIME (FUEL VALVE ONLY).						1	G	7	2 	4U				H4SW 					 
1995030300530	19950303	00530	SW 	1995	3	3	HEEA954359 	1	19950214	G	2824	L88010491	VALVE 			BELL 	412 	412 	1182202	SW 										FUEL SYS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995022400229	19950224	00229	NE 	1995	2	24	HEEA954360 	1	19950214	G	7722	7645001076106	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										TURB TEMP	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				READS 500 DEGREES LOW.						1	G	7	2 	3U				H1NE 					 
1995022400230	19950224	00230	EU 	1995	2	24	HEEA954362 	1	19950214	G	7722	50061036	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										EXH TEMP	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3535T	1 				S113				ERRATIC READING.						1	G	7	2 	3U				H3EU 					 
1995022400231	19950224	00231	SW 	1995	2	24	HEEA954364 	1	19950214	G	5260	FYLM735023	MOTOR ASSY 			BELL 	412 	412 	1182202	SW 										STEP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347					36005				STICKS IN EXTEND AND RETRACT POSITION. VISUALLY INSPECTED BY THE ACCESSORY SHOP. FOUND MOTOR BAD. DEAD SPOT ON ARMAT	URE. UNIT WAS IN SERVICE ONLY 78 DAYS.					1	G	7	2 	4U				H4SW 					 
1995022400232	19950224	00232		1995	2	24	HEEA954365 	4	19950214	G	3457	0845000000	SKYNAV 5000 			BELL 	206 	206L 	1181522	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7074W					52033				UNIT STAYS IN 1982 TEST AND CHECK OPERATION CONSTANTLY. TIME SINCE REPAIR 184:30.						1	G	7	1 	3U				H2SW 					 
1995022400233	19950224	00233	SW 	1995	2	24	HEEA954366 	1	19950214	G	5530	206020113127	FIN 			BELL 	206 	206B 	1181511	SW 										VERT FIN	SEPARATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2277A					3630				SEPARATED AT STINGER AND FIN OVERWEIGHT 17.1 LBS.						1	G	7	1 	3U				H2SW 					 
1995022400234	19950224	00234	EU 	1995	2	24	HEEA954368 	1	19950214	G	6510	1053180301	SHAFT 			BOLKMS	105 	BO105S 	5626006	EU 										T/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4294R					S860				CORROSION ON BEARING SEAL AND SCORING AT SLIDING SLEEVE AREA.						1	G	7	2 	3U				H3EU 					 
1995022400235	19950224	00235	EU 	1995	2	24	HEEA954369 	1	19950214	G	2841	VT42641	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAIN TANK	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	105WK					S812				NO INDICATION ON MAIN TANK SIDE.						1	G	7	2 	3U				H3EU 					 
1995022400236	19950224	00236	EU 	1995	2	24	HEEA954370 	1	19950214	G	5310	D16744101	BRACE 			BOLKMS	105 	BO105S 	5626006	EU 										FUSELAGE	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4302G	1118 				S853				BRACES CORRODED.						1	G	7	2 	3U				H3EU 					 
1995022400237	19950224	00237	EU 	1995	2	24	HEEA954371 	1	19950214	G	2121	420800001	BLOWER 			SNIAS 	350 	AS350B 	8680801	EU 										AIR DIST	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	826 				2653				BLOWER NOT WORKING. MOTOR DOES NOT TURN.						1	G	7	1 	3U				H9EU 					 
1995022400238	19950224	00238		1995	2	24	HEEA954372 	4	19950214	G	2564	214070943108	LIFE RAFT 			BELL 	214 	214ST 	1182106	SW 										SURVIVAL EQUIP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										PHI REQUESTED THAT OUR EQUIPMENT BE BROUGHT UP TO FAR 135 STANDARDS, WITH SURVIVAL KIT INSTALLED. RAFT BULGES OUT AND D	OES NOT FIT IN COMPARTMENT PROPERLY. ALSO THE BUTTON HALF OF THE CASE BELONGS TO A LEFT RAFT ASSEMBLY.					2	G	7	2 	4U				H10SW 					 
1995022400239	19950224	00239	SW 	1995	2	24	HEEA954373 	1	19950214	G	2824	AV24B1119B	VALVE 			BELL 	412 	412 	1182202	SW 										CONNECTOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										CANNON PLUG CONNECTOR IS BENT.						1	G	7	2 	4U				H4SW 					 
1995022400240	19950224	00240	SW 	1995	2	24	HEEA954374 	1	19950215	G	2822	9A1746	CARTRIDGE 			BELL 	214 	214ST 	1182106	SW 										FUEL SYS	TRIPS BREAKER 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				POPS CIRCUIT BREAKER. RECEIVED INSTALLED ON N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995022400241	19950224	00241	SW 	1995	2	24	HEEA954375 	1	19950215	G	6320	206040190005	PUMP 			BELL 	206 	206L3 	1182108	SW 										SEAL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	6610Y					51419				GARLOCK SEAL LEAKING. REPLACED WITH SERVICEABLE PUMP.						1	G	7	1 	3U				H2SW 					 
1995022400242	19950224	00242	EU 	1995	2	24	HEEA954376 	1	19950215	G	7931	DK040	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										ENG OIL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	54197					S805				#2 ENGINE OIL PRESSURE FLUCTUATING AT IDLE. REPLACED WITH SERVICEABLE TRANSMITTER.						1	G	7	2 	3U				H3EU 					 
1995022400243	19950224	00243	EU 	1995	2	24	HEEA954377 	1	19950215	G	7400	355A72302300	SENSOR ASSY 			AEROSP	AS355 	AS355F1 	8680810	EU 										AUTO RELIGHT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5793Y					5141				#2 AUTO RELIGHT COMES ON INTERMITTENTLY DURING FLIGHT. REPLACED WITH SERVICEABLE TRANSDUCER.						1	G	7	2 	3U				H11EU 					 
1995022400244	19950224	00244	SW 	1995	2	24	HEEA954378 	1	19950215	G	6310	206040015103	SHAFT 			BELL 	206 	206B3 	1181506	SW 										GR BOX	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268V	9428 				3605				TEMP-PLATE PEELING OFF. REPLACED INPUT DRIVE SHAFT.						1	G	7	1 	3U				H2SW 					 
1995022400245	19950224	00245	EU 	1995	2	24	HEEA954379 	1	19950216	G	5210	1172428211	CATCHER 			BOLKMS	117 	BK117B2 	5626013	EU 										LT SLIDER	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	860 				7238				L/H SLIDING DOOR FWD CATCHER WORN.						1	G	7	2 	3U			NC	H13EU 					 
1995022400246	19950224	00246	EU 	1995	2	24	HEEA954380 	1	19950216	G	6410	10531756	BLADE 		10531703 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81832	2523 			51127	S828				LEADING EDGE SEPARATION.						1	G	7	2 	3U				H3EU 					 
1995022400247	19950224	00247	EU 	1995	2	24	HEEA954381 	1	19950216	G	6410	10531756	BLADE 		10531703 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	DETERIORATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81832	2552 			51127	S828				RUBBER DETERIORATION.						1	G	7	2 	3U				H3EU 					 
1995022400248	19950224	00248	EU 	1995	2	24	HEEA954382 	1	19950216	G	6410	10531756	BLADE 		10531703 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81982	2212 			050005	S818				LEADING EDGE SEPARATION AT TIP.						1	G	7	2 	3U				H3EU 					 
1995022400249	19950224	00249	EU 	1995	2	24	HEEA954383 	1	19950216	G	6410	10531756	BLADE 		10531703 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	DETERIORATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81982	2760 			050005	S818				RUBBER DETERIORATION.						1	G	7	2 	3U				H3EU 					 
1995022400250	19950224	00250	EU 	1995	2	24	HEEA954384 	1	19950216	G	6410	10531756	BLADE 		10531703 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	724MB	2709 			050237	S756				CRACKED ON THRUSTPLATE.						1	G	7	2 	3U				H3EU 					 
1995022400251	19950224	00251	EU 	1995	2	24	HEEA954385 	1	19950216	G	6410	10531756	BLADE 		10531703 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	724MB	1402 			050237	S756				CRACKED ON THRUSTPLATE.						1	G	7	2 	3U				H3EU 					 
1995022400252	19950224	00252	EU 	1995	2	24	HEEA954386 	1	19950216	G	6410	10531756	BLADE 		10531703 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3535T	3595 			520	S113				LEADING EDGE SEPARATION.						1	G	7	2 	3U				H3EU 					 
1995022400253	19950224	00253	EU 	1995	2	24	HEEA954387 	1	19950216	G	6410	10531754	BLADE 		10531713 	BOLKMS	105 	BO105S 	5626006	EU 										T/R TIP BLOCK	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	54197	3523 			188	S805				TIP BLOCK SEPARATION.						1	G	7	2 	3U				H3EU 					 
1995022400254	19950224	00254	EU 	1995	2	24	HEEA954388 	1	19950216	G	6410	10531754	BLADE 		10531713 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	54197	6310 			188	S805				CRACKED PARALLEL TO THRUSTPLATE.						1	G	7	2 	3U				H3EU 					 
1995022400255	19950224	00255	EU 	1995	2	24	HEEA954389 	1	19950216	G	6410	10531754	BLADE 		10531713 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	91070	3189 			225	S145				DAMAGE ON TRAILING EDGE.						1	G	7	2 	3U				H3EU 					 
1995022400256	19950224	00256	EU 	1995	2	24	HEEA954390 	1	19950216	G	6410	10531754	BLADE 		10531713 	BOLKMS	105 	BO105S 	5626006	EU 										T/R	DETERIORATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	91070	6067 			225	S145				RUBBER DETERIORATION.						1	G	7	2 	3U				H3EU 					 
1995022400257	19950224	00257	EU 	1995	2	24	HEEA954391 	1	19950216	G	6410	10531754	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										T/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	9190F	3455 				S668				LEADING EDGE SEPARATION.						1	G	7	2 	3U				H3EU 					 
1995030300155	19950303	00155	GL 	1995	3	3	HEEA954392 	2	19950221	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE BLADES	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	91070	1195 			CAT25067	S145	CAE831141			ENGINE REMOVED DUE TO HIGH TOT. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION ON 1ST STAGE WHEEL B	LADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995030300156	19950303	00156		1995	3	3	HEEA954393 	2	19950221	G	7250	23001967	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 										3RD STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	91070	2307 			CAT25067	S145				ENGINE REMOVED DUE TO HIGH TOT. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION ON ALL 3RD STAGE WHE	EL BLADE LEADING EDGES AND OUTER BAND I.D. SCRAPPED 3RD STAGE WHEEL.					1	G	7	2 	3U				H3EU 					 
1995030300157	19950303	00157	GL 	1995	3	3	HEEA954394 	2	19950221	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE BLADES	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	724MB	1360 			CAT25294	S756	CAE835286			ENGINE REMOVED DUE TO HIGH CYCLED WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON 1	ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995030300158	19950303	00158	SW 	1995	3	3	HEEA954395 	1	19950221	G	5210	206031117315S	DOOR ASSY 			BELL 	206 	206L1 	1182107	SW 										EDGES	DAMAGED 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	50034					45167				DOOR DEFECTIVE; DIMPLES AT UPPER AND LOWER EDGES OF PART AS IS FROM THE MANUFACTURER.						1	G	7	1 	3U				H2SW 					 
1995030300159	19950303	00159	SW 	1995	3	3	HEEA954396 	1	19950221	G	7110	206064805019	SCREEN 			BELL 	206 	206L1 	1182107	SW 										COWLING	BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										SCREEN MESH BROKEN AFT END (LOWER) AS MARKED.						1	G	7	1 	3U				H2SW 					 
1995030300160	19950303	00160	EU 	1995	3	3	HEEA954397 	2	19950221	G	7532	97914211	VALVE 			BOLKMS	117 	BK117B2 	5626013	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					BLEED SOV	PIN BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	860 				7238				PIN BROKEN IN CONNECTOR.						1	G	7	2 	3U	3	U	NC	H13EU 	E5NE				 
1995030300161	19950303	00161	SW 	1995	3	3	HEEA954398 	1	19950221	G	6510	214040630001	COUPLING ASSY 			BELL 	214 	214ST 	1182106	SW 										T/R	WRONG PART 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										INCORRECT SPRING INSTALLED IN UNIT. SPRING P/N 214-040-632-001 INSTALLED . NEED SPRING P/N 214-040-632-003. REPAIRED B	Y PHI.					2	G	7	2 	4U				H10SW 					 
1995030300162	19950303	00162	SW 	1995	3	3	HEEA954399 	1	19950221	G	5260	FYLM735023	MOTOR ASSY 		SYLC502281 	BELL 	412 	412 	1182202	SW 										STEP	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2148K				565	36001				NO ROD MOVEMENT. VISUALLY INSPECTED BY THE ACCESSORY SHOP. UNIT INOPERATIVE. REMOVED MOTOR FROM UNIT AND BENCH CHECKE	D. DEAD SPOT ON ARMATURE.					1	G	7	2 	4U				H4SW 					 
1995030300163	19950303	00163	EU 	1995	3	3	HEEA954402 	1	19950223	G	2510	10573208	PANEL 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT RT	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4302G	1529 				S853				CRACKED AT MOUNTING POSITION.						1	G	7	2 	3U				H3EU 					 
1995030300164	19950303	00164	EU 	1995	3	3	HEEA954403 	1	19950223	G	2510	10573205	PANEL 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT LT	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4302G	1529 				S853				CRACKED AT MOUNTING POSITION.						1	G	7	2 	3U				H3EU 					 
1995030300165	19950303	00165	EU 	1995	3	3	HEEA954404 	1	19950223	G	2510	10573210	PANEL 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT RT	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4302G	1529 				S853				CRACKED AT MOUNTING POSITION.						1	G	7	2 	3U				H3EU 					 
1995030300166	19950303	00166	EU 	1995	3	3	HEEA954405 	1	19950223	G	2510	1057320701	TRIM ASSY 			BOLKMS	105 	BO105S 	5626006	EU 										DOOR PANEL	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4302G	1529 				S853				CRACKED AT MOUNTING POSITION.						1	G	7	2 	3U				H3EU 					 
1995030300167	19950303	00167	GL 	1995	3	3	HEEA954406 	2	19950223	G	7250	23031426	NOZZLE 		23035128 	BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					4TH STAGE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6160Z				CAT90585	51610	CAE895571			ENGINE REMOVED DUE TO N2 DRAG. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: LIFTING AND FLAKING PLASMA IN 4TH	 STAGE NOZZLE #4 TIP PATH. INSTALLED SERVICEABLE 4TH STAGE NOZZLE.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995030300168	19950303	00168	SW 	1995	3	3	HEEA954407 	1	19950223	G	6330	222330620103	BEARING 			BELL 	230 	230 	1182149	SW 										ISO MOUNT	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	458 				23009				ROD END BEARING WORN ON LATERAL ISOLATION MOUNT.						1	G	7	2 	3U			NC	H9SW 					 
1995030300169	19950303	00169	SW 	1995	3	3	HEEA954408 	1	19950223	G	6220	222031613103	LIFT LINK 			BELL 	230 	230 	1182149	SW 										M/R	BEARING WORN 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	230UN	1910 				23009				LOWER BEARING WORN, CAUSING VIBRATION.						1	G	7	2 	3U			NC	H9SW 					 
1995030300170	19950303	00170	SW 	1995	3	3	HEEA954409 	1	19950223	G	6330	222331618103	PYLON MOUNT 			BELL 	230 	230 	1182149	SW 										M/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	51 				23009				ROD END BEARING WORN ON R/H LONGITUDINAL ISOLATION MOUNT.						1	G	7	2 	3U			NC	H9SW 					 
1995030300171	19950303	00171	SW 	1995	3	3	HEEA954410 	1	19950223	G	2550	214070921103	CARGO HOOK 			BELL 	214 	214ST 	1182106	SW 										EXT LIFT	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				NEEDS OVERHAUL. RECEIVED INSTALLED ON N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995030300172	19950303	00172	GL 	1995	3	3	HEEA954411 	2	19950224	G	7532	23005368	BODY 		23005366 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30 	03013	GL 					BLEED VALVE	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5427S				FF50119	760168				RECEIVING INSPECTION OF NEW, NEVER INSTALLED BLEED VALVE BODY INDICATED PORT HOLE FOR ORIFICE P/N 23003102-01 IS IMPROPE	RLY MACHINED WITHOUT THREADS. INSTALLED NEW BLEED VALVE BODY.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995031000185	19950310	00185		1995	3	10	HEEA954413 	4	19950227	G	3417	214175421103	ADC 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	WRONG PART 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	8045T					28101				AIR DATA COMPUTER IS NOT FAA APPROVED. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH	-LHQ)					2	G	7	2 	4U				H10SW 					 
1995031000186	19950310	00186		1995	3	10	HEEA954414 	4	19950227	G	3454	DMN441	ANTENNA 			BELL 	214 	214ST 	1182106	SW 										VOR LOOP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				VOR NEEDLES WEAK AND ERRATIC. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000187	19950310	00187		1995	3	10	HEEA954415 	4	19950227	G	3454	DMN441	ANTENNA 			BELL 	214 	214ST 	1182106	SW 										VOR LOOP	WEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				VOR NEEDLES WEAK AND ERRATIC. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000188	19950310	00188	SW 	1995	3	10	HEEA954416 	1	19950227	G	5210	NAS5624R0A	CAM FOLLOWER 			BELL 	214 	214ST 	1182106	SW 										LT SLIDER	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				BEARING WORN L/H SLIDING DOOR.. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000189	19950310	00189	SW 	1995	3	10	HEEA954417 	4	19950227	G	2562	DK100	BEACON 			BELL 	214 	214ST 	1182106	SW 										LOCATOR BEACON	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				DUKANE BEACON OUT OF BATTERY DATE 01/28/95. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER W	AS VH-LHQ)					2	G	7	2 	4U				H10SW 					 
1995031000190	19950310	00190	SW 	1995	3	10	HEEA954418 	4	19950227	G	2562	DK100	BEACON 			BELL 	214 	214ST 	1182106	SW 										LOCATOR BEACON	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				DUE DATE ON BATTERY ILLEGIBLE. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000191	19950310	00191	SW 	1995	3	10	HEEA954419 	1	19950227	G	6240	41003285	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	STICKING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				STICKING. WOULD NOT ADJUST FOR COLLECTIVE UP-DOWN BY-PASS LIGHT. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREV	IOUS AIRCRAFT NUMBER WAS VH-LHQ)					2	G	7	2 	4U				H10SW 					 
1995031000192	19950310	00192	SW 	1995	3	10	HEEA954420 	1	19950227	G	7120	NAS620614D	BOLT 			BELL 	214 	214ST 	1182106	SW 										ENG MOUNT	STRIPPED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				BOLT FOR LOWER AFT ENGINE MOUNT HAS STRIPPED THREADS. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAF	T NUMBER WAS VH-LHQ)					2	G	7	2 	4U				H10SW 					 
1995031000193	19950310	00193	SW 	1995	3	10	HEEA954421 	1	19950227	G	6220	214010543101	RACE 			BELL 	214 	214ST 	1182106	SW 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				INNER RACE WORN. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000194	19950310	00194	SW 	1995	3	10	HEEA954422 	1	19950227	G	6220	214010490103	LINK ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R	WRONG PART 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	8045T	3407 				28101				NOT AN FAA APPROVED COMPONENT. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000195	19950310	00195	SW 	1995	3	10	HEEA954423 	1	19950227	G	6220	214010490103	LINK ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R	WRONG PART 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	8045T	3407 				28101				NOT AN FAA APPROVED COMPONENT. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000196	19950310	00196	SW 	1995	3	10	HEEA954424 	1	19950227	G	6330	214031615105	CLEVIS ARM 			BELL 	214 	214ST 	1182106	SW 										ELASTOMER BRG	SEPARATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				ELASTOMER BEARING (TO TORSION ARM) SEPARATED BEYOND LIMITS AS PER 214ST MM. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1	-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)					2	G	7	2 	4U				H10SW 					 
1995031000197	19950310	00197	SW 	1995	3	10	HEEA954426 	1	19950227	G	2432	214175380101	BATTERY 			BELL 	214 	214ST 	1182106	SW 										CELL PLATES	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				BATTERY WILL NOT TAKE A CHARGE, AND GETS VERY HOT. SUSPECT BREAKDOWN OF INSULATION BETWEEN CELL PLATES. PART RECEIVED I	NSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)					2	G	7	2 	4U				H10SW 					 
1995031000198	19950310	00198		1995	3	10	HEEA954427 	4	19950227	G	3421	258719343	GYRO 			BELL 	214 	214ST 	1182106	SW 										COCKPIT HSI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				VALID FLAG ON HSI DOES NOT PULL. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000199	19950310	00199		1995	3	10	HEEA954428 	4	19950227	G	3434	066301201	LIGHT ASSY 			BELL 	214 	214ST 	1182106	SW 										COCKPIT MARKER	INOPERATIVE 	E			HEEA	K				NONE 				P			NO WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	8045T					28101				APPROACH LIGHT WILL NOT ILLUMINATE. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LH	Q)					2	G	7	2 	4U				H10SW 					 
1995031000200	19950310	00200	SW 	1995	3	10	HEEA954429 	4	19950227	G	3450	071121004	CONTROL BOX 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				INTERNAL LIGHTING INOPERATIVE. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000201	19950310	00201		1995	3	10	HEEA954430 	4	19950227	G	2312	071121540	CONTROL 			BELL 	214 	214ST 	1182106	SW 										COCKPIT VHF	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				FACEPLATE WORN NEAR VOLUME CONTROL. FREQUENCY TRANSFER SWITCH MUST BE PRESSED TOO HARD IN ORDER TO TRANSFER FREQUENCIES	. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)					2	G	7	2 	4U				H10SW 					 
1995031000202	19950310	00202		1995	3	10	HEEA954431 	4	19950227	G	2210	214074303115	AMPLIFIER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				IN PITCH MODE, WOULD KICK OFF LINE. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LH	Q)					2	G	7	2 	4U				H10SW 					 
1995031000203	19950310	00203	SW 	1995	3	10	HEEA954433 	1	19950227	G	6710	214001370101	ACTUATOR 			BELL 	214 	214ST 	1182106	SW 										M/R CONTROL	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				AARS FORE AND AFT SERVO MOTOR INTERMITTENT. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WA	S VH-LHQ)					2	G	7	2 	4U				H10SW 					 
1995031000204	19950310	00204	SW 	1995	3	10	HEEA954436 	1	19950227	G	2612	703107	SENSING ELEMENT 			BELL 	214 	214ST 	1182106	SW 										FIRE DET	NUT MISSING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				B NUT MISSING. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000205	19950310	00205		1995	3	10	HEEA954437 	4	19950227	G	3454	214075231007	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT VOR	ERROR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				VOR NEEDLE 10 DEGREES OFF. PART RECEIVED INSTALLED ON AIRCRAFT ON 2-1-95. (PREVIOUS AIRCRAFT NUMBER WAS VH-LHQ)						2	G	7	2 	4U				H10SW 					 
1995031000206	19950310	00206	EU 	1995	3	10	HEEA954441 	1	19950228	G	6420	350A33211905	TAIL ROTOR 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R HUB	BEARING FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	482 				2771				BEARING IN T/R HUB SEPARATED 360 DEGREES AROUND.						1	G	7	1 	3U				H9EU 					 
1995031000207	19950310	00207	SW 	1995	3	10	HEEA954442 	1	19950228	G	2140	MS208228D	ELBOW 		206EC9062 	BELL 	206 	206L1 	1182107	SW 										HEATER	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5019F				1123	45244				FOUND ONE END OF ELBOW SANDED/FILED DOWN.						1	G	7	1 	3U				H2SW 					 
1995031000208	19950310	00208	SW 	1995	3	10	HEEA954443 	1	19950228	G	8010	214175171101	RELAY 			BELL 	214 	214ST 	1182106	SW 										START SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				GENERATOR WON'T GO INTO CROSS START. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995031000209	19950310	00209		1995	3	10	HEEA954444 	4	19950301	G	2312	064100900	TRANSCEIVER 		KTR905 	BELL 	212 	212 	1181420	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3131S					30953				WHEN TRANSMITTING ON 120.35, LOUD SQUEAL HEARD IN HEADSET AND ON RECEIVER END.						1	G	7	1 	4U				H4SW 					 
1995031000210	19950310	00210		1995	3	10	HEEA954445 	4	19950301	G	2312	064100900	TRANSCEIVER 		KTR905 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4253S					760035				WEAK AND GARBLED.						1	G	7	2 	3U				H1NE 					 
1995031000211	19950310	00211		1995	3	10	HEEA954446 	4	19950301	G	2312	064100900	TRANSCEIVER 		KTR905 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2743E					760155				WOULD NOT RECEIVE.						1	G	7	2 	3U				H1NE 					 
1995031000212	19950310	00212		1995	3	10	HEEA954447 	4	19950301	G	2312	064100900	TRANSCEIVER 		KTR905 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31217					760229				INTERMITTENT OPERATION.						1	G	7	2 	3U				H1NE 					 
1995031000213	19950310	00213		1995	3	10	HEEA954448 	4	19950301	G	3455	066104701	RECEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT ADF	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2014K					33020				INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995031000214	19950310	00214		1995	3	10	HEEA954449 	4	19950301	G	3455	066104701	RECEIVER 	KING 																COCKPIT ADF	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03										ADF HAS NO INDICATION AT ALL.																			 
1995031000215	19950310	00215		1995	3	10	HEEA954450 	4	19950301	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6160Z					51610				INOPERATIVE. REPLACED BURNT F401 FUSE, INSTALLED Q415 HEAT SINK. REPAIRED CONNECTION AT LOCAL OSCILLATOR. RETURNED TO 	SERVICE.					1	G	7	1 	3U				H2SW 					 
1995031000216	19950310	00216		1995	3	10	HEEA954451 	4	19950301	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911TL					7198				INOPERATIVE. REPLACED DEFECTIVE CAVITY OSCILLATOR V101 AND BROKEN COIL L101, ADJUSTED FREQUENCY AND RETURNED TO SERVICE.						1	G	7	2 	3U				H13EU 					 
1995031000217	19950310	00217		1995	3	10	HEEA954452 	4	19950301	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5031U					S678				IDENT LIGHT IS OUT. ATC REPORTED GOOD SIGNAL FROM TRANSPONDER. REPLACED V301 PHOTODETECTOR , DETERIORATED RESISTOR R477	...RETURNED TO SERVICE.					1	G	7	2 	3U				H3EU 					 
1995031000218	19950310	00218		1995	3	10	HEEA954453 	4	19950301	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911TL					7198				ATC DOES NOT RECEIVE IN AIRCRAFT. REPLACED DEFECTIVE V101 CAVITY OSCILLATOR, BURNT RESISTOR R441, AND DETERIORATED RESIS	TOR R477, ADJUSTED FREQUENCY AND RETURNED AIRCRAFT TO SERVICE.					1	G	7	2 	3U				H13EU 					 
1995031000219	19950310	00219		1995	3	10	HEEA954454 	4	19950301	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5017G					45228				NO OUTPUT. ADJUSTED FREQUENCY, REPLACED DETERIORATED RESISTOR R477 AND INOPERATIVE V301. RETURNED TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995031000220	19950310	00220		1995	3	10	HEEA954455 	4	19950301	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L 	1181522	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21497					51518				DOES NOT TURN ON. REPLACED INOPERATIVE Q415 TRANSISTOR, INOPERATIVE V101 CAVITY OSCILLATOR, AND DETERIORATED R477 RESIST	OR. RETURNED TO SERVICE.					1	G	7	1 	3U				H2SW 					 
1995031000221	19950310	00221		1995	3	10	HEEA954456 	4	19950301	G	2312	071101215	TRANSCEIVER 		KFS590B 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546G					760076				FREQUENCIES 122.60 AND 122.00 INOPERATIVE.						1	G	7	2 	3U				H1NE 					 
1995031000222	19950310	00222		1995	3	10	HEEA954457 	4	19950301	G	2312	071101218	TRANSCEIVER 		KFS590B 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3122H					760233				NUMBERS WILL NOT TURN.						1	G	7	2 	3U				H1NE 					 
1995031000223	19950310	00223		1995	3	10	HEEA954458 	4	19950301	G	3454	071105404	RECEIVER 		KFS5608 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911MJ					760231				LOCALIZER AND VOR FAILED INTERMITTENTLY. SLIGHT JIGGLE ON SELECTOR CAUSES VOR AND LOCALIZER TO BE FLAGGED.						1	G	7	2 	3U				H1NE 					 
1995031000224	19950310	00224		1995	3	10	HEEA954459 	4	19950301	G	2312	071121540	CONTROL 			BELL 	214 	214ST 	1182106	SW 										COCKPIT COMM	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				DISPLAY DIM IN BRIGHT LIGHT. REPLACED DISPLAY AND LENS. REPLACED INTERMITTENT TRANSFER SWITCH S301 AND HEADER P201. RE	TURNED TO SERVICE.					2	G	7	2 	4U				H10SW 					 
1995031000225	19950310	00225	EU 	1995	3	10	HEEA954460 	1	19950301	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	86CH	5903 				S557				AFTER SETTING BLADE INTO GROUND TRACK AND BALANCE(.095 IPS), AIRCRAFT PICKED UP INTO A HOVER. BLADE CLIMBED OUT AND IPS	 READING WENT TO .6.					1	G	7	2 	3U				H3EU 					 
1995031000226	19950310	00226	EU 	1995	3	10	HEEA954461 	1	19950301	G	6210	10515170	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5029H	3563 				S670				NOSE SHELL CRACKED.						1	G	7	2 	3U				H3EU 					 
1995031000227	19950310	00227	EU 	1995	3	10	HEEA954462 	1	19950301	G	6210	10515170	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5029H	3563 				S670				NOSE SHELL CRACKED.						1	G	7	2 	3U				H3EU 					 
1995031000228	19950310	00228		1995	3	10	HEEA954463 	4	19950301	G	3421	1113034	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT ATTITUDE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22342					760096				INOPERATIVE IN PITCH MODE.						1	G	7	2 	3U				H1NE 					 
1995031000229	19950310	00229	SW 	1995	3	10	HEEA954464 	1	19950301	G	5320	205030280141	DECK 			BELL 	412 	412 	1182202	SW 										LT SERVICE DECK	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				SEPARATION ON TOP SKIN APPROXIMATELY 4" X 7". CENTER OF SEPARATED AREA 7" FROM FWD EDGE AND 11' FROM INBOARD EDGE.						1	G	7	2 	4U				H4SW 					 
1995031000230	19950310	00230	SW 	1995	3	10	HEEA954465 	1	19950301	G	5530	206020113117	FIN ASSY 			BELL 	206 	206L3 	1182108	SW 										TAIL BOOM	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										FIN TOO THICK AT MOUNTING INSERTS MAKING BOLTS TOO SHORT TO MOUNT TO TAILBOOM.						1	G	7	1 	3U				H2SW 					 
1995031000231	19950310	00231	SW 	1995	3	10	HEEA954466 	1	19950301	G	5310	206031100701	TUB 			BELL 	206 	206B3 	1181506	SW 										SHELL ASSY	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	2268W					3606				REMOVED SHELL ASSY FROM CRATE. FOUND AREA NEAR R/H NAV. LIGHT HOLE, ON INSIDE SKIN HAVING A GOUGE (HOLE) IN SKIN, WHICH	 WAS FILLED WITH ADHESIVE AND ADDED INSERT. FOUND INSIDE SKIN POLISHED DUE TO EXCESSIVE SEALANT DROPPINGS, CAUSING PROT	ECTIVE COATING TO BE REMOVED FROM RIGID SKIN. FOUND ALL ANGLES INSTALLED TO SHELL ASSY HAVING SEALANT INSTEAD OF BONDIN	G ADHESIVE. FOUND SEVERAL ADDED INSERTS ON BOTTOM SIDE OF SHELL ASSY.			1	G	7	1 	3U				H2SW 					 
1995031000232	19950310	00232	SW 	1995	3	10	HEEA954467 	1	19950301	G	6320	206040190005	PUMP 			BELL 	206 	206L3 	1182108	SW 										INNER SEAL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	6160Z					51610				OIL PUMP INNER SEAL LEAKING. REPLACED WITH SERVICEABLE OIL PUMP.						1	G	7	1 	3U				H2SW 					 
1995031000233	19950310	00233	SW 	1995	3	10	HEEA954468 	1	19950301	G	6320	206040190005	PUMP 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C30P 	03013	GL 					XMSN OIL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2125M					45649				LEAKING. REPLACED WITH SERVICEABLE OIL PUMP.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995031000234	19950310	00234	SW 	1995	3	10	HEEA954469 	1	19950301	G	6310	206040270101	AFT SUPPORT 			BELL 	206 	206L3 	1182108	SW 										FREEWHEEL	CAP LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	6610Y					51419				FREEWHEELING UNIT AFT CAP LEAKING. REPLACED WITH SERVICEABLE AFT CAP.						1	G	7	1 	3U				H2SW 					 
1995031000235	19950310	00235	SW 	1995	3	10	HEEA954470 	1	19950301	G	7712	206075739103	TORQUEMETER 			BELL 	206 	206L3 	1182108	SW 										COCKPIT	STICKING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6603X					51412				NEEDLE STICKING IN ALL RANGES. TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW 					 
1995031000236	19950310	00236	SW 	1995	3	10	HEEA954471 	1	19950301	G	7722	206375006101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	LIGHTS INOP 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748Q	146 				45499				INTERNAL LIGHTS INOPERATIVE.						1	G	7	1 	3U				H2SW 					 
1995031000237	19950310	00237	EU 	1995	3	10	HEEA954472 	1	19950302	G	6230	350A37000402	TRANSMISSION 			SNIAS 	350 	AS350B2 	8680813	EU 										SWASHPLATE	LEAKS GREASE 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	60951	921 				2771				SWASHPLATE SLINGING GREASE AND BOOT IS STRETCHED.						1	G	7	1 	3U				H9EU 					 
1995031000238	19950310	00238		1995	3	10	HEEA954473 	4	19950302	G	3414	38399330	INDICATOR 			AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT AIR SPD	STUCK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y					5141				NEEDLE STUCK AT 20MPH. TIME SINCE REPAIR 19:50.						1	G	7	2 	3U				H11EU 					 
1995031000239	19950310	00239	SW 	1995	3	10	HEEA954474 	1	19950302	G	7810	206064300005	EXHAUST ASSY 			BELL 	206 	206L1 	1182107	SW 										MOUNT FLANGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5742N					45477				CRACKED ON AFT SIDE NEAR MOUNTING FLANGE. CRACK IS ONE INCH LONG. INSTALLED SERVICEABLE EXHAUST STACK.						1	G	7	1 	3U				H2SW 					 
1995031000240	19950310	00240		1995	3	10	HEEA954475 	4	19950302	G	3453	453105004	R50I 	ARNAV 		SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5426U					760167				ENTER BUTTON WORKS INTERMITTENTLY.						1	G	7	2 	3U				H1NE 					 
1995031000241	19950310	00241		1995	3	10	HEEA954476 	4	19950302	G	3451	6222012011	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT DME	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				DRAWS EXCESSIVE CURRENT WHEN TURNED ON.						1	G	7	2 	3U				H1NE 					 
1995031000242	19950310	00242	EU 	1995	3	10	HEEA954477 	1	19950302	G	6720	741C000004	ACTUATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8765J					7054				TAIL ROTOR ACTUATOR WILL NOT MODE WITH HYDRAULIC POWER APPLIED.						1	G	7	2 	3U				H13EU 					 
1995031000243	19950310	00243	NE 	1995	3	10	HEEA954478 	1	19950302	G	6410	7610105101041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5444X	9391 				760174				BLADE HAS THE NYLON WRAP ON PADDLE "A" SIDE ON THE OUTBOARD SIDE.						1	G	7	2 	3U				H1NE 					 
1995031000244	19950310	00244		1995	3	10	HEEA954479 	4	19950302	G	3414	8000	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT AIR SPD	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	50182					45242				NEEDLE INDICATES 8 KNOTS LOW AT 100 KNOTS.						1	G	7	1 	3U				H2SW 					 
1995031000245	19950310	00245		1995	3	10	HEEA954480 	4	19950302	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				CVR LIGHT ILLUMINATES INTERMITTENTLY IN FLIGHT. TIME SINCE REPAIR 553:50.						1	G	7	2 	4U				H4SW 					 
1995031000246	19950310	00246		1995	3	10	HEEA954481 	4	19950302	G	2350	AA95758	AUDIO CONTROL 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	401PH					7050				BOTH VHF'S GARBLED AND BLEED OVER (VHF1 TO VHF2) REPLACED C309 P/N 10-36-227, BENCH TEST GOOD WITH NAT TS-AA TEST PANEL.						1	G	7	2 	3U				H13EU 					 
1995031000247	19950310	00247	SW 	1995	3	10	HEEA954482 	1	19950302	G	6320	206040190005	PUMP 			BELL 	206 	206L1 	1182107	SW 										M/R XMSN	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	5748Q					45499				OIL LEAKING OUT OF SPLINE SHAFT. REPLACED SHAFT SEAL .						1	G	7	1 	3U				H2SW 					 
1995031000248	19950310	00248		1995	3	10	HEEA954483 	4	19950302	G	3413	RC30VIL	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				NEEDLE STICKS AT 3000 FPM GOING UP SCALE. TIME SINCE REPAIR :40.						1	G	7	2 	4U				H4SW 					 
1995031000249	19950310	00249	EU 	1995	3	10	HEEA954484 	1	19950302	G	2435	23032027	STARTER 			BOLKMS	117 	BK117B2 	5626013	EU 										START/GEN	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911LK					7168				INOPERATIVE. REPLACED WITH SERVICEABLE STARTER GENERATOR.						1	G	7	2 	3U			NC	H13EU 					 
1995031000250	19950310	00250	EU 	1995	3	10	HEEA954485 	1	19950302	G	2435	23032048	STARTER 			BOLKMS	117 	BK117B2 	5626013	EU 										START/GEN	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	1807 				7234				STARTER GENERATOR INOPERATIVE. REPLACED WITH SERVICEABLE STARTER GENERATOR.						1	G	7	2 	3U			NC	H13EU 					 
1995031000251	19950310	00251	SW 	1995	3	10	HEEA954486 	1	19950302	G	3310	900281	LIGHT ASSY 			BELL 	206 	206L3 	1182108	SW 										COCKPIT	INCOMPLETE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										INCOMPLETE ASSEMBLY.						1	G	7	1 	3U				H2SW 					 
1995031000252	19950310	00252		1995	3	10	HEEA954487 	4	19950302	G	3442	MI5851345	INDICATOR 		P40 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				NO DISPLAY.						1	G	7	2 	3U				H1NE 					 
1995031000253	19950310	00253	SW 	1995	3	10	HEEA954488 	1	19950303	G	6220	412010124109	BOLT 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	21498	1613 				36003				CARBIDE COATING FLAKING BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995031000254	19950310	00254	EU 	1995	3	10	HEEA954489 	1	19950303	G	7110	55S15	CLAMP 			SNIAS 	350 	AS350B2 	8680813	EU 										COWL	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	567 				2777				BOLT ON ATTACH ANGLE BROKE. INSTALLED SERVICEABLE CLAMP.						1	G	7	1 	3U				H9EU 					 
1995031000255	19950310	00255	EU 	1995	3	10	HEEA954490 	1	19950303	G	7112	350A54112420	BRACKET 			SNIAS 	350 	AS350B2 	8680813	EU 										AIR DUCT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	567 				2777				STARTER GENERATOR AIR DUCT SUPPORT BRACKET BROKE. INSTALLED NEW SUPPORT.						1	G	7	1 	3U				H9EU 					 
1995031000256	19950310	00256	GL 	1995	3	10	HEEA954491 	2	19950303	G	7230	23008090	GEAR SHAFT 		23005200 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					SPUR ADAPTER	STEP WEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3178K	915 			CAC70148	45765	CAE860046			ENGINE REMOVED DUE TO OIL OVERTEMP INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYO	ND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEARSHAFT.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995032400121	19950324	00121	EU 	1995	3	24	HEEA954534 	1	19950315	G	6720	350A33214501	ROD 			SNIAS 	350 	AS350B2 	8680813	EU 										PITCH CONTROL	WORN BEARINGS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	932 				2771				WORN BEARINGS.						1	G	7	1 	3U				H9EU 					 
1995032400122	19950324	00122	SW 	1995	3	24	HEEA954536 	1	19950315	G	5260	FYLM735023	MOTOR ASSY 		SYLC502281 	BELL 	412 	412 	1182202	SW 										STEP	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N	42 			92794	33010				INTERMITTENT OPERATION. INSPECTED BY ACCESSORY SHOP AND FOUND UNIT INTERMITTENT. REMOVED MOTOR AND FOUND DEAD SPOT ON 	ARMATURE.					1	G	7	2 	4U				H4SW 					 
1995032400123	19950324	00123	SW 	1995	3	24	HEEA954537 	1	19950315	G	7722	35712519129	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										INDICATOR NEEDS BENCH CHECK.						1	G	7	1 	3U				H2SW 					 
1995032400124	19950324	00124	SW 	1995	3	24	HEEA954538 	1	19950316	G	6510	214040606005	BEARING 		214040600103	BELL 	214 	214ST 	1182106	SW 										HANGER ASSY	ROUGH 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	3897N				A478	28106				VIBRATION ON AIRCRAFT. (ROUGH BEARING)						2	G	7	2 	4U				H10SW 					 
1995032400125	19950324	00125	SW 	1995	3	24	HEEA954540 	1	19950316	G	6220	206010110105	WASHER 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2754W	1129 			A2057	45260				EXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO BE DETERIORATED. SCRAPPED LOCALLY. APPLIED LOWER TORQUE ON ADJ. SCREWS P/N 	206-010-111-105 AND LOWER PRELOAD ON THRUST PLUGS.					1	G	7	1 	3U				H2SW 					 
1995032400126	19950324	00126	SW 	1995	3	24	HEEA954542 	1	19950316	G	6320	206040052009	HOUSING 			BELL 	206 	206B 	1181511	SW 										MAIN GR BOX	SEAL LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2277A					3630				SEAL LEAKING. ALSO REPLACED SEAL P/N 206-040-156-101 AND ADAPTER P/N 206-040-048-003 AS AN ASSEMBLY. SEE MMIR'S #4543	 AND #4544 FOR OTHER PARTS REPLACED.					1	G	7	1 	3U				H2SW 					 
1995032400127	19950324	00127	SW 	1995	3	24	HEEA954543 	1	19950316	G	6320	206040156101	SEAL ASSY 			BELL 	206 	206B 	1181511	SW 										M/R GR BOX	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2277A					3630				SEAL LEAKING. ALSO REPLACED HOUSING P/N 206-040-052-009 AND ADAPTER P/N 206-040-048-003 AS AN ASSEMBLY. SEE MMIR'S #45	42 AND #4544 FOR OTHER PARTS REPLACED.					1	G	7	1 	3U				H2SW 					 
1995032400128	19950324	00128	SW 	1995	3	24	HEEA954544 	1	19950316	G	6320	206040048003	ADAPTER 			BELL 	206 	206B 	1181511	SW 										M/R GR BOX	SEAL LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2277A					3630				SEAL LEAKING. ALSO REPLACED HOUSING P/N 206-040-052-009 AND SEAL P/N 206-040-156-101 AS AN ASSEMBLY. SEE MMIR'S #4542 	AND #4543 FOR OTHER PARTS REPLACED.					1	G	7	1 	3U				H2SW 					 
1995032400129	19950324	00129	GL 	1995	3	24	HEEA954545 	2	19950316	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	54197	1740 			CAT40390	S805	CAE830763			ENGINE REMOVED DUE TO 1750 HOUR INSPECTION AND TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 	 SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995032400130	19950324	00130	GL 	1995	3	24	HEEA954546 	2	19950317	G	7320	40030043800	LINEAR ACTUATOR 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30 	03013	GL 					ENGINE	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3116P	359 				51530				BEEP MOTOR INOPERATIVE.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995032400131	19950324	00131	SW 	1995	3	24	HEEA954547 	1	19950317	G	6230	412310400107	BEARING 		412010402109	BELL 	412 	412 	1182202	SW 										SWASHPLATE	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2148K	586 			RE0017	36001				BEARING WORN BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995032400132	19950324	00132	SW 	1995	3	24	HEEA954548 	1	19950317	G	6230	412310400107	BEARING 		412010402107	BELL 	412 	412 	1182202	SW 										SWASHPLATE	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347	451 			RE0018	36005				BEARING WORN BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995032400133	19950324	00133	SW 	1995	3	24	HEEA954549 	1	19950317	G	6230	412310400107	BEARING 		412010402107	BELL 	412 	412 	1182202	SW 										SWASHPLATE	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	33008	245 			RE0006	36004				BEARING WORN BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995033100149	19950331	00149	SW 	1995	3	31	HEEA954557 	1	19950320	G	2430	214175155103	RELAY 			BELL 	214 	214ST 	1182106	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				LONG TIME DELAY.						2	G	7	2 	4U				H10SW 					 
1995033100150	19950331	00150	SW 	1995	3	31	HEEA954560 	1	19950322	G	6330	206033552001	STOP ASSY 			BELL 	206 	206L3 	1182108	SW 										M/R XMSN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										RUBBER AND STEEL WASHER BONDED OFF SET ON STOP ASSEMBLY.						1	G	7	1 	3U				H2SW 					 
1995033100151	19950331	00151	EU 	1995	3	31	HEEA954561 	1	19950322	G	6410	355A12004008	BLADE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	983 				2771				SPAR REINFORCEMENT CRACKED, BUBBLING ON SKIN OF BLADE.						1	G	7	1 	3U				H9EU 					 
1995033100152	19950331	00152	EU 	1995	3	31	HEEA954562 	1	19950322	G	6710	10513142	ROD END 			BOLKMS	117 	BK117B2 	5626013	EU 										M/R	WORN BEARING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	992 				7234				WORN BEARINGS.						1	G	7	2 	3U			NC	H13EU 					 
1995033100153	19950331	00153	GL 	1995	3	31	HEEA954563 	2	19950322	G	7250	6886407	WHEEL 		6898735 	BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20B 	03013	GL 					4TH STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2271V	1244 			CAT32847F	3615	CAE835219			ENGINE REMOVED DUE TO CYCLED 1ST THROUGH 4TH STAGE WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MILD 	SULFIDATION ON 50% OF TURBINE 1ST STAGE WHEELS BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995033100154	19950331	00154		1995	3	31	HEEA954564 	4	19950322	G	3421	7660002113102	GYRO 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VG	PRECESSING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1546K					760082				GYRO PRECESSING.						1	G	7	2 	3U				H1NE 					 
1995033100155	19950331	00155	EU 	1995	3	31	HEEA954566 	1	19950322	G	3510	50C002410	INDICATOR 			BOLKMS	117 	BK117B2 	5626013	EU 										OXY SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	132AE	849 				7238				INDICATOR DEFECTIVE. CANNOT CALIBRATE, ZERO GOES FROM -.2 TO + .2.						1	G	7	2 	3U			NC	H13EU 					 
1995033100156	19950331	00156	EU 	1995	3	31	HEEA954567 	1	19950322	G	6730	7004109901	ACTUATOR ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 										M/R CONTROL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8765J					7054				UNIT MAKES EXCESSIVE NOISE DURING OPERATION AND DURING RIGGING CHECK OF AIRCRAFT FOUND LOCK WASHER BROKEN.						1	G	7	2 	3U				H13EU 					 
1995033100157	19950331	00157	EU 	1995	3	31	HEEA954568 	1	19950322	G	3310	0252341	JUNCTION BOX 			BOLKMS	117 	BK117B2 	5626013	EU 										LIGHTING	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	134AE	952 				7237				TRANSFORMER LOOSE IN BOX, INOPERATIVE, 35A CIRCUIT BREAKER LUG STRIPPED. TIME SINCE REPAIR 0:00.						1	G	7	2 	3U			NC	H13EU 					 
1995033100158	19950331	00158	SW 	1995	3	31	HEEA954569 	1	19950322	G	7931	APTE138100G	TRANSMITTER 			BELL 	412 	412 	1182202	SW 										OIL PRESSURE	LOW OUTPUT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	23023					33080				LOW OUTPUT - READS 15 PSI LOW ON GAUGE.						1	G	7	2 	4U				H4SW 					 
1995033100159	19950331	00159		1995	3	31	HEEA954570 	4	19950322	G	3421	501145301	GYRO 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	PRECESSING 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546K					760082				GYRO PRECESSING.						1	G	7	2 	3U				H1NE 					 
1995033100160	19950331	00160	SW 	1995	3	31	HEEA954571 	1	19950322	G	5310	206031100701	TUB 			BELL 	206 	206L3 	1182108	SW 										FUSELAGE SHELL	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										AFT TRANSITION AREA TOO LARGE AND RIGHT HAND RAIL TOO LOW. TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW 					 
1995033100161	19950331	00161	EU 	1995	3	31	HEEA954572 	2	19950322	G	7532	97914211	VALVE 			BOLKMS	105 	BO105S 	5626006	EU 										BLEED SOV	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8197X					S808				SOLENOID INTERMITTENT OPERATION.						1	G	7	2 	3U				H3EU 					 
1995033100162	19950331	00162	EU 	1995	3	31	HEEA954573 	1	19950322	G	2430	UC2814	DC CONVERTER 			BOLKMS	117 	BK117B1 	5626012	EU 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5196T					7152				OVERHEATS AND WORKS INTERMITTENTLY.						1	G	7	2 	3U				H13EU 					 
1995033100163	19950331	00163	SW 	1995	3	31	HEEA954574 	1	19950322	G	6410	212010750105	BLADE 			BELL 	212 	212 	1181420	SW 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1079U	3274 				31122				TIP CLOSURE WORN THROUGH AND SEPARATED.						1	G	7	1 	4U				H4SW 					 
1995033100164	19950331	00164	SW 	1995	3	31	HEEA954575 	1	19950322	G	6410	212010750105	BLADE 			BELL 	212 	212 	1181420	SW 										T/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1079U	3274 				31122				SEPARATION ON TIP CAP AND BLADE SKIN.						1	G	7	1 	4U				H4SW 					 
1995033100165	19950331	00165		1995	3	31	HEEA954576 	4	19950322	G	2210	258719343	GYRO 			BEECH 	200 	200CBEECH 	1152926	CE 										YAW DAMPER	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	500PH					BL29				CAUSES YAW DAMPER TO SWING SIDE TO SIDE.						1	L	7	2 	4T				A24CE 					 
1995033100166	19950331	00166	EU 	1995	3	31	HEEA954577 	1	19950322	G	6720	741C000004	ACTUATOR 			BOLKMS	117 	BK117B2 	5626013	EU 										T/R	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	134AE					7237				LEAKING LOWER SEAL AND PILOT VALVE AND EHA SEAL.						1	G	7	2 	3U			NC	H13EU 					 
1995033100167	19950331	00167	SW 	1995	3	31	HEEA954578 	1	19950323	G	7712	412075008111	INDICATOR 			BELL 	412 	412 	1182202	SW 										NR 2 TORQUE	TRIPS BREAKER 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22608					33075				#2 SIDE POPS CIRCUIT BREAKER.						1	G	7	2 	4U				H4SW 					 
1995033100168	19950331	00168		1995	3	31	HEEA954579 	4	19950323	G	3451	6222012011	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT DME	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				LED INOPERATIVE.						1	G	7	2 	3U				H1NE 					 
1995033100169	19950331	00169		1995	3	31	HEEA954580 	4	19950323	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6559Z					36019				HEADING CARD WILL NOT MOVE. TIME SINCE REPAIR 2:55.						1	G	7	2 	4U				H4SW 					 
1995033100170	19950331	00170	SW 	1995	3	31	HEEA954581 	1	19950323	G	7810	212061201012	EJECTOR 			BELL 	212 	212 	1181420	SW 										RT EXHAUST	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										DIMPLES CRACKED OUT AT MOUNTING PLATE. SEAL RETAINER BENT AND DISTORTED AND RIVETS IMPROPERLY INSTALLED. TIME SINCE RE	PAIR 0:00.					1	G	7	1 	4U				H4SW 					 
1995033100171	19950331	00171	SW 	1995	3	31	HEEA954582 	1	19950323	G	2824	L88010491	VALVE 			BELL 	412 	412 	1182202	SW 										FUEL SYS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				VALVE INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995033100172	19950331	00172	SW 	1995	3	31	HEEA954583 	1	19950323	G	3340	4596	LAMP 			BELL 	206 	206L4 	1182110	SW 										LANDING LIGHT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	62127					52023				LOWER LANDING LIGHT INOPERATIVE. REPLACED WITH SERVICEABLE LIGHT.						1	G	7	1 	3U			NC	H2SW 					 
1995033100173	19950331	00173		1995	3	31	HEEA954584 	4	19950323	G	3421	5040017901	INDICATOR 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT ATTITUDE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951	583 				2771				ATTITUDE INDICATOR WON'T STAY ERECT.						1	G	7	1 	3U				H9EU 					 
1995033100174	19950331	00174		1995	3	31	HEEA954586 	4	19950323	G	3453	25410038	LORAN 		7000CDU 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22608					33075				PARTIAL LIGHT SEGMENT IN DISPLAY.						1	G	7	2 	4U				H4SW 					 
1995033100175	19950331	00175		1995	3	31	HEEA954587 	4	19950323	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S	2465 				36002				CVR WILL NOT START.						1	G	7	2 	4U				H4SW 					 
1995033100176	19950331	00176		1995	3	31	HEEA954588 	4	19950323	G	3451	066106902	INDICATOR 		KDI573 	BELL 	412 	412 	1182202	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2298Z					33077				DISPLAY INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995033100177	19950331	00177		1995	3	31	HEEA954589 	4	19950323	G	2312	4000106010	CONTROL UNIT 		C1000 	BELL 	412 	412 	1182202	SW 										COCKPIT	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	23023					33080				BROKEN FACE PLATE AND INTERMITTENT THUMBWHEEL, ALSO UNIT GIVES ERRONEOUS TONE FREQUENCIES.						1	G	7	2 	4U				H4SW 					 
1995033100178	19950331	00178		1995	3	31	HEEA954590 	4	19950323	G	2312	40001452500	TRANSCEIVER 		RT138F 	BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT VHF	LOW POWER 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5196T					7152				LOW POWER OUT.						1	G	7	2 	3U				H13EU 					 
1995033100179	19950331	00179		1995	3	31	HEEA954591 	4	19950323	G	3453	4530103	RECEIVER 		ARNAV21 	BOLKMS	105 	BO105CBS 	5626008	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5421E					S806				INTERMITTENTLY GOES INTO OSCILLATION MODE.						1	G	7	2 	3U			NC	H3EU 					 
1995033100180	19950331	00180	NE 	1995	3	31	HEEA954592 	1	19950323	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911MJ					760231				CRACK IN THE ABRASION STRIP WITH SEPARATION.						1	G	7	2 	3U				H1NE 					 
1995033100181	19950331	00181	NE 	1995	3	31	HEEA954593 	1	19950323	G	6410	7610105101041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	WONT BALANCE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5426U	6309 				760167				UNABLE TO BALANCE. SUSPECT THAT PADDLE "A" MAY HAVE WATER INSIDE.						1	G	7	2 	3U				H1NE 					 
1995033100182	19950331	00182	GL 	1995	3	31	HEEA954594 	2	19950323	G	7261	6854424	SHAFT SEAL 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					START/GENERATOR	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	230UN					23009				LEAK AT STARTER GENERATOR SEAL. REPLACED WITH SERVICEABLE SEAL.						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995033100183	19950331	00183	EU 	1995	3	31	HEEA954595 	1	19950323	G	2910	704A33690004	BELT 			SNIAS 	350 	AS350B2 	8680813	EU 										HYD PUMP	FRAYED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951					2771				FRAYED HYD PUMP BELT. REPLACED WITH SERVICEABLE BELT.						1	G	7	1 	3U				H9EU 					 
1995033100184	19950331	00184	SW 	1995	3	31	HEEA954598 	1	19950323	G	6300	212040005103	SHAFT 			BELL 	412 	412 	1182202	SW 										MAIN DRIVE	RUSTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2258F	18045				33073				HEAT TEMP INDICATORS COMING UNBONDED AND RUSTING UNDERNEATH. REPLACED WITH SERVICEABLE MAIN DRIVE SHAFT.						1	G	7	2 	4U				H4SW 					 
1995033100185	19950331	00185	SW 	1995	3	31	HEEA954599 	1	19950323	G	6300	206040015103	SHAFT 			BELL 	206 	206B3 	1181506	SW 										TEMP PLATES	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268V	7704 				3605				TEMP PLATES COMING UNBONDED ON DRIVESHAFT AFTER ONLY 24:50 HOURS IN SERVICE. REPLACED DRIVE SHAFT AND RETURNED AIRCRAFT 	TO SERVICE.					1	G	7	1 	3U				H2SW 					 
1995033100186	19950331	00186	SW 	1995	3	31	HEEA954600 	1	19950323	G	6320	206040052009	HOUSING 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	6160Z					51610				INPUT SEAL LEAKING ON TRANSMISSION. INSTALLED SERVICEABLE SEAL ASSY.						1	G	7	1 	3U				H2SW 					 
1995033100187	19950331	00187		1995	3	31	HEEA954601 	4	19950323	G	3451	066107001	TRANCEIVER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT DME	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	105WK					S812				DME INOPERATIVE. FOUND BURNT FUSE (F201). REPLACED FUSE. REPAIRED PROBLEM. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995033100188	19950331	00188		1995	3	31	HEEA954602 	4	19950323	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X					51495				BENCH CHECK REQUIRED. REPLACED DETERIORATED RESISTOR R477. INSTALLED HEATSINK BEHIND TRANSISTOR Q415 AS PER KING SERVI	CE BULLETIN KT76A-6. REPLACED WEAK PHOTOCELL V301. ADJUSTED POWER OUT AND FREQUENCY TO MEET SPECS. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995033100189	19950331	00189		1995	3	31	HEEA954603 	4	19950323	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3892R					45594				REPLY LIGHT INOPERATIVE. REPLACED DETERIORATED RESISTOR R477. REPLACED TRANSISTOR Q415 AND INSTALLED HEATSINK BEHIND Q	415. REPLACED FACEPLATE AND WEAK PHOTOCELL V301. REPLACED CAVITY OSCILLATOR V101. REPAIRED. ADJUSTED PULSE WIDTH AND	 FREQUENCY. CLEANED CONTACTS ON ALL WAFERS. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995033100190	19950331	00190		1995	3	31	HEEA954604 	4	19950323	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31801					51074				NO OUTPUT; WILL NOT REPLY TO INTERROGATIONS FROM ATC600 OR GROUND CONTROL. VERIFIED UNIT TO HAVE WEAK POWER AND OFF FREQ	UENCY. REPLACED CAVITY OSCILLATOR V101. REPAIRED. UNIT HAS WEAK RECEIVER SENSE. REPLACED MIXER DIODE CR202. REPAIRE	D. ALIGNED RECEIVER. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995033100191	19950331	00191		1995	3	31	HEEA954605 	4	19950323	G	2312	TH3502FFF	CONTROL HEAD 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT FM	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911TL					7198				CHANNEL 1 INTERMITTENT ON RT-3.						1	G	7	2 	3U				H13EU 					 
1995033100192	19950331	00192		1995	3	31	HEEA954606 	4	19950323	G	2312	064101700	TRANSCEIVER 		KAC952 	BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8045T					28101				NO TRANSMIT; WILL NOT TONE.						2	G	7	2 	4U				H10SW 					 
1995033100193	19950331	00193	NE 	1995	3	31	HEEA954607 	1	19950323	G	2931	7645001078104	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				PILOT REPORTED #1 HYD PRESSURE DROP TO LOWER RED LINE. (#1 NEEDLE READS LOW WHEN HEATED)						1	G	7	2 	3U				H1NE 					 
1995033100194	19950331	00194	SW 	1995	3	31	HEEA954608 	1	19950323	G	6320	412040002113	TRANSMISSION 			BELL 	412 	412 	1182202	SW 										M/R	CHIP WARN 	E			HEEA	A				UNSCHED LANDING 				J			WARNING INDICATION 			CR	CRUISE 	1			SW	03	33008	5733 				36004				TRANSMISSION CHIP LIGHT OUTBOUND. RETURNED TO BASE. CHIP LIGHT CAME FROM PLANETARY GEAR RING. CLEANED, PENALTY RUN OK A	ND RETURNED TO SERVICE.					1	G	7	2 	4U				H4SW 					 
1995033100195	19950331	00195	NE 	1995	3	31	HEEA954609 	1	19950323	G	2840	MS3476L106S	CONNECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										FUEL QTY	DIRTY 	E			HEEA	K				NONE 				N			FALSE WARNING 			CR	CRUISE 	1			SW	03	1545K					760047				FUEL QUANTITY WENT TO ZERO IN FLIGHT. CLEANED CONNECTOR FOR FUEL PROBE.						1	G	7	2 	3U				H1NE 					 
1995033100196	19950331	00196	NE 	1995	3	31	HEEA954610 	2	19950323	G	7210	MS3126E1419P	CONNECTOR 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					NR 2 ENG CHIP	SHORTED 	E			HEEA	K				NONE 				N			FALSE WARNING 			CR	CRUISE 	1			SW	03	22608					33075				#2 ENGINE CHIP LIGHT IN FLIGHT. FOUND PINS IN CONNECTOR SHORTED. REPLACED CONNECTOR AND RETURNED TO SERVICE.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995033100197	19950331	00197	GL 	1995	3	31	HEEA954611 	2	19950323	G	7323	25246928	GOVERNOR 			BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			TO	TAKEOFF 	1			SW	03	6160Z	7083 				51610				ON TAKEOFF, N1, N2 AND ROTOR FLUCTUATIONS -- OVERTORQUE EXCEEDING 120%. REPLACED WITH SERVICEABLE GOVERNOR AND PERFORMED	 OVERTORQUE INSPECTION.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995033100198	19950331	00198		1995	3	31	HEEA954612 	4	19950323	G	3452	066104100	TRANSPONDER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546G					760076				TRANSPONDER WAS NOT WORKING. AIRCRAFT RETURNED TO BASE.						1	G	7	2 	3U				H1NE 					 
1995033100199	19950331	00199	EU 	1995	3	31	HEEA954613 	1	19950323	G	6320	4639312025	SHAFT SEAL 			BOLKMS	105 	BO105S 	5626006	EU 										TRANSMISSION	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			CR	CRUISE 	1			SW	03	4391S					S787				IN CRUISE FLIGHT, DEVELOPED LEAK FROM BOTTOM OF TRANSMISSION. REPLACED SEAL DUE TO SLIP RING RETAINER LEAKING.						1	G	7	2 	3U				H3EU 					 
1995033100200	19950331	00200	SW 	1995	3	31	HEEA954614 	1	19950323	G	2432	30703001	BATTERY 			BELL 	412 	412 	1182202	SW 										DC SYS	OVERHEAT LIGHT 	E			HEEA	K				NONE 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	03	7128R					36007				BATTERY HOT LIGHT IN FLIGHT. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	2 	4U				H4SW 					 
1995033100201	19950331	00201		1995	3	31	HEEA954615 	4	19950323	G	2312	064102300	TRANSCIEVER 			BELL 	412 	412 	1182202	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				BREAKS SQUELCH AND WILL NOT RE-SQUELCH. INSPECTED AND FOUND HEAVY CORROSION THROUGH MAIN BOARD NEAR CONNECTOR J5981. F	OUND MAIN BOARD TO BE UNREPAIRABLE. REPLACED MAIN BOARD AND 2 EACH INSULATORS. ADJUSTED POWER OUT, SIDETONE, MODULATIO	N, AND TRANSMIT COMPRESSOR. BENCH CHECK GOOD.				1	G	7	2 	4U				H4SW 					 
1995033100202	19950331	00202		1995	3	31	HEEA954616 	4	19950323	G	3453	453105004	LORAN 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31219					760230				INTERMITTENT OPERATION.						1	G	7	2 	3U				H1NE 					 
1995033100203	19950331	00203	EU 	1995	3	31	HEEA954617 	1	19950323	G	7712	642519032	TRANSMITTER 			SNIAS 	350 	AS350B2 	8680813	EU 										ENG TORQUE	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										ERRATIC TORQUE GAUGE; FLUCTUATIONS AND VIBRATION SENSITIVE. (LOOSE PARTS INSIDE)						1	G	7	1 	3U				H9EU 					 
1995033100204	19950331	00204		1995	3	31	HEEA954618 	4	19950323	G	3453	4530093	RECEIVER 		ARNAV20 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4193R					S851				DOESN'T PROVIDE NAVIGATION DATA (LED ON DISPLAY IS PEELING AND CRACKING, #3 AND "HLD" BUTTON IS STICKING INTERMITTENTLY	. FOUND LENS ON DISPLAY PEELING AND CRACKING.					1	G	7	2 	3U				H3EU 					 
1995033100205	19950331	00205	SW 	1995	3	31	HEEA954619 	1	19950323	G	5260	FYLM735023	MOTOR ASSY 		SYLC502281 	BELL 	412 	412 	1182202	SW 										STEP	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347	98 			1005	36005				WILL NOT RETRACT. VISUALLY INSPECTED AND BENCH CHECKED BY THE ACCESSORY SHOP AND FOUND UNIT INOPERATIVE. REMOVED MOTOR	 FROM UNIT. DEAD SPOT ON ARMATURE.					1	G	7	2 	4U				H4SW 					 
1995033100206	19950331	00206		1995	3	31	HEEA954620 	4	19950323	G	3457	0845000000	SKY 5000 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911TL					7198				LOSES MEMORY AFTER SHUTDOWN.						1	G	7	2 	3U				H13EU 					 
1995033100207	19950331	00207		1995	3	31	HEEA954621 	4	19950323	G	2370	9806019001	CVR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N	1657 				28106				CVR INOPERATIVE.						2	G	7	2 	4U				H10SW 					 
1995033100208	19950331	00208	EU 	1995	3	31	HEEA954622 	1	19950323	G	5610	1053001	WINDSHIELD 			BOLKMS	105 	BO105S 	5626006	EU 										LT COCKPIT	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	617					S578				WINDSHIELD LAMINATED TO THICK AND CONTOUR OF WINDOW DOES NOT MATCH AIRFRAME.						1	G	7	2 	3U				H3EU 					 
1995033100209	19950331	00209	EU 	1995	3	31	HEEA954623 	1	19950323	G	5610	1053002	WINDSHIELD 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT RT	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	617					S578				WINDSHIELD LAMINATED TO THICK AND CONTOUR OF WINDOW DOES NOT MATCH AIRFRAME.						1	G	7	2 	3U				H3EU 					 
1995033100210	19950331	00210	EU 	1995	3	31	HEEA954624 	1	19950323	G	5610	1053002	WINDSHIELD 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT RT	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	86CH					S557				WINDSHIELD CRACKED DURING INSTALLATION AT UPPER INBOARD CORNER. FOUND WINDOW TO HAVE IMPROPER FORM AND FIBERGLASS EDGIN	G TOO THICK TO ALLOW PROPER FIT ON AIRFRAME.					1	G	7	2 	3U				H3EU 					 
1995033100211	19950331	00211	EU 	1995	3	31	HEEA954625 	1	19950323	G	5610	1053002	WINDSHIELD 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT RT	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	86CH					S557				DURING INITIAL FIT OF WINDSHIELD ON AIRFRAME, FOUND WINDOW TO HAVE IMPROPER FORM AND FIBERGLASS EDGING TOO THICK TO ALL	OW PROPER FIT ON AIRFRAME.					1	G	7	2 	3U				H3EU 					 
1995033100212	19950331	00212	EU 	1995	3	31	HEEA954626 	1	19950323	G	5610	1053002	WINDSHIELD 			BOLKMS	105 	BO105CBS 	5626008	EU 										COCKPIT RT	MIS MFG 	E		A	HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5418A					S800				FOUND WINDSHIELD TO HAVE IMPROPER FORM AND FIBERGLASS EDGING TOO THICK TO ALLOW PROPER FIT ON AIRFRAME. THIS CAUSED WIN	DSHIELD TO CRACK AT UPPER INBOARD CORNER. THE CRACK APPEARED THE FOLLOWING DAY AFTER THE INSTALLATION OF WINDOW WAS COM	PLETED.				1	G	7	2 	3U			NC	H3EU 					 
1995033100213	19950331	00213	SW 	1995	3	31	HEEA954627 	1	19950323	G	5610	M2063402	WINDSHIELD 			BELL 	206 	206L3 	1182108	SW 										COCKPIT	DISTORTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3108E	2 				51498				DISTORTED IN LOWER QUARTER AND L/H UPPER QUARTER (CAUSES SERIOUS VISUAL PROBLEMS DURING APPROACHES OFFSHORE).						1	G	7	1 	3U				H2SW 					 
1995033100214	19950331	00214	SW 	1995	3	31	HEEA954628 	1	19950323	G	7722	212075067105	INDICATOR 			BELL 	212 	212 	1181420	SW 										COCKPIT ITT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5736D					31135				NEEDLE HAS NO INDICATION. TIME SINCE REPAIR 0:00.						1	G	7	1 	4U				H4SW 					 
1995033100215	19950331	00215		1995	3	31	HEEA954629 	4	19950323	G	3413	RC30VIL	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT VSI	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				NEEDLE HAS A ERRATIC OPERATION. TIME SINCE REPAIR 51:30.						1	G	7	2 	4U				H4SW 					 
1995033100216	19950331	00216		1995	3	31	HEEA954630 	4	19950324	G	3442	MI585202	ANT PEDESTAL 			SKRSKY	S76 	S76A 	8143006	NE 										RADAR ANT	BRACKET BROKEN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4253S					760035				MOUNTING BRACKET BROKEN.						1	G	7	2 	3U				H1NE 					 
1995033100217	19950331	00217		1995	3	31	HEEA954631 	4	19950324	G	2312	6222078001	TRANSCEIVER 	VHF251 		BOLKMS	105 	BO105C 	5626005	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3535T					S113				KNOB LOOSE.						1	G	7	2 	3U				H3EU 					 
1995033100218	19950331	00218	EU 	1995	3	31	HEEA954632 	1	19950324	G	6720	11731822	PITCH LINK ASSY 			BOLKMS	117 	BK117B2 	5626013	EU 										T/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	992 				7234				WORN BEARINGS.						1	G	7	2 	3U			NC	H13EU 					 
1995033100219	19950331	00219	EU 	1995	3	31	HEEA954633 	1	19950324	G	6710	10513141	ROD END ASSY 			BOLKMS	117 	BK117B2 	5626013	EU 										M/R	WORN BEARINGS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	992 				7234				WORN BEARINGS.						1	G	7	2 	3U			NC	H13EU 					 
1995033100220	19950331	00220	EU 	1995	3	31	HEEA954634 	1	19950324	G	6700	1054661114	BELLOWS 			BOLKMS	117 	BK117B2 	5626013	EU 										ACTUATOR	DRY ROT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	992 				7234				DRY ROTTED AND CRACKING.						1	G	7	2 	3U			NC	H13EU 					 
1995033100221	19950331	00221	GL 	1995	3	31	HEEA954635 	2	19950324	G	7261	MS9372019	SEAL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					OIL NOZZLE "T"	LEAKING 	E		A	HEEA	O				OTHER 				A	K		FLAME/FIRE 	FLUID LOSS 		NR	NOT REPORTED 	1			SW	03	27702				CAT70676	45300				PILOT REPORTED A FIRE IN ENGINE COMPARTMENT. THE FIRE FLASHED, THEN EXTINGUISHED. INVESTIGATION REVEALED OIL LEAK AT 6 	& 7 OIL NOZZLE "T" FITTING. REPLACED SEAL ASSEMBLY AND RETURNED ENGINE TO SERVICE.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995033100222	19950331	00222	EU 	1995	3	31	HEEA954636 	1	19950324	G	7160	6893660	ENGINE ASSY 			BOLKMS	105 	BO105S 	5626006	EU 										INLET	OBSTRUCTED 	E		A	HEEA	K				NONE 				M			OVER TEMP 			CR	CRUISE 	1			SW	03	86CH	6691 				S557				#1 ENGINE T.O.T. INCREASED TO 800 DEGREES CELCIUS IN CRUISE. FOUND AN APPROXIMATELY 4 X 4 INCH PIECE OF CHAFE TAPE OBSTR	UCTING THE INLET. REPAIRED ENGINE AND RETURNED TO SERVICE.					1	G	7	2 	3U				H3EU 					 
1995033100223	19950331	00223	GL 	1995	3	31	HEEA954637 	2	19950324	G	7210	6893660	ENGINE ASSY 			BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					NR 1	CHIP LIGHT 	E			HEEA	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	7136J	4876 				S830				#1 ENGINE CHIP LIGHT CAME ON IN FLIGHT. (FOUND METAL ON THE LOWER PLUG) INSTALLED SERVICEABLE ENGINE AND RETURNED AIRCR	AFT TO SERVICE.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995033100224	19950331	00224	NE 	1995	3	31	HEEA954638 	1	19950324	G	2120	7620001012103	FLAP VALVE 			SKRSKY	S76 	S76A 	8143006	NE 										FRESH AIR BOX	LEAKING 	E			HEEA	K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			CR	CRUISE 	1			SW	03	1546G					760076				WHILE IN CRUISE FLIGHT, LORAN C CONTROL HEAD BECAME INOPERATIVE AND EMITTED SOME SMOKE. FOUND WATER LEAKING OVERHEAD FRO	M FRESH AIR BOX. AIR INLET TO BOX IS COLD AIR FLAP VALVE P/N 76200-01012-103. REPAIRED LEAK.					1	G	7	2 	3U				H1NE 					 
1995040700323	19950407	00323	GL 	1995	4	7	HEEA954639 	2	19950328	G	7230	23008090	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	706AE	641 			CAC90530	760275	CAE890508S			ENGINE REMOVED DUE TO N1 SHAFTING INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYON	D LMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEARSHAFT.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995040700324	19950407	00324	SW 	1995	4	7	HEEA954640 	1	19950328	G	6220	412010179105	CONE 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347	3793 			AAD50064	36005				LOWER CONE TEFLON DAMAGED.						1	G	7	2 	4U				H4SW 					 
1995040700325	19950407	00325	SW 	1995	4	7	HEEA954641 	1	19950328	G	6220	412010124109	BOLT 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	COAT FLAKE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347	1423 			AAD50064	36005				CARBIDE COATING FLAKING BEYOND LIMITS. BOLT S/N A81, A599, A566.						1	G	7	2 	4U				H4SW 					 
1995040700326	19950407	00326	EU 	1995	4	7	HEEA954642 	1	19950328	G	6320	704A34543009	CHIP DETECTOR 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R XMSN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	597 				2777				INTERMITTENT FALSE AND DIM LIGHT INDICATION.						1	G	7	1 	3U				H9EU 					 
1995040700327	19950407	00327	GL 	1995	4	7	HEEA954643 	1	19950328	G	6710	206062721105	ACTUATOR 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					DROOP COMP	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	466 				23009				ACTUATOR INOPERATIVE; NO MOVEMENT OF MOTOR.						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995040700328	19950407	00328		1995	4	7	HEEA954644 	4	19950328	G	3414	22697061	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT AIR SPD	STICKING 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5742N					45477				INDICATOR STICKING. REPLACED WITH SERVICEABLE INDICATOR.						1	G	7	1 	3U				H2SW 					 
1995040700329	19950407	00329	SW 	1995	4	7	HEEA954645 	1	19950328	G	6340	60001	INDICATOR 		206040015103	BELL 	206 	206B3 	1181506	SW 										DR SHAFT	PEELING 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268V	76 			A1077	3605				PEELING OVERTEMP INDICATOR. REPLACED INPUT DRIVE SHAFT AND RETURNED TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995040700330	19950407	00330	EU 	1995	4	7	HEEA954646 	1	19950328	G	6210	10514101111	BLADE BOLTS 			BOLKMS	117 	BK117B2 	5626013	EU 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	992 				7234				SECONDARY BLADE BOLTS FOUND WORN BEYOND LIMITS ON INSPECTION. REPLACED WITH SERVICEABLE BLADE BOLTS AND RETURNED TO SER	VICE. S/N PHI513 & PHI 514					1	G	7	2 	3U			NC	H13EU 					 
1995040700331	19950407	00331	NE 	1995	4	7	HEEA954647 	2	19950328	G	7323	25249994	GOVERNOR SHAFT 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					FREE TURBINE	BINDING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3911L					33023				FREE TURBINE GOV THROTTLE SHAFT BINDING.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995040700332	19950407	00332	EU 	1995	4	7	HEEA954648 	1	19950328	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117B2 	5626013	EU 										NR 1 FUEL	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	992 				7234				#1 SUPPLY NEEDLE WOULD NOT GO ABOVE ONE GALLON.						1	G	7	2 	3U			NC	H13EU 					 
1995040700333	19950407	00333	EU 	1995	4	7	HEEA954649 	1	19950328	G	5210	1172433901	LATCH ASSY 			BOLKMS	117 	BK117B2 	5626013	EU 										DOOR	BROKEN SPRING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	134AE	895 				7237				BROKEN EJECTION SPRING OF LATCH REQUIRES TWO HANDS TO OPERATE LATCH ASSY. REPLACED WITH SERVICEABLE LATCH ASSY AND RETUR	NED TO SERVICE.					1	G	7	2 	3U			NC	H13EU 					 
1995040700334	19950407	00334		1995	4	7	HEEA954651 	4	19950329	G	3451	066107001	TRANCEIVER 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT DME	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5196T					7152				DME IS INOPERATIVE. REPLACED BURNT F401 FUSE AND REPLACED DEFECTIVE INSULATOR ON Q203 TRANSISTOR. REPAIRED PROBLEM.						1	G	7	2 	3U				H13EU 					 
1995040700335	19950407	00335		1995	4	7	HEEA954652 	4	19950329	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B3 	1181506	SW 										COCKPIT ATC	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2270G					3610				WHEN SET ON 60.33, TRANSPONDER PUTS OUT FREQUENCY 1200. FOUND WEAK POWER OUT. REPLACED CAVITY OSCILLATOR V101. REPAIRE	D. REPLACED DAMAGED TRANSISTOR Q415 AND INSTALLED HEATSINK BEHIND Q415 AS PER KING SERVICE AID KT76A-6. REPLACED DETER	IORATED RESISTOR R477. UNIT HAS WEAK RECEIVER SENSE. REPLACED MIXER DIODE CR202. REPAIRED. ADJUSTED POWER OUT AND FRE	QUENCY. BENCH CHECK GOOD.			1	G	7	1 	3U				H2SW 					 
1995040700336	19950407	00336		1995	4	7	HEEA954653 	4	19950329	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748Q					45499				KNOB WILL NOT TURN TO TEST. VERIFIED. REPLACED FACEPLATE ASSEMBLY DUE TO KNOB BROKEN. INSTALLED HEATSINK DUE TO SERVIC	E BULLETIN KT76A-6. REPLACED CAVITY OSCILLATOR V101 DUE TO WEAK POWER. REPLACED V301 PHOTOCELL DUE TO BEING WEAK. REP	LACED DETERIORATED R477 RESISTOR.REPAIRED.				1	G	7	1 	3U				H2SW 					 
1995040700337	19950407	00337	SW 	1995	4	7	HEEA954657 	1	19950330	G	6322	214076333107	MOTOR 			BELL 	214 	214ST 	1182106	SW 										BLOWER	DEFECTIVE 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5748M					28102				MOTOR CAUSES LOUD NOISE AND VIBRATION. (RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94)						2	G	7	2 	4U				H10SW 					 
1995040700338	19950407	00338	SW 	1995	4	7	HEEA954658 	1	19950330	G	6322	214076333107	MOTOR 			BELL 	214 	214ST 	1182106	SW 										BLOWER	DEFECTIVE 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5748M					28102				MOTOR CAUSES LOUD NOISE AND VIBRATION. TIME SINCE REPAIR 0:00.						2	G	7	2 	4U				H10SW 					 
1995040700339	19950407	00339		1995	4	7	HEEA954659 	4	19950330	G	3417	214175421101	COMPUTER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT AIR DATA	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5748M	72 				28102				WON'T TEST; CAN'T CHANGE GROSS WEIGHT BELOW 16500 AND VNE WON'T CHANGE.						2	G	7	2 	4U				H10SW 					 
1995040700340	19950407	00340	SW 	1995	4	7	HEEA954664 	1	19950331	G	6220	206010110105	WASHER 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2249Z	1182 			HB400	45753				EXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO DETERIORATE. SCRAPPED LOCALLY. APPLIED LOWER TORQUE ON ADJUSTMENT SCREWS AN	D LOWER PRELOAD ON THRUST PLUGS.					1	G	7	1 	3U				H2SW 					 
1995040700341	19950407	00341	SW 	1995	4	7	HEEA954665 	1	19950331	G	6220	412010145103	DAMPER SET 		412010100193	BELL 	412 	412 	1182202	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347	1304 			AAD50064	36005				DAMPER SET CAUSING LEAD/LAG PROBLEMS. SEE MMIR # 4666 FOR ADDITIONAL DAMPER SETS REMOVED. S/N LK2881 & LK2880						1	G	7	2 	4U				H4SW 					 
1995040700342	19950407	00342	SW 	1995	4	7	HEEA954666 	1	19950331	G	6220	412010145103	DAMPER SET 		412010100193	BELL 	412 	412 	1182202	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347	1304 			AAD50064	36005				DAMPER SET CAUSING LEAD/LAG PROBLEMS. RADS READINGS SENT FOR YOUR CONVENIENCE OF TESTING. SEE MMIR # 4665 FOR ADDITIO	NAL DAMPER SETS REMOVED. S/N LK2922 & LK2914					1	G	7	2 	4U				H4SW 					 
1995041400078	19950414	00078	EU 	1995	4	14	HEEA954667 	1	19950403	G	2910	105450121	HYD PACK 			BOLKMS	105 	BO105LSA3 	5626020	EU 										NR 1 SYS	WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	202LF	1769 				2014				LATERAL PLAY ON #1 SYSTEM. LONGITUDINAL AND COLLECTIVE INPUT LEVERS EXCEEDED .5MM.						1	G	7	2 	3U				H3AU 					 
1995041400079	19950414	00079		1995	4	14	HEEA954668 	4	19950404	G	2210	214074303115	AMPLIFIER ASSY 			BELL 	214 	214ST 	1182106	SW 										AUTOFLIGHT	DEFECTIVE 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5748M					28102				PITCH MOTORS FORWARD IN FLIGHT AND WON'T TEST PROPERLY. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995041400080	19950414	00080	GL 	1995	4	14	HEEA954669 	2	19950404	G	7230	23008090	GEARSHAFT 		23005290 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122H	678 			CAC90180	760233	CAE890176S			ENGINE REMOVED DUE TO CYCLED 1ST AND 2ND STAGE WHEELS. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP W	EAR BEYOND SPECS ON SPUR ADAPTER GEARSHAFT FWD AND AFT SPLINES AND STEP WEAR ON INTERNAL SPLINES OF SPLINE ADAPTER BEYON	D SPECS. INSTALLED NEW SPUR ADAPTER GEARSHAFT AND SPLINE ADAPTER. SEE MMIR #4670 FOR SPLINE ADAPTER INFORMAITON.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995041400081	19950414	00081	GL 	1995	4	14	HEEA954670 	2	19950404	G	7230	230052711	SPLINE ADAPTER 		23005290 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					COMPRESSOR	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122H	678 			CAC90180	760233	CAE890176S			ENGINE REMOVED DUE TO CYCLED 1ST AND 2ND STAGE WHEELS. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP W	EAR BEYOND SPECS ON SPUR ADAPTER GEARSHAFT FWD AND AFT SPLINES AND STEP WEAR ON INTERNAL SPLINES OF SPLINE ADAPTER BEYON	D SPECS. INSTALLED NEW SPUR ADAPTER GEARSHAFT AND SPLINE ADAPTER. SEE MMIR #4669 FOR SPUR ADAPTER GEARSHAFT INFORMATI	ON.			1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995041400082	19950414	00082	GL 	1995	4	14	HEEA954671 	2	19950404	G	7250	23032345	N1 COUPLING 		23035128 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					TURBINE	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122H	678 			CAT90574	760233	CAE890176S			ENGINE REMOVED DUE TO CYCLED 1ST AND 2ND STAGE WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: FWD AND A	FT SPLINE STEP WEAR BEYOND LIMITS ON N1 COUPLING. INSTALLED NEW COUPLING.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995041400083	19950414	00083	SW 	1995	4	14	HEEA954672 	1	19950404	G	6220	206010110105	WASHER 		206011100150	BELL 	206 	206L3 	1182108	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X	1150 			A572	51495				EXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO DETERIORATE. PARTS SCRAPPED LOCALLY. APPLIED LOWER TORQUE ON ADJUSTING SCRE	WS AND LOWERED PRELOAD ON THRUST PLUGS.					1	G	7	1 	3U				H2SW 					 
1995041400084	19950414	00084	NE 	1995	4	14	HEEA954673 	2	19950404	G	7421	9560147770	IGNITOR 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1C 	60030	NE 					ENG LT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	615 				2777				DURING ROUTINE INSPECTION NOTED LH IGNITER DID NOT FIRE.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995041400085	19950414	00085	EU 	1995	4	14	HEEA954674 	1	19950404	G	6230	704A33699008	BOOT 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6097Z	384 				2820				BOOT DETERIORATED AND TORN.						1	G	7	1 	3U				H9EU 					 
1995041400086	19950414	00086	EU 	1995	4	14	HEEA954676 	1	19950404	G	2121	420800001	BLOWER 			SNIAS 	350 	AS350B2 	8680813	EU 										AIR DIST	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	937 				2653				BLOWER INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995041400087	19950414	00087	EU 	1995	4	14	HEEA954677 	1	19950404	G	6520	350A33215300	BEARING 		350A33211905	SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	873 				2653				BEARING WORN.						1	G	7	1 	3U				H9EU 					 
1995041400088	19950414	00088	SW 	1995	4	14	HEEA954679 	1	19950405	G	5313	212030128153	LONGERON 		212030100133	BELL 	412 	412 	1182202	SW 										STA 101.38	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	21498	7369 			36001	36003				LONGERON HAS DEEP CORROSION AT STATION 101.38 SPLICE AS SEEN IN UPPER R/H AFT CORNER OF BAGGAGE COMPARTMENT, JUST OUTBOA	RD OF WHERE THE BAGGAGE COMPARTMENT CEILING PANEL ATTACHES TO LONGERON. REPLACED WITH SERVICEABLE LONGERON ASSY AND RETU	RNED TO SERVICE.				1	G	7	2 	4U				H4SW 					 
1995041400089	19950414	00089	SW 	1995	4	14	HEEA954680 	1	19950405	G	6320	206040190005	PUMP 			BELL 	206 	206L1 	1182107	SW 										TRANSMISSION	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2245Y					45751				FRONT SEAL ON PUMP LEAKING OIL. REPLACED WITH SERVICEABLE PUMP ASSEMBLY.						1	G	7	1 	3U				H2SW 					 
1995041400090	19950414	00090		1995	4	14	HEEA954681 	4	19950405	G	3453	453105004	LORAN 	ARNAV 	R501 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5426U					760167				MUST PRESS ENTER BUTTON SEVERAL TIMES BEFORE IT FUNCTIONS PROPERLY. CLEANED ENTER BUTTON AND CONTACT. BUTTON WORKS EVE	RY TIME BUT ONLY WHEN PUSHED IN CENTER. WORKS INTERMITTENTLY WHEN PUSHED ON SIDES.					1	G	7	2 	3U				H1NE 					 
1995041400091	19950414	00091	SW 	1995	4	14	HEEA954682 	1	19950405	G	5302	206031329101	FITTING 			BELL 	206 	206L3 	1182108	SW 										TAILBOOM	BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3116P	5933 				51530				UPPER L/H CASTING BROKEN INTO THREE SEPARATE PIECES. SCRAPPED PART.						1	G	7	1 	3U				H2SW 					 
1995041400092	19950414	00092	SW 	1995	4	14	HEEA954683 	1	19950405	G	5302	206032308003	FRAME 			BELL 	206 	206L3 	1182108	SW 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3116P	5933 				51530				TAILBOOM RING CRACKED IN SEVERAL PLACES ON UPPER L/H ATTACHMENT POINT. SCRAPPED PART. SENT TO BELL HELICOPTER-CANADA, A	TTENTION: CLAUDE PAQUETTE PER HIS REQUEST FOR EVALUATION.					1	G	7	1 	3U				H2SW 					 
1995041400093	19950414	00093	SW 	1995	4	14	HEEA954684 	1	19950405	G	5320	205030710008P	FITTING 			BELL 	412 	412 	1182202	SW 										FUSELAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22608	14171				33075				FITING CRACKED AT CENTER INBOARD EDGE AT RIVET HOLE OF ADEL WITH NO EDGE DISTANCE. REMOVED AND REPLACED FITTING AND SHIM	S AS NEEDED. SUBMITTER SUGGESTS SHIM PROPERLY, ALLOW FOR PROPER EDGE DISTANCE, AND DEBURR ALL HOLES.					1	G	7	2 	4U				H4SW 					 
1995041400094	19950414	00094	EU 	1995	4	14	HEEA954685 	1	19950405	G	3340	356H2802	POWER SUPPLY 			SNIAS 	350 	AS350B2 	8680813	EU 										ANTI COLL LIGHT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6097Z	410 				2820				ANTI-COLLISION LIGHT INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995041400095	19950414	00095		1995	4	14	HEEA954686 	4	19950405	G	3417	214175421101	COMPUTER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT ADC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				1ST DIGIT IN GROSS WEIGHT INOPERATIVE.						2	G	7	2 	4U				H10SW 					 
1995041400096	19950414	00096	EU 	1995	4	14	HEEA954687 	1	19950405	G	2435	150SG122Q	GENERATOR 			SNIAS 	350 	AS350B2 	8680813	EU 										START/GEN	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	343 				2653				STARTER GENERATOR FUNCTIONS INTERMITTENTLY.						1	G	7	1 	3U				H9EU 					 
1995041400097	19950414	00097	SW 	1995	4	14	HEEA954688 	1	19950405	G	2913	214076334105	PUMP 			BELL 	214 	214ST 	1182106	SW 										HYD SYS	DEFECTIVE 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5748M					28102				HYD PUMP CAUSING VIBRATION.						2	G	7	2 	4U				H10SW 					 
1995041400098	19950414	00098	SW 	1995	4	14	HEEA954689 	1	19950405	G	7810	206064300005	EXHAUST 			BELL 	206 	206L1 	1182107	SW 										WELDED SEAM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5745N	234 				45489				EXHAUST CRACKED AT WELDED SEAM UPWARDS.						1	G	7	1 	3U				H2SW 					 
1995041400099	19950414	00099	SW 	1995	4	14	HEEA954690 	1	19950405	G	6520	206340103101	SEAL 		206040402003	BELL 	206 	206L1 	1182107	SW 										T/R GR BOX	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	3892R	42 			AFS2435	45594				INSTALLED NEW SEAL IN T/R GEARBOX. SEAL WAS LEAKING A LITTLE THE NEXT DAY AND CONTINUED TO GET WORSE UNTIL IT WAS CHANGE	D WITH 42 HOURS ON IT.					1	G	7	1 	3U				H2SW 					 
1995041400100	19950414	00100	SW 	1995	4	14	HEEA954691 	1	19950405	G	6520	206340103101	SEAL 		206040402003	BELL 	206 	206L1 	1182107	SW 										T/R GR BOX	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	3892R	99 			AFS2435	45594				INSTALLED NEW SEAL IN T/R GEARBOX. SEAL WAS LEAKING A LITTLE THE NEXT DAY AND CONTINUED TO GET WORSE UNTIL IT WAS CHANGE	D WITH 99 HOURS ON IT.					1	G	7	1 	3U				H2SW 					 
1995041400101	19950414	00101	GL 	1995	4	14	HEEA954692 	2	19950406	G	7210	6876925	TUBE ASSY. 		23001938 	AEROSP	AS355 	AS355F1 	8680810	EU 	ALLSN 	250C 	250C20B 	03013	GL 					GR BOX	DEFECTIVE 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	57906	8674 			CAG40092	5107	CAE840091			ENGINE WAS REMOVED DUE TO OIL LEAK AT AFT T/M BUSHING. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: OIL TRANS	FER TUBE FAILED DIMENSIONAL CHECK IN ACCORDANCE WITH CEB 1307. INSTALLED NEW TUBE ASSEMBLY.					1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1995041400102	19950414	00102	SW 	1995	4	14	HEEA954693 	1	19950406	G	2450	M833830211	BREAKER 			BELL 	214 	214ST 	1182106	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				BREAKER WILL NOT CLOSE. RECEIVED INSTALLED ON AIRCRAFT N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995041400103	19950414	00103		1995	4	14	HEEA954694 	4	19950406	G	3453	066402601	LORAN 		KLN88 	BELL 	230 	230 	1182149	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN					23009				LORAN INTERMITTENTLY LOSES PROGRAM.						1	G	7	2 	3U			NC	H9SW 					 
1995041400104	19950414	00104	SW 	1995	4	14	HEEA954700 	1	19950407	G	6220	206010110105	WASHER 		206011100149	BELL 	206 	206B 	1181511	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2272V	1173 			A2056	3621				EXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO DETERIORATE. APPLIED LOWER TORQUE ON ADJUSTING SCREWS AND LOWERED PRELOAD ON	 THRUST PLUGS. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995041400105	19950414	00105	SW 	1995	4	14	HEEA954701 	1	19950407	G	2430	214175133101	RELAY 			BELL 	214 	214ST 	1182106	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				CONTACTS BURNED. RECEIVED INSTALLED ON N5748M, S/N 28102 ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995041400106	19950414	00106	SW 	1995	4	14	HEEA954702 	1	19950407	G	6330	206033552001	STOP ASSY 			BELL 	206 	206L 	1181522	SW 										XMSN MOUNT	SEPARATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W	1575 				52033				RUBBER COMPLETELY SEPARATED FROM METAL IN BOTH STOP ASSEMBLIES.						1	G	7	1 	3U				H2SW 					 
1995041400107	19950414	00107	GL 	1995	4	14	HEEA954703 	2	19950407	G	7210	23056128	GEARSHAFT 		23001938 	AEROSP	AS355 	AS355F1 	8680810	EU 	ALLSN 	250C 	250C20F 	03013	GL 					ENG GR BOX	SPALLED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5796T	361 			CAG40449	5166	CAE840100			ENGINE REMOVED DUE TO MAIN ENGINE DRIVESHAFT FAILURE. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: SPALLING O	N GEAR TEETH OF BOTH GEARSHAFTS. INSTALLED NEW GEARSHAFT. SEE MMIR #4704 FOR OTHER GEARSHAFT INFORMATION.					1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1995041400108	19950414	00108	GL 	1995	4	14	HEEA954704 	2	19950407	G	7210	6896437	GEARSHAFT 		23001938 	AEROSP	AS355 	AS355F1 	8680810	EU 	ALLSN 	250C 	250C20F 	03013	GL 					ENG GR BOX	SPALLED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5796T	361 			CAG40449	5166	CAE840100			ENGINE REMOVED DUE TO MAIN ENGINE DRIVESHAFT FAILURE. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: SPALLING O	N GEARTEETH OF BOTH GEARSHAFTS. INSTALLED NEW GEARSHAFT. SEE MMIR #4703 FOR OTHER GEARSHAFT INFORMATION.					1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1995041400109	19950414	00109		1995	4	14	HEEA954705 	4	19950407	G	3453	4530103	LORAN 	ARNAV 	ARNAV21 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5421E					S806				SLOW TO WARM UP. LOSES ITSELF. SENT TO ARNAV SYSTEMS FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H3EU 					 
1995041400110	19950414	00110		1995	4	14	HEEA954706 	4	19950407	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K	4144 				36001				CVR TEST LIGHT COMES ON IN FLIGHT.						1	G	7	2 	4U				H4SW 					 
1995041400111	19950414	00111	EU 	1995	4	14	HEEA954707 	1	19950407	G	7722	TM42739	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT EGT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										INDICATOR READS BACKWARDS.						1	G	7	2 	3U				H3EU 					 
1995041400112	19950414	00112	SW 	1995	4	14	HEEA954708 	1	19950407	G	5610	M2063402	WINDSHIELD 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5000K					45167				WINDHSIELD IS SHORT ON EDGE DISTANCE ON THE UPPER OUTBOARD CORNER.						1	G	7	1 	3U				H2SW 					 
1995041400113	19950414	00113		1995	4	14	HEEA954709 	4	19950407	G	2312	064102300	TRANSCIEVER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VHF	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	707AE					760276				PILOT REPORTS NO TRANSMITTER OUTPUT. FOUND CORROSION HAD EATEN THROUGH MAINBOARD UNDER HEADER J304. FOUND MAIN BOARD TO	 BE UNREPAIRABLE. REPLACED MAINBOARD. CLEANED CORROSION ON CHASIS AND ALODYNED. ADJUSTED SQUELCH, MODULATION, FREQUEN	CY, TRANSMIT COMPRESSOR, SIDETONE AND POWER OUT.BENCH CHECK GOOD.				1	G	7	2 	3U				H1NE 					 
1995041400114	19950414	00114	EU 	1995	4	14	HEEA954710 	1	19950407	G	6520	350A33200403	SPIDER 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	BEARING FAULTY 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1063 				2771				BEARING SLINGING GREASE.						1	G	7	1 	3U				H9EU 					 
1995041400115	19950414	00115	EU 	1995	4	14	HEEA954711 	1	19950407	G	7160	350A54108004	INLET 			SNIAS 	350 	AS350B2 	8680813	EU 										ENG INTAKE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	615 				2777				DURING ROUTINE INSPECTION, NOTED CRACK ON LOWER PORTION OF ENGINE INLET.						1	G	7	1 	3U				H9EU 					 
1995041400116	19950414	00116		1995	4	14	HEEA954713 	4	19950407	G	2370	9806019001	CVR 			BEECH 	200 	200CBEECH 	1152926	CE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	39PH	2424 				BL3				BEGAN TRANSCRIBING TAPE AND FOUND CVR TO DIE AFTER 30-45 SECONDS OF OPERATION.						1	L	7	2 	4T				A24CE 					 
1995041400117	19950414	00117		1995	4	14	HEEA954714 	4	19950407	G	3414	8000A	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT AIR SPD	READS HIGH 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5742N					45477				NEEDLE INDICATES 5 MPH HIGH AT 100 MPH.						1	G	7	1 	3U				H2SW 					 
1995041400118	19950414	00118		1995	4	14	HEEA954715 	4	19950407	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				INDICATOR COURSE DIGITAL OFF.						1	G	7	2 	4U				H4SW 					 
1995041400119	19950414	00119		1995	4	14	HEEA954716 	4	19950407	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	3893P	2590 				33012				CVR DOESN'T TEST CORRECTLY.						1	G	7	2 	4U				H4SW 					 
1995041400120	19950414	00120	SW 	1995	4	14	HEEA954717 	1	19950407	G	2842	206364601101	TRANSMITTER 			BELL 	206 	206L 	1181522	SW 										FUEL QTY	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			CR	CRUISE 	1			SW	03	7074W	1598 				52033				AIRCRAFT EXPERIENCES A 100-150 LB MOVEMENT OF FUEL QUANTITY INDICATION IN CRUISE FLIGHT.						1	G	7	1 	3U				H2SW 					 
1995041400121	19950414	00121		1995	4	14	HEEA954718 	4	19950407	G	3414	355A82122001	INDICATOR 			AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT AIR SPD	GLASS CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5796S					5164				UNIT HAS VERTICAL CRACKS IN GLASS.						1	G	7	2 	3U				H11EU 					 
1995041400122	19950414	00122		1995	4	14	HEEA954719 	4	19950407	G	3413	38210490	INDICATOR 			AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT VSI	GLASS CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5796S					5164				UNIT HAS VERTICAL CRACKS IN GLASS. SENT TO AVIATION AVIONICS & INSTR. CORP FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H11EU 					 
1995042100138	19950421	00138	NE 	1995	4	21	HEEA954720 	1	19950410	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76A 	8143006	NE 										M/R BLADE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5444X					760174				TIP CAP HAS A PREVIOUS REPAIR THAT HAS COLLAPSED AND HAS EXCESSIVE PAINT PEELING.						1	G	7	2 	3U				H1NE 					 
1995042100139	19950421	00139		1995	4	21	HEEA954721 	4	19950410	G	3421	258719343	GYRO 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5435V					760158				PILOT AND CO-PILOT HSI OSCILLATING EXCESSIVELY.						1	G	7	2 	3U				H1NE 					 
1995042100140	19950421	00140	SW 	1995	4	21	HEEA954722 	1	19950410	G	7722	12444412	INDICATOR 			BELL 	206 	206B 	1181511	SW 										COCKPIT TOT	READS HIGH 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										INDICATES 100 DEGREES HIGH AT 900 DEGREES. TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW 					 
1995042100141	19950421	00141	SW 	1995	4	21	HEEA954723 	1	19950410	G	2436	206075447007	VOLT REGULATOR 			BELL 	206 	206L1 	1182107	SW 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2246Q					45752				GENERATOR COMES OFF LINE 8 TIMES IN 45 MINUTES OF FLIGHT.						1	G	7	1 	3U				H2SW 					 
1995042100142	19950421	00142		1995	4	21	HEEA954724 	4	19950410	G	3422	5222644011	AMPLIFIER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT DG	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	352TT					S59				TROUBLESHOOTING FROZEN D.G., CARD FOUND SLAVING AMPLIFIER BAD.						1	G	7	2 	3U				H3EU 					 
1995042100143	19950421	00143		1995	4	21	HEEA954725 	4	19950410	G	3422	5223241000	GYRO COMPASS 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	352TT					S59				TROUBLESHOOTING FROZEN D.G. CARD, FOUND GYRO COMPASS DEFECTIVE.						1	G	7	2 	3U				H3EU 					 
1995042100144	19950421	00144	SW 	1995	4	21	HEEA954726 	1	19950410	G	7330	206075676101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2246Q					45752				FUEL PRESSURE NEEDLE WILL NOT INDICATE.						1	G	7	1 	3U				H2SW 					 
1995042100145	19950421	00145	EU 	1995	4	21	HEEA954727 	1	19950410	G	7722	50061036	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT EXH TEMP	READS HIGH 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	91070					S145				NEEDLE INDICATES 20 DEGREES CELSIUS HIGH THROUGHOUT SCALE.						1	G	7	2 	3U				H3EU 					 
1995042100146	19950421	00146	EU 	1995	4	21	HEEA954728 	1	19950410	G	7933	TM41039	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										TRIPLE OIL TEMP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5421E					S806				#2 NEEDLE READS LOW BELOW TOLERANCE.						1	G	7	2 	3U				H3EU 					 
1995042100147	19950421	00147	EU 	1995	4	21	HEEA954729 	1	19950410	G	7933	TM41039	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										TRIPLE OIL TEMP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5421E					S806				ROTOR AND #2 NEEDLE BOUNCES.						1	G	7	2 	3U				H3EU 					 
1995042100148	19950421	00148	EU 	1995	4	21	HEEA954730 	1	19950410	G	2840	81141010010	TRANSMITTER 			AEROSP	AS355 	AS355F1 	8680810	EU 										FUEL SYS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y					5141				TRANSMITTER OUTPUT READS ZERO. TIME SINCE REPAIR 42:00.						1	G	7	2 	3U				H11EU 					 
1995042100149	19950421	00149		1995	4	21	HEEA954731 	4	19950410	G	2210	2593996333	TARSYN 333 			BELL 	412 	412 	1182202	SW 										COCKPIT	FAILS TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	2149S					36002				VG HAS NOISY BEARING AND FAILS 6.7 TEST ON SST.						1	G	7	2 	4U				H4SW 					 
1995042100150	19950421	00150		1995	4	21	HEEA954732 	4	19950410	G	3421	4021541671	ARTIFICIAL HORIZ			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT	FAILS TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5196T					7152				FAILS TEST 3.2, 4.2, 4.4, 4.7, 4.8, 4.9 AND 8.1 TO 13.4 ON SST.						1	G	7	2 	3U				H13EU 					 
1995042100151	19950421	00151		1995	4	21	HEEA954733 	4	19950410	G	2211	4025008918	COMPUTER 			BELL 	412 	412 	1182202	SW 										COCKPIT AFCS	FAILS TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	22347					36005				FAILED SAS ENGAGE LOGIC TEST 3.2 ON SST.						1	G	7	2 	4U				H4SW 					 
1995042100152	19950421	00152		1995	4	21	HEEA954734 	4	19950410	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	STUCK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2298Z					33077				HUNDREDS AND TENS ON COURSE SELECT STUCK.						1	G	7	2 	4U				H4SW 					 
1995042100153	19950421	00153	EU 	1995	4	21	HEEA954735 	1	19950410	G	6410	355A12003114	BLADES 			AEROSP	AS355 	AS355F1 	8680810	EU 										T/R	PAINT PEEL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5774M	959 				5009				PAINT PEELING OFF TIPS SPOT ON TARGET BLADE LEADING EDGE S.B. 64.03 UNABLE TO VERIFY.						1	G	7	2 	3U				H11EU 					 
1995042100154	19950421	00154	SW 	1995	4	21	HEEA954736 	1	19950410	G	5530	206020113117	FIN ASSY 			BELL 	206 	206L1 	1182107	SW 										TAIL BOOM	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1078D					45397				FIN ASSY CORRODED, TOO HEAVY AT 19.69 LBS.						1	G	7	1 	3U				H2SW 					 
1995042100155	19950421	00155		1995	4	21	HEEA954737 	4	19950410	G	2562	ELT910	ELT 	NARCO 		BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3071K					S859				ELT WON'T SHUT OFF. DISONNECTED BATTERY. SENT TO NARCO AVIONICS FOR INSPECTION AND REPAIR. TIME SINCE REPAIR 215:15.						1	G	7	2 	3U				H3EU 					 
1995042100156	19950421	00156		1995	4	21	HEEA954738 	4	19950410	G	3416	A30	ALT ENCODER 	ACK 		BELL 	206 	206B 	1181511	SW 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2272V					3621				ENCODER IS 160 FEET OFF, ONLY WHEN COMING DOWN. WILL NOT CALIBRATE.						1	G	7	1 	3U				H2SW 					 
1995042100157	19950421	00157		1995	4	21	HEEA954739 	4	19950410	G	2211	4025008918	COMPUTER 			BELL 	412 	412 	1182202	SW 										COCKPIT AFCS	FAILS TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	3893S					33022				FAILS TEST #15.2 ON SST; NO POWER OUTPUT.						1	G	7	2 	4U				H4SW 					 
1995042100158	19950421	00158		1995	4	21	HEEA954740 	4	19950410	G	3120	M87714	CLOCK 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT MASTER	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5196T					7152				CLOCK WILL NOT COME ON.						1	G	7	2 	3U				H13EU 					 
1995042100159	19950421	00159	SW 	1995	4	21	HEEA954741 	1	19950410	G	6330	206033506101	RESTRAINT 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	WORN BEARINGS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6603X					51412				WORN BEARINGS AND FLEX CRACK.						1	G	7	1 	3U				H2SW 					 
1995042100160	19950421	00160		1995	4	21	HEEA954742 	4	19950410	G	3421	1113034	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT ATTITUDE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2298Z					33077				HORIZONTAL POINTER WILL NOT GO FULL SCALE.						1	G	7	2 	4U				H4SW 					 
1995042100161	19950421	00161		1995	4	21	HEEA954745 	4	19950410	G	2562	ELT1104	ELT 	NARCO 																COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		61 								ELT UNIT COMES ON BY ITSELF AND WILL NOT TURN OFF.																			 
1995042100162	19950421	00162	SW 	1995	4	21	HEEA954746 	1	19950410	G	7810	212061201011	EJECTOR 			BELL 	412 	412 	1182202	SW 										LT EXH	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	33008					36004				EJECTOR UNIT CRACKED.						1	G	7	2 	4U				H4SW 					 
1995042100163	19950421	00163	SW 	1995	4	21	HEEA954747 	1	19950410	G	7810	212061201012	EJECTOR 			BELL 	412 	412 	1182202	SW 										RT EXH	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	33008					36004				EJECTOR UNIT CRACKED.						1	G	7	2 	4U				H4SW 					 
1995042100164	19950421	00164		1995	4	21	HEEA954748 	4	19950410	G	3416	D120P2T	ALTIMETER 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	ERROR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										ALTITUDE OFF BY 200 FEET.						1	G	7	1 	3U				H2SW 					 
1995042100165	19950421	00165	EU 	1995	4	21	HEEA954749 	1	19950411	G	6510	11203152105	RUBBER SLEEVE 			BOLKMS	117 	BK117B2 	5626013	EU 										T/R DRIVE	SLIPPING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	916 				7238				T/R DRIVESHAFT BEARING BUSHINGS SLIPPING ON DRIVESHAFT.						1	G	7	2 	3U			NC	H13EU 					 
1995042100166	19950421	00166	SW 	1995	4	21	HEEA954750 	1	19950411	G	6240	214074280105	DETECTOR 			BELL 	214 	214ST 	1182106	SW 										ROTOR RPM	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				LOW ROTOR WARNING AUDIO COMES ON AT IDLE WITH MUTE SWITCH OFF.						2	G	7	2 	4U				H10SW 					 
1995042100167	19950421	00167	SW 	1995	4	21	HEEA954751 	1	19950411	G	6330	214031614125	TORSION ARM 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN MOUNT	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				CRACKED PLATE ASSEMBLY AND TORSION ARM ELASTOMER. RECEIVED INSTALLED ON AIRCRAFT N8045T.						2	G	7	2 	4U				H10SW 					 
1995042100168	19950421	00168	SW 	1995	4	21	HEEA954752 	1	19950411	G	6330	214031614105	ARM ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN MOUNT	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				CRACKED AND DETERIORATED PLATE ASSEMBLY. RECEIVED INSTALLED ON AIRCRAFT N8045T.						2	G	7	2 	4U				H10SW 					 
1995042100169	19950421	00169	SW 	1995	4	21	HEEA954753 	1	19950411	G	6410	222012701117	BLADE 			BELL 	230 	230 	1182149	SW 										T/R	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	698 				23009				T/R BLADES HAVE LEADING EDGE DAMAGE.						1	G	7	2 	3U			NC	H9SW 					 
1995042100170	19950421	00170	SW 	1995	4	21	HEEA954755 	1	19950411	G	6330	206033506103	RESTRAINT 			BELL 	206 	206L 	1181522	SW 										TRANSMISSION	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7077F	764 				52038				TRANSMISSION RESTRAINT HAS ONE BEARING WORN AND THE OTHER BEARING IS UNSTAKED.						1	G	7	1 	3U				H2SW 					 
1995042100171	19950421	00171	EU 	1995	4	21	HEEA954756 	1	19950411	G	2840	81141010010	TRANSMITTER 			AEROSP	AS355 	AS355F1 	8680810	EU 										FUEL SYS	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y					5141				TRANSMITTER FLUCTUATES AND WORKS INTERMITTENTLY.						1	G	7	2 	3U				H11EU 					 
1995042100172	19950421	00172		1995	4	21	HEEA954757 	4	19950411	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	1077A					45382				WILL NOT SELF-TEST. FOUND IDENT LIGHT VERY DIM. REPLACED PHOTOCELL V301. REPAIRED. REPLACED DETERIORATED RESISTOR R47	7. INSTALLED HEAT SINK BEHIND TRANSISTOR Q415 AS PER SERVICE BULLETIN KT76A-6. UNIT HAD WEAK POWER OUT. REPLACED CAVI	TY TUBE V101. REPAIRED.ADJUSTED PULSE WIDTH. CLEANED CONTACTS ON WAFERS FOR FREQUENCY SELECTOR KNOBS. UNIT BENCH CHECK	 GOOD.			1	G	7	1 	3U				H2SW 					 
1995042100173	19950421	00173		1995	4	21	HEEA954758 	4	19950411	G	3453	4530103	LORAN 		ARNAV21 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	10814					45415				WON'T COME ON LINE.						1	G	7	1 	3U				H2SW 					 
1995042100174	19950421	00174		1995	4	21	HEEA954759 	4	19950411	G	3457	0110010600	GPS UNIT 		GPS165 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K	554 				36001				PILOT REPORTED CHECK BATTERY MESSAGE. (SOMETHING LOOSE INSIDE)						1	G	7	2 	4U				H4SW 					 
1995042100175	19950421	00175		1995	4	21	HEEA954760 	4	19950411	G	2312	066106600	TRANSCEIVER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545X					760050				BENCH CHECK REQUIRED. INSPECTED AND FOUND CORROSION. CLEANED CORROSION ON CHASIS AND APPLIED ALODINE. FOUND C101 CAPAC	ITOR ON POWER SUPPLY BOARD HAD LEAKAGE. REPLACED C101 CAPACITOR. REPAIRED. BENCH CHECK GOOD.					1	G	7	2 	3U				H1NE 					 
1995042100176	19950421	00176		1995	4	21	HEEA954761 	4	19950411	G	3457	0845000000	SKYNAV 5000 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT GPS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8765J					7054				GPS LOSES SIGNAL IN FLIGHT.						1	G	7	2 	3U				H13EU 					 
1995042100177	19950421	00177	SW 	1995	4	21	HEEA954762 	1	19950411	G	6240	206070265101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT DUAL TAC	NEEDLE STUCK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1073W					45386				BOTH ROTOR AND N2 NEEDLES STUCK AT 0%.						1	G	7	1 	3U				H2SW 					 
1995042100178	19950421	00178	SW 	1995	4	21	HEEA954763 	1	19950411	G	6310	206040270009	FREEWHEEL 			BELL 	206 	206L1 	1182107	SW 										M/R DRIVE	SEALS LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	20898	13223				45721				LEAKING FROM FORWARD AND AFT SEALS. REPLACED WITH SERVICEABLE FREEWHEELING UNIT AND RETURNED AIRCRAFT TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995042100179	19950421	00179	GL 	1995	4	21	HEEA954764 	2	19950411	G	7313	6899001	FUEL NOZZLE 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50034					45167				AIRCRAFT WILL NOT START ABOVE 12% N1. REPLACED FUEL NOZZLE DUE TO IMPROPER SPRAY PATTERN.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995042100180	19950421	00180		1995	4	21	HEEA954765 	4	19950411	G	3416	1179404203	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5196T	879 				7152				AIR SPEED INDICATOR IS SUSPECT TO CAUSE INSTRUMENTS LIGHTS TO GO OUT.						1	G	7	2 	3U				H13EU 					 
1995042100181	19950421	00181	SW 	1995	4	21	HEEA954766 	1	19950411	G	6310	206040222009	SHAFT 		206040270009	BELL 	206 	206L3 	1182108	SW 										FREEWHEEL	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	206FS				B46332	51506				CORROSION BEYOND LIMITS ON SEAL RIDE.						1	G	7	1 	3U				H2SW 					 
1995042100182	19950421	00182	SW 	1995	4	21	HEEA954767 	1	19950411	G	6310	206040222009	SHAFT 		206040270009	BELL 	206 	206L1 	1182107	SW 										FREEWHEEL	PITTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y				BMB45478	45751				PITTING ON CLUTCH RIDE.						1	G	7	1 	3U				H2SW 					 
1995042100183	19950421	00183	SW 	1995	4	21	HEEA954768 	1	19950411	G	6320	206040156101	SEAL ASSY 			BELL 	206 	206L1 	1182107	SW 										GR BOX	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2125M					45649				SEAL LEAKING.						1	G	7	1 	3U				H2SW 					 
1995042100184	19950421	00184	SW 	1995	4	21	HEEA954769 	1	19950411	G	6320	206040052009	HOUSING 			BELL 	206 	206L1 	1182107	SW 										TRANSMISSION	SEAL LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2125M					45649				SEAL LEAKING.						1	G	7	1 	3U				H2SW 					 
1995042100185	19950421	00185	SW 	1995	4	21	HEEA954770 	1	19950411	G	6320	206040048003	ADAPTER 			BELL 	206 	206L1 	1182107	SW 										GR BOX	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2125M					45649				SEAL LEAKING.						1	G	7	1 	3U				H2SW 					 
1995042100186	19950421	00186	SW 	1995	4	21	HEEA954776 	1	19950413	G	6300	222044645103	SHAFT 		222044000107	BELL 	222 	222 	1182122	SW 										MAIN DRIVE	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	602BA	919 			ANE00227	47043				CORRODED INSIDE OF BORES. COMPLY WITH ASB222-94-69. REMOVED FROM CUSTOMER AIRCRAFT N602BA.						1	G	7	2 	3U				H9SW 					 
1995042100187	19950421	00187	SW 	1995	4	21	HEEA954777 	1	19950413	G	6300	222044645103	SHAFT 		222044000107	BELL 	222 	222 	1182122	SW 										MAIN DRIVE	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	602BA	919 			ANE00222	47043				CORRODED INSIDE OF BORES. COMPLY WITH ASB222-94-69. REMOVED FROM CUSTOMER AIRCRAFT N602BA.						1	G	7	2 	3U				H9SW 					 
1995042100188	19950421	00188	SW 	1995	4	21	HEEA954778 	1	19950414	G	5530	204031826023	SPAR 			BELL 	212 	212 	1181420	SW 										AFT FIN	DENTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1079U					31122				DENT AT UPPER END OF SPAR.						1	G	7	1 	4U				H4SW 					 
1995042100189	19950421	00189		1995	4	21	HEEA954779 	4	19950414	G	3424	214075244001	GYRO 			BELL 	214 	214ST 	1182106	SW 										COCKPIT RATE	STUCK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				RATE OF TURN INDICATOR STUCK TO THE LEFT ON ADI. RECEIVED INSTALLED ON AIRCRAFT N5748M.						2	G	7	2 	4U				H10SW 					 
1995042100190	19950421	00190	SW 	1995	4	21	HEEA954780 	1	19950414	G	6520	222035101101	GEAR BOX 			BELL 	230 	230 	1182149	SW 										90 DEG GR BOX	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2004 				23009				90 DEGREE GEARBOX CASTING CRACKED ON WEBBING IN FOUR PLACES.						1	G	7	2 	3U			NC	H9SW 					 
1995042100191	19950421	00191	SW 	1995	4	21	HEEA954781 	1	19950414	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										START/GEN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				STARTER CAUSES ENGINE INSTRUMENTS TO SHORT OUT UNTIL START BUTTON IS RELEASED.						2	G	7	2 	4U				H10SW 					 
1995042100192	19950421	00192	SW 	1995	4	21	HEEA954782 	1	19950414	G	6420	214011801109	HUB 		214011801109	BELL 	214 	214ST 	1182106	SW 										T/R FEATHER	WORN BEARING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N	3660 			A45	28106				WORN FEATHERING BEARING.						2	G	7	2 	4U				H10SW 					 
1995042100193	19950421	00193	SW 	1995	4	21	HEEA954783 	1	19950414	G	6220	214010512105	BEARING 			BELL 	214 	214ST 	1182106	SW 										M/R	WASHER CHAFED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				WASHERS CHAFED.						2	G	7	2 	4U				H10SW 					 
1995042100194	19950421	00194	SW 	1995	4	21	HEEA954784 	1	19950414	G	2611	3023131	DETECTOR 			BELL 	214 	214ST 	1182106	SW 										SMOKE DET SYS	WONT TEST 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				INTERMITTENTLY WILL NOT TEST.						2	G	7	2 	4U				H10SW 					 
1995042100195	19950421	00195	SW 	1995	4	21	HEEA954785 	1	19950414	G	6520	222042412101	SLEEVE 			BELL 	230 	230 	1182149	SW 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2004 				23009				REPLACED WITH MODIFIED PART.						1	G	7	2 	3U			NC	H9SW 					 
1995042800621	19950428	00621	NE 	1995	4	28	HEEA954787 	1	19950418	G	6210	7615009100041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545X	11419				760050				NUMEROUS CRACKS ON THE NICKEL STRIP. THE TIP RIB IS PARTIALLY UNBONDED. THERE ARE NO MODIFICATIONS DONE TO THE TIP END	 FOR THE CSN TO BE COMPLIED WITH AND THIS BLADE ALSO MEETS THE TIME REQUIREMENT FOR THE ULTRA SONIC INSPECTION FOR TIME 	EXTENSION.				1	G	7	2 	3U				H1NE 					 
1995042800622	19950428	00622	NE 	1995	4	28	HEEA954788 	1	19950418	G	6210	7615009100049A	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	DEBONDING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	707AE	7389 				760276				SKIN DEBONDING CENTERED AT STATION 62" ON THE LOWER SURFACE DUE TO EXCESSIVE HEAT FROM THE ENGINE.						1	G	7	2 	3U				H1NE 					 
1995042800623	19950428	00623	SW 	1995	4	28	HEEA954789 	1	19950418	G	2810	206061661101	CELL 			BELL 	206 	206B3 	1181506	SW 										FUEL SYS	LEAKING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268W					3606				INTERIOR OF FUEL CELL IS BAD AND LEAKING.						1	G	7	1 	3U				H2SW 					 
1995042800624	19950428	00624		1995	4	28	HEEA954790 	4	19950418	G	2312	0110014700	ANTENNA 	GARMIN 	GA56 	BOLKMS	117 	BK117B1 	5626012	EU 										VHF	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC	33 				7152				RECEIVES INTERMITTENTLY.						1	G	7	2 	3U				H13EU 					 
1995042800625	19950428	00625	EU 	1995	4	28	HEEA954791 	1	19950418	G	6720	10543080	TUBE ASSEMBLY 			BOLKMS	105 	BO105S 	5626006	EU 										T/R CONTROL	LOOSE RIVETS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	724MB					S756				WHILE INSPECTING OVERHEAD SECTION IN BAGGAGE COMPARTMENT, FOUND BLACK MUD DRIPPING FROM ROOF. MUD WAS COMING FROM LONG 	TAIL ROTOR CONTROL TUBE END, FROM THREADED FITTING AND ATTACHING RIVETS. FITTING AND RIVETS WERE SLIDING IN TUBE APPROX	.1/8". REMOVED AND REPLACED TUBE ASSEMBLY. TAIL ROTOR RIGGING FOUND WITHIN LIMITS.				1	G	7	2 	3U				H3EU 					 
1995042800626	19950428	00626	SW 	1995	4	28	HEEA954792 	1	19950418	G	2910	70053H000A100A	HOSE ASSY 			BELL 	206 	206L1 	1182107	SW 										HYD SYS	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			LD	LANDING 	1			SW	03	2253E					45758				PILOT LANDED, REDUCED THROTTLE TO GROUND IDLE, HEARD A LOUD GRINDING SQUEALING NOISE AND FELT VIBRATION IN COLLECTIVE ST	ICK. SHUT ENGINE DOWN. CHECKED HYD FILTERS, FOUND NO METAL. PUMP WAS REPLACED DUE TO RESERVOIR RUNNING DRY CAUSING LOU	D NOISE. REPLACED O-RING ON ELBOW DUE TO FINDING ELBOW LOOSE. REMOVED AND REPLACED HOSE ASSY DUE TO LEAK SPRAYING FROM	 HYD. HOSE. RETURNED AIRCRAFT TOSERVICE.			1	G	7	1 	3U				H2SW 					 
1995042800627	19950428	00627	SW 	1995	4	28	HEEA954793 	1	19950418	G	6320	206040563001	TUBE ASSY 			BELL 	206 	206L1 	1182107	SW 										XMSN OIL	LEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748Q	586 				45499				TUBE ASSEMBLY DEVELOPED A PIN HOLE LEAK AROUND "B" NUT COLLAR. PIN HOLE APEARS TO BE CAUSED BY CORROSION. "B" NUT FERRU	LE ON TUBE ASSEMBLY WAS STAINLESS STEEL AS THIS IS AN ALUMINUM LINE.					1	G	7	1 	3U				H2SW 					 
1995042800628	19950428	00628		1995	4	28	HEEA954794 	4	19950418	G	3416	214175278101	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT ENCODER	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				ENCODING PORTION OF ALTIMETER INOPERATIVE. WOULD NOT PASS ANNUAL AIRCRAFT INSPECTION.						2	G	7	2 	4U				H10SW 					 
1995042800629	19950428	00629		1995	4	28	HEEA954795 	4	19950419	G	2200	214074153101	TRANSDUCER 			BELL 	214 	214ST 	1182106	SW 										AUTO FLIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				BODY OF TRANSDUCER BROKEN. PART RECEIVED INSTALLED ON AIRCRAFT.						2	G	7	2 	4U				H10SW 					 
1995042800630	19950428	00630	SW 	1995	4	28	HEEA954797 	1	19950419	G	2520	214070966101	SEAT BELT 			BELL 	214 	214ST 	1182106	SW 										CABIN	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				SEAT BELT WORN BEYOND LIMITS. PART RECEIVED INSTALLED ON AIRCRAFT.						2	G	7	2 	4U				H10SW 					 
1995042800631	19950428	00631	SW 	1995	4	28	HEEA954799 	1	19950419	G	3310	214175368101	PANEL 			BELL 	214 	214ST 	1182106	SW 										LIGHTING	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				INTERNAL LIGHTING INOPERATIVE. PART RECEIVED INSTALLED ON AIRCRAFT.						2	G	7	2 	4U				H10SW 					 
1995042800632	19950428	00632	SW 	1995	4	28	HEEA954800 	1	19950419	G	7120	214060207101	FITTING 			BELL 	214 	214ST 	1182106	SW 										ENG MOUNT	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				#1 ENGINE AFT ENGINE MOUNT BEARING WORN.						2	G	7	2 	4U				H10SW 					 
1995042800633	19950428	00633	SW 	1995	4	28	HEEA954801 	1	19950419	G	7120	214060207102	FITTING 			BELL 	214 	214ST 	1182106	SW 										ENG MOUNT	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				#2 ENGINE AFT ENGINE MOUNT BEARING WORN.						2	G	7	2 	4U				H10SW 					 
1995042800634	19950428	00634	SW 	1995	4	28	HEEA954802 	1	19950419	G	3040	214075186001	CONTROLLER UNIT 			BELL 	214 	214ST 	1182106	SW 										WINDSHLD HEAT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				HEATED WINDSHIELD INOPERATIVE.						2	G	7	2 	4U				H10SW 					 
1995042800635	19950428	00635		1995	4	28	HEEA954803 	4	19950419	G	3421	214175370103	CONNECTOR PLATE 			BELL 	214 	214ST 	1182106	SW 										ATT INDICATOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				NOT EQUIPPED WITH A STANDBY ATTITUDE INDICATOR ON/OFF/TEST SWITCH.						2	G	7	2 	4U				H10SW 					 
1995042800636	19950428	00636	SW 	1995	4	28	HEEA954805 	1	19950419	G	6220	214010258101	CLIP 			BELL 	214 	214ST 	1182106	SW 										M/R	BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				CLIPS BROKEN.						2	G	7	2 	4U				H10SW 					 
1995042800637	19950428	00637	SW 	1995	4	28	HEEA954806 	1	19950419	G	2510	110105201	PILOT RESTRAINT 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	NOT PROPER 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				PILOT AND COPILOTS RESTRAINTS NOT FAA APPROVED.						2	G	7	2 	4U				H10SW 					 
1995042800638	19950428	00638	SW 	1995	4	28	HEEA954807 	1	19950419	G	6500	214010774001	BEARING 			BELL 	214 	214ST 	1182106	SW 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				BEARING WORN AND ROUGH.						2	G	7	2 	4U				H10SW 					 
1995042800639	19950428	00639	SW 	1995	4	28	HEEA954808 	1	19950419	G	6230	214010516101	BUSHING 			BELL 	214 	214ST 	1182106	SW 										M/R	PITTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				BUSHING PITTED.						2	G	7	2 	4U				H10SW 					 
1995042800640	19950428	00640	SW 	1995	4	28	HEEA954809 	1	19950419	G	5220	633401	CONTROL CABLE 			BELL 	214 	214ST 	1182106	SW 										JETTISON DOOR	FRAYED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				PILOT AND COPILOT'S JETTISON DOOR CABLE FRAYED.						2	G	7	2 	4U			 	H10SW 					 
1995042800641	19950428	00641	SW 	1995	4	28	HEEA954810 	1	19950419	G	5220	6341	HANDLE 			BELL 	214 	214ST 	1182106	SW 										JETTISON DOOR	CABLE FRAYED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				PILOT AND COPILOT'S JETISON DOOR CABLE FRAYED.						2	G	7	2 	4U				H10SW 					 
1995042800642	19950428	00642	SW 	1995	4	28	HEEA954811 	1	19950419	G	7110	214061874102	FITTING 			BELL 	214 	214ST 	1182106	SW 										COWL	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				FITTING CRACKED.						2	G	7	2 	4U				H10SW 					 
1995042800643	19950428	00643	SW 	1995	4	28	HEEA954812 	1	19950419	G	6220	214010435003	BEARING 			BELL 	214 	214ST 	1182106	SW 										M/R	COVER MISSING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				DUST COVERS MISSING.						2	G	7	2 	4U				H10SW 					 
1995042800644	19950428	00644	SW 	1995	4	28	HEEA954813 	1	19950419	G	6220	50047838	BOLT 			BELL 	214 	214ST 	1182106	SW 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				WORN BEYOND LIMITS AS PER ASB 214ST-90-51.						2	G	7	2 	4U				H10SW 					 
1995042800645	19950428	00645	SW 	1995	4	28	HEEA954814 	1	19950419	G	6220	214010518101	WASHER 			BELL 	214 	214ST 	1182106	SW 										M/R THRUST	CHAFED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				THRUST WASHER CHAFED.						2	G	7	2 	4U				H10SW 					 
1995042800646	19950428	00646	SW 	1995	4	28	HEEA954815 	1	19950419	G	3244	500510PLY	TIRE 			BELL 	214 	214ST 	1182106	SW 										MLG	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				ONE TIRE SPLIT TO THREADS AND ONE TIRE SPLIT WITH PUCTURE.						2	G	7	2 	4U				H10SW 					 
1995042800647	19950428	00647		1995	4	28	HEEA954817 	4	19950419	G	3416	7000839904	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT ALT	STUCK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				NEEDLE STUCK AT 950 FEET. WHEN TESTED NEEDLE GOES TO 2000 FEET.						2	G	7	2 	4U				H10SW 					 
1995042800648	19950428	00648	SW 	1995	4	28	HEEA954818 	1	19950419	G	5210	214031913101	STRIKER 			BELL 	214 	214ST 	1182106	SW 										DOOR	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				WORN AND ALLOWING DOOR TO OPEN IN FLIGHT.						2	G	7	2 	4U				H10SW 					 
1995042800649	19950428	00649		1995	4	28	HEEA954820 	1	19950420	G	2432	3055401C	BATTERY 	MARATHON 																DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										INSPECTED BY ACCESSORY SHOP AND FOUND NUMEROUS CELLS CONTAMINATED AND WOULD NOT ACCEPT A CHARGE.																			 
1995042800650	19950428	00650		1995	4	28	HEEA954821 	4	19950420	G	2210	7683431	POTENTIOMETER 			SKRSKY	S76 	S76 	8143010	NE 										AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										CAUSES VOLTAGE FROM J1-B TO GROUND ON BOTH EXTEND AND RETRACT POSITIONS OF ACTUATOR TO BE TOO LOW AND OUT OF LIMITS.						1	G	7	2 	3U				H1NE 					 
1995042800651	19950428	00651	GL 	1995	4	28	HEEA954822 	2	19950420	G	7321	252464428	FUEL CONTROL 			BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					NR 1 ENG	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5418A	7234 				S800				#1 ENGINE OSCILLATING 10% ABOVE 55% TORQUE. REPLACED WITH SERVICEABLE FUEL CONTROL.						1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995042800652	19950428	00652	EU 	1995	4	28	HEEA954823 	1	19950420	G	6210	10515150	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	86CH	4049 				S557				NOSE AND NECK SHELLS CRACKED.						1	G	7	2 	3U				H3EU 					 
1995042800653	19950428	00653	EU 	1995	4	28	HEEA954824 	1	19950420	G	3340	MS3450L10SL3S	RECEPTACLE 			BOLKMS	117 	BK117B2 	5626013	EU 										ANTI COLL LIGHT	SHORTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	860 				7238				CANNON PLUG RECEPTACLE SHORTED CAUSING ANTI COLLISON LIGHT TO QUIT WORKING. REPLACED WITH SERVICEABLE RECEPTACLE.						1	G	7	2 	3U			NC	H13EU 					 
1995042800654	19950428	00654	NE 	1995	4	28	HEEA954825 	1	19950420	G	3020	7630407900111	SNOW BLANKET 			SKRSKY	S76 	S76A 	8143006	NE 										ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			SW	03	3122G					760232				ENGINE ANTI-ICE CAUTION LIGHT CYCLES OFF AND ON.						1	G	7	2 	3U				H1NE 					 
1995042800655	19950428	00655	SW 	1995	4	28	HEEA954830 	1	19950421	G	5313	212030128153	LONGERON 		212030100133	BELL 	412 	412 	1182202	SW 										STA 101.38	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	21498	7369 			36001	36003				LONGERON CORRODED DEEP AT STATION 101.38 SPLICE AS SEEN IN UPPER R/H AFT CORNER OF BAGGAGE COMPARTMENT, JUST OUTBOARD OF	 WHERE THE BAGGAGE COMPARTMENT CEILING PANEL ATTACHES TO LONGERON.					1	G	7	2 	4U				H4SW 					 
1995042800656	19950428	00656	SW 	1995	4	28	HEEA954831 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8594X	1923 			CS4506	51531				BEARINGS CRACKED. ALSO REPLACED 4 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800657	19950428	00657	SW 	1995	4	28	HEEA954832 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81671	530 			CS4360	51301				BEARINGS CRACKED. ALSO REPLACED 4 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800658	19950428	00658	SW 	1995	4	28	HEEA954833 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	32041	573 			CS6283	51539				BEARINGS CRACKED. ALSO REPLACED 4 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROUG	H # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800659	19950428	00659	SW 	1995	4	28	HEEA954834 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5019F	677 			CS2630	45244				BEARINGS CRACKED. ALSO REPLACED 4 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800660	19950428	00660	SW 	1995	4	28	HEEA954835 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2754W	1918 			CS5328	45260				BEARINGS CRACKED. ALSO REPLACED 4 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800661	19950428	00661	SW 	1995	4	28	HEEA954836 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5007Q	723 			CS5344	45187				BEARINGS CRACKED. ALSO REPLACED 2 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROUG	H # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800662	19950428	00662	SW 	1995	4	28	HEEA954837 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5007Q	948 			CS5344	45187				BEARINGS CRACKED. ALSO REPLACED 2 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THRO	UGH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800663	19950428	00663	SW 	1995	4	28	HEEA954838 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	206FS	880 			CS5348	51506				BEARINGS CRACKED. ALSO REPLACED 4 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800664	19950428	00664	SW 	1995	4	28	HEEA954839 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X	1719 			CS5106	51495				BEARINGS CRACKED. ALSO REPLACED 2 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800665	19950428	00665	SW 	1995	4	28	HEEA954840 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X	1643 			CS5097	51495				BEARINGS CRACKED. ALSO REPLACED 1 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROUG	H # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800666	19950428	00666	SW 	1995	4	28	HEEA954841 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X	1719 			CS5097	51495				BEARINGS CRACKED. ALSO REPLACED 1 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800667	19950428	00667	SW 	1995	4	28	HEEA954842 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X	348 			CS5827	51495				BEARINGS CRACKED. ALSO REPLACED 2 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800668	19950428	00668	SW 	1995	4	28	HEEA954843 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L3 	1182108	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X	899 			CS5827	51495				BEARINGS CRACKED. ALSO REPLACED 2 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THR	OUGH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995042800669	19950428	00669	SW 	1995	4	28	HEEA954844 	1	19950421	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5014Y	843 			CS5895	45219				BEARINGS CRACKED. ALSO REPLACED 4 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY. SEE MMIR'S # 4831 THROU	GH # 4844 FOR ADDITIONAL BEARINGS.					1	G	7	1 	3U				H2SW 					 
1995050500202	19950505	00202	SW 	1995	5	5	HEEA954845 	1	19950424	G	2432	39563001	BATTERY 			BELL 	412 	412 	1182202	SW 										DC SYS	FAIL TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	2261D	830 				33076				INSPECTED BY ACCESSORY SHOP AND FOUND BATTERY FAILED CAPACITY TEST.						1	G	7	2 	4U				H4SW 					 
1995050500203	19950505	00203	NE 	1995	5	5	HEEA954847 	1	19950424	G	2432	6013211	BATTERY 			SKRSKY	S76 	S76A 	8143006	NE 										EMERG POWER	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4253S					760035				CELL NO. 6 READING ZERO VOLTS.						1	G	7	2 	3U				H1NE 					 
1995050500204	19950505	00204		1995	5	5	HEEA954848 	4	19950424	G	2211	40008519916	COMPUTER 			BEECH 	200 	200CBEECH 	1152926	CE 										AUTO PILOT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	500PH					BL29				YAW DAMPER INOPERATIVE. TIME SINCE REPAIR 1284:40.						1	L	7	2 	4T				A24CE 					 
1995050500205	19950505	00205	SW 	1995	5	5	HEEA954849 	1	19950424	G	6710	214001347005	ROTARY ACTUATOR 			BELL 	412 	412 	1182202	SW 										AUTO FLIGHT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				LATERAL AFCS INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995050500206	19950505	00206	SW 	1995	5	5	HEEA954850 	1	19950424	G	6710	214001347005	ACTUATOR ROTARY 			BELL 	412 	412 	1182202	SW 										AUTO FLIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				LATERAL BINDING IN CONTROLS. OVERHAULED BY BELL 8-26-94.						1	G	7	2 	4U				H4SW 					 
1995050500207	19950505	00207	NE 	1995	5	5	HEEA954851 	1	19950424	G	7722	7645001076107	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT TIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				FLUCTUATES AND DROPS TO ZERO. TIME SINCE REPAIR 232:35.						1	G	7	2 	3U				H1NE 					 
1995050500208	19950505	00208	SW 	1995	5	5	HEEA954852 	1	19950424	G	7722	35712519127	INDICATOR 			BELL 	206 	206B 	1181511	SW 										COCKPIT TOT	READS HIGH 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2276B					3628				INDICATES 10 DEGREES HIGH AT 600 DEGREES CELSUIS AFTER UNIT WARMS UP. TIME SINCE REPAIR 278:40.						1	G	7	1 	3U				H2SW 					 
1995050500209	19950505	00209	SW 	1995	5	5	HEEA954853 	1	19950424	G	6240	206070265101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT DUAL TAC	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	50034					45167				TURBINE NEEDLE SLUGGISH AND ROTOR INOPERATIVE.						1	G	7	1 	3U				H2SW 					 
1995050500210	19950505	00210	SW 	1995	5	5	HEEA954855 	1	19950424	G	2810	206061661101	FUEL CELL 			BELL 	206 	206B 	1181511	SW 										FUEL SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										FUEL CELL HAS PULLED HELICOILS AS MARKED. UNBONDED INSERT AND CRACKED SEAMS AS MARKED.						1	G	7	1 	3U				H2SW 					 
1995050500211	19950505	00211	EU 	1995	5	5	HEEA954856 	1	19950424	G	2810	FT17521	TANK 			BOLKMS	105 	BO105S 	5626006	EU 										MAIN FUEL	LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	7161J					S834				DUE TO PIN-HOLE LEAK ON FILLER NECK SEAM AS MARKED IN RED.						1	G	7	2 	3U				H3EU 					 
1995050500212	19950505	00212	SW 	1995	5	5	HEEA954857 	1	19950424	G	2435	230811010	ARMATURE 			BELL 	206 	206L1 	1182107	SW 										START GEN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										ARMATURE RUBS AGAINST BRUSH BOX WHEN INSTALLED IN STARTER GENERATOR. UNIT WAS REWOUND ON 1-25-95.						1	G	7	1 	3U				H2SW 					 
1995050500213	19950505	00213	SW 	1995	5	5	HEEA954858 	1	19950424	G	2824	L88010491	VALVE 			BELL 	412 	412 	1182202	SW 										FUEL SYS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2298Z					33077				VALVE INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995050500214	19950505	00214	EU 	1995	5	5	HEEA954859 	1	19950424	G	7930	174000103	FILTER ASSEMBLY 			BOLKMS	117 	BK117B1 	5626012	EU 										BY PASS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5196T	885 				7152				FILTER BYPASS INDICATOR BUTTON DID NOT EXTEND DURING FUNCTIONAL CHECK.						1	G	7	2 	3U				H13EU 					 
1995050500215	19950505	00215	EU 	1995	5	5	HEEA954860 	1	19950424	G	7930	174000103	FILTER ASSEMBLY 			BOLKMS	117 	BK117B1 	5626012	EU 										BY PASS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5196T	885 				7152				FILTER BYPASS INDICATOR BUTTON DID NOT EXTEND DURING FUNCTIONAL CHECK.						1	G	7	2 	3U				H13EU 					 
1995050500216	19950505	00216		1995	5	5	HEEA954861 	4	19950424	G	3421	1113034	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT ATTITUDE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22342					760096				RATE OF TURN FLAG WILL NOT PULL SOMETIMES. TIME SINCE REPAIR 91:55.						1	G	7	2 	3U				H1NE 					 
1995050500217	19950505	00217		1995	5	5	HEEA954862 	4	19950424	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2298Z					33077				COURSE PRECESSES 47 DEGREES.						1	G	7	2 	4U				H4SW 					 
1995050500218	19950505	00218		1995	5	5	HEEA954863 	4	19950424	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2298Z					33077				BEARING #1 AND #2 NEEDLES STICKING TOGETHER.						1	G	7	2 	4U				H4SW 					 
1995050500219	19950505	00219	SW 	1995	5	5	HEEA954864 	1	19950424	G	7722	206375007103	INDICATOR 			BELL 	206 	206L 	1181522	SW 										COCKPIT TOT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7077B					52037				TAKES TOO LONG FOR OVER TEMP. LIGHT TO COME ON.						1	G	7	1 	3U				H2SW 					 
1995050500220	19950505	00220	SW 	1995	5	5	HEEA954865 	1	19950424	G	7810	212061201011	EJECTOR 			BELL 	212 	212 	1181420	SW 										LT EXH ASSY	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5736J					31140				EJECTOR CRACKED AND BUCKLED.						1	G	7	1 	4U				H4SW 					 
1995050500221	19950505	00221	EU 	1995	5	5	HEEA954866 	1	19950424	G	7712	10594575	TRANSMITTER 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT TORQUE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC	900 				7152				NEEDLE HAS AN ERRATIC INDICATION.						1	G	7	2 	3U				H13EU 					 
1995050500222	19950505	00222	EU 	1995	5	5	HEEA954867 	1	19950424	G	6240	117945641	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										MAST MOMENT	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC	900 				7152				NEEDLE HAS AN ERRATIC INDICATION.						1	G	7	2 	3U				H13EU 					 
1995050500223	19950505	00223		1995	5	5	HEEA954868 	4	19950424	G	3416	5035P2P13	ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT ENCODER	ERROR 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				ENCODER IS 140 FEET OFF AT 18,000 FEET.						1	G	7	2 	4U				H4SW 					 
1995050500224	19950505	00224	SW 	1995	5	5	HEEA954869 	1	19950424	G	2436	206075447007	REGULATOR 			BELL 	206 	206L1 	1182107	SW 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5007Q					45187				REGULATOR CAUSING GEN. TO NOT COME ON LINE.						1	G	7	1 	3U				H2SW 					 
1995050500225	19950505	00225		1995	5	5	HEEA954870 	4	19950424	G	2312	6223078001	TRANSCEIVER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3535T					S113				KNOB LOOSE. FOUND THE FOLLOWING PARTS BAD - SPUR GEAR DRIVE BROKEN. BEARING WORN, SPUR GEAR FOLLOWER HAS BROKEN TOOTH	, GUIDE CIRCUIT CARD IS CRACKED. PLATE FOR VOLUME TEST SWITCH HAS STRIPPED THREAD.					1	G	7	2 	3U				H3EU 					 
1995050500226	19950505	00226		1995	5	5	HEEA954871 	4	19950424	G	3423	2593379001	COMPENSATOR 			BELL 	212 	212 	1181420	SW 										COMPASS	FAILS TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5736J					31140				FAILS #1 AND #2 FLUX VALVE INSULATION CAP TEST.						1	G	7	1 	4U				H4SW 					 
1995050500227	19950505	00227	NE 	1995	5	5	HEEA954872 	1	19950424	G	7931	7645001078112	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	READS HIGH 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				OIL PRESS INDICATOR READS HIGH.						1	G	7	2 	3U				H1NE 					 
1995050500228	19950505	00228	EU 	1995	5	5	HEEA954873 	1	19950425	G	6720	741C000004	ACTUATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										TAIL ROTOR	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	911TL					7198				LEAKING AT CONTROL VALVE.						1	G	7	2 	3U				H13EU 					 
1995050500229	19950505	00229	SW 	1995	5	5	HEEA954874 	1	19950425	G	2910	412375017101	MDAU 			BELL 	412 	412 	1182202	SW 										HYD SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7128R	1759 				36007				WHEN TESTING HYD SYSTEM, BOTH HYD CAN BE TURNED OFF AT THE SAME TIME. REMOVED MDAU SYSTEM, TESTED GOOD.						1	G	7	2 	4U				H4SW 					 
1995050500230	19950505	00230	SW 	1995	5	5	HEEA954875 	1	19950425	G	6700	206001173101	TUBE ASSY 			BELL 	206 	206L1 	1182107	SW 										FLT CONTROLS	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										TUBE ASSY CORRODED BEYOND LIMITS.						1	G	7	1 	3U				H2SW 					 
1995050500231	19950505	00231	NE 	1995	5	5	HEEA954876 	2	19950425	G	7210	3024780	GEARBOX 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					COMBINING BOX	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3911L	13832				33023				METAL IN OIL.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995050500232	19950505	00232	NE 	1995	5	5	HEEA954877 	2	19950425	G	7210	3024780	GEARBOX TOOTH 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					COMBINING BOX	BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3131S	11661				30953				GR BOX NEEDS OVERHAUL DUE TO GEAR TOOTH FOUND ON #1 ENGINE AFT CHIP PLUG.						1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1995050500233	19950505	00233		1995	5	5	HEEA954878 	4	19950425	G	2200	7690001802106	ACTUATOR 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122G					760232				KICKS AFCS CHANNEL IN FLIGHT.						1	G	7	2 	3U				H1NE 					 
1995050500234	19950505	00234		1995	5	5	HEEA954879 	4	19950425	G	2200	7690001802106	ACTUATOR 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545X	7113 				760050				ACTUATOR CHATTERS.						1	G	7	2 	3U				H1NE 					 
1995050500235	19950505	00235		1995	5	5	HEEA954880 	4	19950425	G	2200	7690001802106	ACTUATOR 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	CHATTERING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545X	5589 				760050				ACTUATOR CHATTERING.						1	G	7	2 	3U				H1NE 					 
1995050500236	19950505	00236	EU 	1995	5	5	HEEA954881 	1	19950425	G	2840	81141010010	TRANSMITTER 			AEROSP	AS355 	AS355F2 	8680812	EU 										FUEL PRESS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6040U					5474				NO INDICATION ON GAUGE. TIME SINCE REPAIR 516:55.						1	G	7	2 	3U				H11EU 					 
1995050500237	19950505	00237	EU 	1995	5	5	HEEA954882 	1	19950425	G	6510	10531802001	SHAFT 			BOLKMS	105 	BO105S 	5626006	EU 										T/R	SCORED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	724MB					S756				SLIDING SLEEVE AREA SCORING AND CORROSION AT BEARING SEAT.						1	G	7	2 	3U				H3EU 					 
1995050500238	19950505	00238	SW 	1995	5	5	HEEA954883 	1	19950425	G	2422	ASH4501	INVERTER 			BELL 	412 	412 	1182202	SW 										AC SYS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21498					36003				VOLTAGE WENT TO 120V THEN DROPPED OFF LINE.						1	G	7	2 	4U				H4SW 					 
1995050500239	19950505	00239	GL 	1995	5	5	HEEA954884 	3	19950425	G	6114		HUB 			BEECH 	200 	200CBEECH 	1152926	CE 						HARTZL	HCB3T	HCB3TN3 	GL 	NR 2 PROP	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	39PH					BL3		BU7949		#2 ENGINE MAKING METAL. TARGET SCREWS MISSING IN DEICE SLIP RING.						1	L	7	2 	4T				A24CE 		6	C	P15EA	 
1995050500240	19950505	00240		1995	5	5	HEEA954885 	4	19950425	G	3422	109290	GYRO UNIT 			BOLKMS	117 	BK117B2 	5626013	EU 										AUTO FLIGHT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	132AE	916 				7238				INTERMITTENT KICKING OF YAW/SAS SYSTEM.						1	G	7	2 	3U			NC	H13EU 					 
1995050500241	19950505	00241	EU 	1995	5	5	HEEA954886 	1	19950425	G	6220	704A33633109	BEARING 			SNIAS 	350 	AS350B 	8680801	EU 										M/R	BLISTERED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	881 				2771				UNITS BLISTERED. SN 8535, 8536, & 8537.						1	G	7	1 	3U				H9EU 					 
1995050500242	19950505	00242	SW 	1995	5	5	HEEA954887 	1	19950425	G	2910	214076333107	MOTOR 			BELL 	214 	214ST 	1182106	SW 										HYD	LEAKS 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	5748M					28102				HYD MOTOR LEAKS-RADIAL PLAY.						2	G	7	2 	4U				H10SW 					 
1995050500243	19950505	00243	SW 	1995	5	5	HEEA954888 	1	19950425	G	2913	214076334105	PUMP 			BELL 	214 	214ST 	1182106	SW 										HYD	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M	82 				28102				SUSPECT PUMP WAS RUN WITHOUT FLUID.						2	G	7	2 	4U				H10SW 					 
1995050500244	19950505	00244	NE 	1995	5	5	HEEA954889 	2	19950425	G	7314	02527730007	FUEL PUMP 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					NR 1 ENG	FAILED 	E			HEEA	O				OTHER 				X			ENGINE FLAMEOUT 			NR	NOT REPORTED 	1			SW	03	1079U	10278				31122				#1 ENGINE FLAMED OUT IN FLIGHT. FOUND FUEL PUMP DRIVE COUPLING FAILURE. MALE SPLINES ON DRIVE GEAR INSIDE PUMP WERE RO	UNDED OFF. REPLACED FUEL PUMP AND RETURNED TO SERVICE.					1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1995050500245	19950505	00245	NE 	1995	5	5	HEEA954890 	1	19950425	G	2913	7665009808101	HYD PUMP 			SKRSKY	S76 	S76A 	8143006	NE 										HYD SYS	FAILED 	E			HEEA	K				NONE 				J			WARNING INDICATION 			CL	CLIMB 	1			SW	03	911MJ					760231				ON TAKE OFF THE #2 SERVO LIGHT LLUMINATED WITH DROP IN HYDRAULIC PRESSURE. REPLACED HYD PUMP AND RETURNED AIRCRAFT TO SE	RVICE.					1	G	7	2 	3U				H1NE 					 
1995050500246	19950505	00246	EU 	1995	5	5	HEEA954891 	1	19950425	G	6310	330A54020628	COUPLING 		355A35203400	AEROSP	AS355 	AS355F1 	8680810	EU 										NR 2 ENG	FAILED 	E			HEEA	O				OTHER 				E			VIBRATION/BUFFET 			NR	NOT REPORTED 	1			SW	03	5796T	1616 			PMA92	5166				PILOT DETECTED A HUM AND VIBRATION FOR APPROXIMATELY ONE MINUTE. FOLLOWED BY A BANG AND LOSS OF POWER ON #2 ENGINE. FOU	ND #2 FLEX COUPLING AT THE TRANSMISSION DESTROYED. SCRAPPED COUPLING AND REPLACED WITH SERVICEABLE PART--RETURNED AIRCR	AFT TO SERVICE.				1	G	7	2 	3U				H11EU 					 
1995050500247	19950505	00247	GL 	1995	5	5	HEEA954892 	2	19950425	G	7250	6898911	WHEEL 		23031925 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		1750 			CAT90593		CAE890585			ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: EXCESSIVE SULFIDATION AN	D DELAMINATION ON ALL 1ST STAGE WHEEL BLADES CAUSING 10 EACH BLADE TIP FAILURES .062" CHORDALLY PROGRESSING .062"ACROSS 	TRAILING EDGE MAXIMUM. SCRAPPED 1ST STAGE WHEEL.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995050500248	19950505	00248	SW 	1995	5	5	HEEA954894 	1	19950426	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										START GEN	FAILED 	E			HEEA	K				NONE 				O	B		OTHER 	SMOKE/FUMES/ODORS/SPARKS 		IN	INSP/MAINT 	1			SW	03	5748M					28102				BURNT UP--WILL NOT START--SMOKING.						2	G	7	2 	4U				H10SW 					 
1995050500249	19950505	00249	SW 	1995	5	5	HEEA954895 	1	19950428	G	7722	206375007101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	UNRELIABLE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5005F					45176				UNRELIABLE (C/W 206L-93-165)						1	G	7	1 	3U				H2SW 					 
1995050500250	19950505	00250		1995	5	5	HEEA954898 	4	19950428	G	3451	066106602	TRANSCEIVER 			BELL 	230 	230 	1182149	SW 										COCKPIT DME	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN					23009				DME WILL NOT HOLD STATIONS.						1	G	7	2 	3U			NC	H9SW 					 
1995051200150	19950512	00150	EU 	1995	5	12	HEEA954899 	1	19950501	G	7160	350A54108004	INTAKE 			SNIAS 	350 	AS350B2 	8680813	EU 										ENG AIR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	350BZ	937 				2653				INTAKE DOES NOT TURN.						1	G	7	1 	3U				H9EU 					 
1995051200151	19950512	00151	EU 	1995	5	12	HEEA954900 	1	19950501	G	6321	350A32050002	BRAKE ASSY 			SNIAS 	350 	AS350B2 	8680813	EU 										ROTOR	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	911 				2771				ROTOR BRAKE WORN.						1	G	7	1 	3U				H9EU 					 
1995051200152	19950512	00152	SW 	1995	5	12	HEEA954901 	1	19950501	G	7712	222375077117	TRANSMITTER 			BELL 	230 	230 	1182149	SW 										NR 1 ENG TORQUE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2007 				23009				#1 ENGINE TORQUE INDICATION READS ZERO ON GAUGE.						1	G	7	2 	3U			NC	H9SW 					 
1995051200153	19950512	00153	SW 	1995	5	12	HEEA954902 	1	19950501	G	6210	222015600111	BLADE 			BELL 	230 	230 	1182149	SW 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2033 				23009				CLOSURE AT BLADE ROOT TRAILING EDGE SIDE CRACKED. REPAIRED THREE TIMES PREVIOUSLY.						1	G	7	2 	3U			NC	H9SW 					 
1995051200154	19950512	00154	SW 	1995	5	12	HEEA954904 	1	19950502	G	7920	70037C073000	HOSE ASSY 			BELL 	230 	230 	1182149	SW 										OIL SYS	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	230UN	2007 				23009				HOSE LEAKING THROUGH BRAIDS.						1	G	7	2 	3U			NC	H9SW 					 
1995051200155	19950512	00155	SW 	1995	5	12	HEEA954905 	1	19950502	G	2910	AE1009102G0174	HOSE ASSY 			BELL 	230 	230 	1182149	SW 										NR 1 HYD	CHAFED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2007 				23009				PRESSURE LINE ON #1 HYD SYSTEM CHAFFED.						1	G	7	2 	3U			NC	H9SW 					 
1995051200156	19950512	00156	SW 	1995	5	12	HEEA954907 	1	19950503	G	6320	206040531105	CASE ASSY 		206040004107	BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	3116P	4463 			B51702	51530				UPON DISASSEMBLY OF TRANSMISSION FOR OVERHAUL, CENTER CASE WAS IDENTIFIED AS BEING INCORRECTLY MANUFACTURED. (STUD HOLE	 PATTERN NOT IN PROPER LOCATION TO FACILITATE OIL PASSAGES) (APPROX 72 DEGREES)					1	G	7	1 	3U				H2SW 					 
1995051200157	19950512	00157	SW 	1995	5	12	HEEA954908 	1	19950503	G	6210	412015300109	BLADE 			BELL 	412 	412 	1182202	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		2499 								ROOT END RUBBER TORN. BLADE NEEDS 2500 HOUR INSPECTION, PAINT PEELING ON TOP AND BOTTOM SIDE OF BLADE. REPLACED ROOT 	END RUBBER, COMPLIED WITH 2500 HOUR INSPECTION AND FEATHERED PEELING PAINT.					1	G	7	2 	4U				H4SW 					 
1995051200158	19950512	00158	SW 	1995	5	12	HEEA954909 	1	19950503	G	6210	412015300109	BLADE 			BELL 	412 	412 	1182202	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		2499 								SEPARATION ON THE MIDSPAN TRIM TAB EAR, PAINT PEELING ON TOP AND BOTTOM SIDE OF THE BLADE. BLADE NEEDS 2500 HOUR INSPE	CTION. REPLACED TRIM TAB EARS, FEATHERED THE PEELING PAINT, COMPLIED WITH 2500 HOUR INSPECTION.					1	G	7	2 	4U				H4SW 					 
1995051200159	19950512	00159	SW 	1995	5	12	HEEA954910 	1	19950503	G	6220	412010401109	HUB 			BELL 	412 	412 	1182202	SW 										M/R	REQ OHAUL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		2499 								2500 HOUR OVERHAUL DUE.						1	G	7	2 	4U				H4SW 					 
1995051200160	19950512	00160	SW 	1995	5	12	HEEA954911 	1	19950503	G	6230	412010402105	SWASHPLATE 			BELL 	412 	412 	1182202	SW 										M/R MAST	REQ OHAUL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		2499 								2500 HOUR OVERHAUL DUE.						1	G	7	2 	4U				H4SW 					 
1995051200161	19950512	00161	EU 	1995	5	12	HEEA954912 	1	19950504	G	5320	355A58305322	SUPPORT 			AEROSP	AS355 	AS355F1 	8680810	EU 										FUSELAGE	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5796S					5164				SUPPORT P/N IS FOR THE FORWARD LEFT HAND ANGLE; BUT THE ANGLE IS BENT UP TO FIT ON R/H SIDE OF AIRCRAFT.						1	G	7	2 	3U				H11EU 					 
1995110200008	19951102	00008	GL 	1995	11	2	HEEA954913 	2	19950504	G	7230	23008090	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEP WEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	31219	681 			CAC90703	760230	CAE890555S			ENGINE REMOVED DUE TO TURBINE OVERHAUL AND COMPRESSOR N1 SHAFTING INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED	 THE FOLLOWING: STEP WEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER G	EARSHAFT.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995051200162	19950512	00162	GL 	1995	5	12	HEEA954914 	2	19950504	G	7230	23008090	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEP WEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5435V	821 			CAC90511	760158	CAE890507S			ENGINE REMOVED DUE TO COMPRESSOR 1750 HOUR INSPECTION AND TURBINE OVERHAUL. UPON INSPECTION OF COMPRESSOR PARTS NOTED T	HE FOLLOWING: STEP WEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEA	RSHAFT.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995051200163	19950512	00163	GL 	1995	5	12	HEEA954915 	2	19950504	G	7250	23031494	LAB SEAL 		23031925 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					NR 8 BEARING	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03					CAT90593		CAE890585S			RECEIVING INSPECTION OF NEW, NEVER INSTALLED #8 BEARING. LAB SEAL INDICATED EXCESSIVELY FLATTENED LAB SEAL. INSTALLED 	NEW LAB SEAL.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995051200164	19950512	00164	GL 	1995	5	12	HEEA954916 	2	19950504	G	7250	23031478	BEARING 		23035128 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30P 	03013	GL 					NR 8 BEARING	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03					CAT95521		CAE900058			ENGINE REMOVED FOR MODIFICATION. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: PULLER GROOVE MISSING ON #8 BEA	RING. INSTALLED NEW #8 BEARING.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995051200165	19950512	00165	GL 	1995	5	12	HEEA954917 	2	19950504	G	7250	6895801	WHEEL 		23031899 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					1ST STAGE BLADE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3905B	1216 			CAT70739	45598	CAE860510			ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON 1ST	 STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995051200166	19950512	00166		1995	5	12	HEEA954918 	4	19950504	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2277A					3630				INOPERATIVE. NO OUTPUT. REPLACED WEAK V101 CAVITY OSCILLATOR AND INOPERATIVE. V301 PHOTODETECTOR. INSTALLED Q415 HEAT 	SINK ACCORDING TO KT76A MOD 6. ADJUSTED AS NEEDED. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995051200167	19950512	00167		1995	5	12	HEEA954919 	4	19950504	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	10814					45415				TOTALLY INOPERATIVE. REPLACED TRANSISTOR Q415. REPAIRED PROBLEM. BENCH CHECK GOOD.						1	G	7	1 	3U				H2SW 					 
1995051200168	19950512	00168		1995	5	12	HEEA954920 	4	19950504	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6603X					51412				INOPERATIVE. FOUND REPLY LIGHT TO BE DIM. REPLACED PHOTOCELL V301. REPAIRED. REPLACED DETERIORATED RESISTOR R477. FO	UND INTERMITTENT PULSES ON OSCILLOSCOPE WHEN DIALING THROUGH FREQUENCIES. CLEANED CONTACTS ON ALL WAFERS. REPAIRED. B	ENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995051200169	19950512	00169		1995	5	12	HEEA954921 	4	19950504	G	3452	066106200	TRANSCEIVER 		KT76 	SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT ATC	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	60951					2771				TRANSPONDER WILL NOT TEST. ADJUSTED FREQUENCY. UNIT BENCH CHECK GOOD.						1	G	7	1 	3U				H9EU 					 
1995051200170	19950512	00170		1995	5	12	HEEA954922 	4	19950504	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ATC	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	7171A									WILL NOT TEST. REPLACED DS301 REPLY LAMP BULB. ALIGNED PRESELECTOR, ADJUSTED PULSE AND FREQUENCY. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995051200171	19950512	00171		1995	5	12	HEEA954923 	4	19950504	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911FL					S717				NO TRANSMIT POWER. REPLACED V101 CAVITY OSCILLATOR. REPLACED BROKEN FACE-PLATE ASSY. LOCKING MECHANISM BROKEN; REPLACE	D SCREW, FLAT WASH AND GROOVE PIN. REPAIRED. ADJUSTED V101 AND MEETS MFGS SPECS.					1	G	7	2 	3U				H3EU 					 
1995051200172	19950512	00172		1995	5	12	HEEA954924 	4	19950504	G	2312	071121612	CONTROL UNIT 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				LOWER SECTION HAD SEGMENTS MISSING AND INTERMITTENT. FOUND CORROSION UNDER HEADER J203. REPLACED HEADER J203 AND CLEANE	D CORROSION. REPAIRED PROBLEM. CHECKED 28V BACKLIGHTING. BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995051200173	19950512	00173		1995	5	12	HEEA954925 	4	19950504	G	3454	071121627	CONTROL 			BELL 	412 	412 	1182202	SW 										COCKPIT NAV	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				SECOND NUMBER DIGITAL READOUT INOPERATIVE. REPLACED BROKEN SPOOL ON TOP OF SWITCH S103. REPAIRED. ALSO REPLACED INTERM	ITTENT TRANSFER SWITCH S102. REPLACED HEADER P201 AND APPLIED HUMISEAL TO HEADER FOR CORROSION CONTROL. FOUND BRIGHT S	POT ON DISPLAY. REPLACED DISPLAY DS101. REPAIRED.BENCH CHECK GOOD.				1	G	7	2 	4U				H4SW 					 
1995051200174	19950512	00174		1995	5	12	HEEA954926 	4	19950504	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	5435V	2233 				760158				CVR DOES NOT TEST.						1	G	7	2 	3U				H1NE 					 
1995051200175	19950512	00175		1995	5	12	HEEA954927 	4	19950504	G	3453	4530103	LORAN 	ARNAV 	ARNAV21 	BELL 	206 	206B 	1181511	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268A					3602				NAV FLAGGED FOR 25 MINUTES.						1	G	7	1 	3U				H2SW 					 
1995051200176	19950512	00176	SW 	1995	5	12	HEEA954928 	1	19950504	G	2436	206075447007	REGULATOR 			BELL 	206 	206L3 	1182108	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6603X					51412				GENERATOR WOULD NOT COME ON LINE.						1	G	7	1 	3U				H2SW 					 
1995051200177	19950512	00177		1995	5	12	HEEA954929 	4	19950504	G	3422	5050010902	GYRO 		200 	SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT DG	TRIPS BREAKER 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951					2771				POPS CIRCUIT BREAKER. REPLACED WITH SERVICEABLE D.G. AND RETURNED AIRCRAFT TO SERVICE.						1	G	7	1 	3U				H9EU 					 
1995051200178	19950512	00178		1995	5	12	HEEA954930 	4	19950504	G	2370	9806019001	CVR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5748M	4267 				28102				CVR INOPERATIVE; WILL NOT TEST.						2	G	7	2 	4U				H10SW 					 
1995051900086	19950519	00086	SW 	1995	5	19	HEEA954931 	1	19950508	G	6730	212076005105	CYL ASSY 			BELL 	412 	412 	1182202	SW 										M/R	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03		1323 								SERVO SENT IN FOR REPAIR - FOUND SERVO LEAKING AT BOTH END CAPS, GLAND & AT INTERCONNECT CYLINDER.						1	G	7	2 	4U				H4SW 					 
1995051900087	19950519	00087	SW 	1995	5	19	HEEA954932 	1	19950508	G	6730	212076004005	SERVO ACT 			BELL 	412 	412 	1182202	SW 										M/R	LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03		2140 								SERVO SENT IN FOR OVERHAUL- FOUND INTERNAL LEAK AND EXCESSIVE BREAK OUT FORCE ON PILOT LEVER.						1	G	7	2 	4U				H4SW 					 
1995051900088	19950519	00088	SW 	1995	5	19	HEEA954933 	1	19950508	G	6730	212076005105	CYL ASSY 			BELL 	412 	412 	1182202	SW 										M/R	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03		1427 								SERVO SENT IN FOR REPAIR- FOUND SERVO LEAKING AT BOTH END CAPS, GLAND & AT INTERCONNECT CYLINDER.						1	G	7	2 	4U				H4SW 					 
1995051900089	19950519	00089	SW 	1995	5	19	HEEA954934 	1	19950508	G	6730	212076005105	CYL ASSY 			BELL 	412 	412 	1182202	SW 										M/R	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03		2022 								SERVO SENT IN FOR OVERHAUL- FOUND SERVO LEAKING AT BOTH END CAPS, GLAND & AT INTERCONNECT CYLINDER.						1	G	7	2 	4U				H4SW 					 
1995051900090	19950519	00090	EU 	1995	5	19	HEEA954936 	1	19950509	G	7130	350A5801100801	FIREWALL ASSY 			SNIAS 	350 	AS350B2 	8680813	EU 										ENG COMPT	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1064 				2771				FIREWALL CRACKED IN APPROXIMATELY SEVEN PLACES. REPAIRED FIREWALL.						1	G	7	1 	3U				H9EU 					 
1995051900091	19950519	00091	EU 	1995	5	19	HEEA954937 	1	19950509	G	5512	350A1305200302	SKIN 			SNIAS 	350 	AS350B2 	8680813	EU 										HORIZ LT LOWER	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1064 	1064 			2771				CRACK ON L/H LOWER OUTER SKIN. STOP DRILLED CRACK.						1	G	7	1 	3U				H9EU 					 
1995051900092	19950519	00092	SW 	1995	5	19	HEEA954939 	1	19950509	G	6220	412010124109	BOLT 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6559Z	1494 			AAD00018	36019				CARBIDE COATING FLAKING BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995051900093	19950519	00093	SW 	1995	5	19	HEEA954940 	1	19950509	G	6230	206010452109	SUPPORT 		206010450113	BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	REQ REPLACEMENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5000K	1432 			GDJG10354	45167				PER ASB 206L-93-89 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT) HELD FOR CSR SIGNATURE. PHI REQUESTS FOR PRO-R	ATED WARRANTY CREDIT AS OUTLINED IN BULLETIN.					1	G	7	1 	3U				H2SW 					 
1995051900094	19950519	00094	NE 	1995	5	19	HEEA954941 	2	19950510	G	7510	5044T08P05	VALVE 			BELL 	214 	214ST 	1182106	SW 	GE 	CT7TS 	CT72A 	30030	NE 					ENGINE AI	CORROSION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101	GEE343061			ANTI ICE VALVE CORROSION.						2	G	7	2 	4U	4	U		H10SW 	E8NE				 
1995051900095	19950519	00095	NE 	1995	5	19	HEEA954942 	2	19950510	G	7313	5051T35G05	NOZZLE 			BELL 	214 	214ST 	1182106	SW 	GE 	CT7TS 	CT72A 	30030	NE 					ENG FUEL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8045T					28101	GEE343006			FUEL NOZZLE DEFECTIVE. EXCESSIVE DROOLING AND SPITTING. SERIAL NUMBERS REMOVED PKHC4238 & PANO0613 & PKHA8102.						2	G	7	2 	4U	4	U		H10SW 	E8NE				 
1995051900096	19950519	00096	NE 	1995	5	19	HEEA954943 	2	19950510	G	7421	4053T22P06	IGNITOR 			BELL 	214 	214ST 	1182106	SW 	GE 	CT7TS 	CT72A 	30030	NE 					ENGINE	ERRODED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8045T					28101	GEE343006			TWO EACH IGNITOR PLUGS ERRODED.						2	G	7	2 	4U	4	U		H10SW 	E8NE				 
1995051900097	19950519	00097	SW 	1995	5	19	HEEA954944 	1	19950510	G	6220	412010106101	BEARING 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N	4989 			A473	33010				SEPARATION BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995051900098	19950519	00098	SW 	1995	5	19	HEEA954945 	1	19950510	G	6220	412010106101	BEARING 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N	3273 			A473	33010				SEPARATION BEYOND LIMITS. BEARING S/N LK3275 & LK3388						1	G	7	2 	4U				H4SW 					 
1995051900099	19950519	00099	SW 	1995	5	19	HEEA954946 	1	19950510	G	6220	412010145103	DAMPER SET 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N	2410 			A473	33010				DAMPER SET SEPARATION BEYOND LIMITS. SERIAL NUMBERS REMOVED 2809, 2815, 2826 AND 2803.						1	G	7	2 	4U				H4SW 					 
1995051900100	19950519	00100		1995	5	19	HEEA954947 	4	19950510	G	3454	071107600	RECEIVER 		KDA697 	BELL 	212 	212 	1181420	SW 										COCKPIT NR 1	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1074C					30989				#1 VOR INOPERATIVE.						1	G	7	1 	4U				H4SW 					 
1995051900101	19950519	00101		1995	5	19	HEEA954948 	4	19950510	G	3457	0845000000	SKYNAV 5000 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT GPS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	350BZ					2653				SKY NAV 5000 INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995051900102	19950519	00102	SW 	1995	5	19	HEEA954949 	1	19950510	G	7714	412075010109	INDICATOR 			BELL 	412 	412 	1182202	SW 										TRIPLE TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				#1 & #2 NEEDLES HAVE A 3% SPLIT THROUGHOUT						1	G	7	2 	4U				H4SW 					 
1995051900103	19950519	00103	NE 	1995	5	19	HEEA954950 	1	19950510	G	6210	7615009043051	TIP CAP 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										TIP CAP HAS A CREASE IN THE ABRASION STRIP ON THE LOWER SIDE AS MARKED.						1	G	7	2 	3U				H1NE 					 
1995051900104	19950519	00104	NE 	1995	5	19	HEEA954951 	1	19950510	G	6410	7610105101041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	WONT BALANCE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	706AE	8767 				760275				T/R BLADE DOES NOT BALANCE. PADDLE "B" IS APPROXIMATELY 29 GRAM HEAVIER THAN PADDLE "A" SUSPECT H20 IN PADDLE "B".						1	G	7	2 	3U				H1NE 					 
1995051900105	19950519	00105	NE 	1995	5	19	HEEA954952 	1	19950510	G	6410	7610105101041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545X	10655				760050				CRACK ON THE ABRASION STRIP WITH MULTIPLE BRANCH ON PADDLE "B".						1	G	7	2 	3U				H1NE 					 
1995051900106	19950519	00106	SW 	1995	5	19	HEEA954953 	1	19950510	G	6210	206015001107	BLADE 			BELL 	206 	206L3 	1182108	SW 										M/R	UNBONDED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4180F	2899 				51469				#1 LOWER FINGER UNBONDED BEYOND THE MAXIMUM LIMIT.						1	G	7	1 	3U				H2SW 					 
1995051900107	19950519	00107	SW 	1995	5	19	HEEA954954 	1	19950510	G	7714	206075681117	INDICATOR 			BELL 	206 	206L3 	1182108	SW 										DUAL TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6160Z					51610				TURBINE NEEDLE DROPS 20 RPM WHEN AIRCRAFT IS AT 100 RPM. TIME SINCE REPAIR 16:45.						1	G	7	1 	3U				H2SW 					 
1995051900108	19950519	00108	SW 	1995	5	19	HEEA954955 	1	19950510	G	6240	206075681117	INDICATOR 			BELL 	206 	206L3 	1182108	SW 										DUAL TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6160Z					51610				LOW ROTOR WARNING HORN WILL NOT MUTE WHEN REDUCED TO IDLE.						1	G	7	1 	3U				H2SW 					 
1995051900109	19950519	00109	EU 	1995	5	19	HEEA954956 	1	19950510	G	5610	3503005	WINDSHIELD 			AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5796S					5164				MISTY LOOK IN GLASS (VERY DISTORTED)						1	G	7	2 	3U				H11EU 					 
1995051900110	19950519	00110		1995	5	19	HEEA954957 	4	19950510	G	2312	064102300	TRANSCIEVER 			BELL 	412 	412 	1182202	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				#1 VHF HAS SQUEAL IN BOTH TRANSMIT AND RECEIVE.						1	G	7	2 	4U				H4SW 					 
1995051900111	19950519	00111		1995	5	19	HEEA954958 	4	19950510	G	2312	069102443	TRANSCEIVER 		KX155 	BELL 	206 	206B 	1181511	SW 										COCKPIT VHF	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2020R					3599				TRANSCEIVER INOPERATIVE; UNIT DOESN'T POWER UP. FOUND BURNT FOIL FOR 27.5V LINE FROM R400 RESISTOR TO E444 BOTH LOCATED 	ON THE MAIN BOARD. ALSO FOUND DS101 DISPLAY HAD SOME VERY WEAK DIGITS DISPLAYED. REPLACED DS101 AND REPAIRED. BENCH C	HECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995051900112	19950519	00112		1995	5	19	HEEA954959 	4	19950510	G	3455	066107200	RECEIVER 		KR87 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21240					45647				SOME LED SEGMENTS DON'T DISPLAY. REPLACED DISPLAY. REPAIRED. FOUND LOWER DOT ON COLON ON STANDBY SIDE VERY BRIGHT AND 	DOES NOT DISAPPEAR WHEN TRANSFERRING FREQUENCIES. REPLACED INTEGRATED CIRCUIT I507. REPAIRED. INSPECTED FOR CORROSION	. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995051900113	19950519	00113		1995	5	19	HEEA954960 	4	19950510	G	2312	071121525	CONTROL UNIT 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	401PH					7050				CANNOT CHANGE FREQUENCIES. REPLACED BAD TRANSFER SWITCH S102. REPAIRED. REPLACED WEAK DISPLAY DS101 AND FADED LENS. R	EPLACED HEADER P201 AND APPLIED HUMISEAL TO HEADER FOR CORROSION CONTROL. BENCH CHECK GOOD.					1	G	7	2 	3U				H13EU 					 
1995051900114	19950519	00114	EU 	1995	5	19	HEEA954961 	1	19950510	G	2436	51565000R	REGULATOR 			BOLKMS	105 	BO105S 	5626006	EU 										DC VOLTS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	81992					S827				COULD NOT ADJUST OVERVOLTAGE. REPLACED Q4 TRANSISTOR P/N 03-0044-28, R65 RESISTOR P/N 05-508624. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995051900115	19950519	00115	NE 	1995	5	19	HEEA954962 	1	19950510	G	2430	51530006A	CONTROL UNIT 			SKRSKY	S76 	S76A 	8143006	NE 										DC SYS	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1545K					760047				CORRODED. REPLACED J1 CONNECTOR P/N MS3470L20-16P, COVER P/N 51530-1055. BENCH CHECK GOOD.						1	G	7	2 	3U				H1NE 					 
1995051900116	19950519	00116		1995	5	19	HEEA954963 	4	19950510	G	3457	0845000000	SKYNAV 5000 			BELL 	206 	206L1 	1182107	SW 										COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2246Q					45752				SKYNAV 5000 DOES NOT PICK UP SIGNALS.						1	G	7	1 	3U				H2SW 					 
1995051900117	19950519	00117	SW 	1995	5	19	HEEA954964 	1	19950510	G	7712	412075008111	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT TORQUE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				INDICATOR LIGHTS TOO DIM.						1	G	7	2 	4U				H4SW 					 
1995051900118	19950519	00118		1995	5	19	HEEA954965 	4	19950510	G	3452	066106201	TRANSPONDER 		KT78A 	BOLKMS	105 	BO105C 	5626005	EU 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	205BB					S58				INOPERATIVE. REPLACED WEAK V101 CAVITY OSCILLATOR, WEAK V301 PHOTOCELL AND WEAK CR202 MIXER DIIODE. ADJUSTED PULSE WID	TH AND FREQUENCY. BENCH CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995051900119	19950519	00119	NE 	1995	5	19	HEEA954966 	1	19950510	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	EDGE SPLIT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5444X					760174				TIP CAP HAS THE TRAILING EDGE SPLIT OPEN APPROXIMATELY THREE INCHES.						1	G	7	2 	3U				H1NE 					 
1995051900120	19950519	00120	SW 	1995	5	19	HEEA954967 	1	19950510	G	2430	51509002R	CONTROL UNIT 			BELL 	412 	412 	1182202	SW 										DC SYS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	23023					33080				INOPERATIVE, GENERATOR WON'T COME ON LINE. REPLACED VR13, VR17 ZENER DIODES P/N 05-900964, VR16 ZENER DIODE P/N 03-0065-	10 ON CIRCUIT BOARD P/N 51509-363. BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995051900121	19950519	00121	SW 	1995	5	19	HEEA954968 	1	19950510	G	2430	51509002R	CONTROL UNIT 			BELL 	412 	412 	1182202	SW 										DC SYS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	23023					33080				INOPERATIVE; GENERATOR WON'T COME ON LINE. REPLACED VR16 ZENER DIODE P/N 03-0065-10 ON CIRCUIT BOARD P/N 51509-363. BEN	CH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995051900122	19950519	00122	SW 	1995	5	19	HEEA954969 	1	19950510	G	2436	214175153105	REGULATOR 			BELL 	214 	214ST 	1182106	SW 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				GENERATOR KICKS OFF INTERMITTENTLY DURING CROSS START.						2	G	7	2 	4U				H10SW 					 
1995051900123	19950519	00123	SW 	1995	5	19	HEEA954970 	1	19950510	G	7714	212070160101	INDICATOR 			BELL 	212 	212 	1181420	SW 										DUAL TACH	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3131S					30953				#2 NEEDLE STICKS ON LOW END.						1	G	7	1 	4U				H4SW 					 
1995051900124	19950519	00124	EU 	1995	5	19	HEEA954971 	1	19950511	G	7810	117651121	TAIL PIPE ASSY 			BOLKMS	117 	BK117B2 	5626013	EU 										ENG EXH	LOOSE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	960 				7238				TAILPIPE CAME LOOSE. FOUND CRACK AROUND ONE SUPPORT ROD.						1	G	7	2 	3U			NC	H13EU 					 
1995051900125	19950519	00125	EU 	1995	5	19	HEEA954972 	1	19950511	G	5210	T6408103	SLIDER 			BOLKMS	117 	BK117B2 	5626013	EU 										LT-RT DOORS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	954 				7238				REPLACED SLIDES ON L/H AND R/H AFT SLIDING DOORS.						1	G	7	2 	3U			NC	H13EU 					 
1995051900126	19950519	00126	EU 	1995	5	19	HEEA954973 	1	19950511	G	6520	1053040212	FITTING 			BOLKMS	117 	BK117B2 	5626013	EU 										T/R GR BOX	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	916 				7238				HAIRLINE CRACK ON INSIDE CASTING NEAR L/H UPPER MOUNT HOLE.						1	G	7	2 	3U			NC	H13EU 					 
1995051900127	19950519	00127	SW 	1995	5	19	HEEA954976 	1	19950512	G	6520	222042001007	GEARBOX 			BELL 	230 	230 	1182149	SW 										T/R	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	230UN	2004 				23009				REPAIR DUE TO SEALS LEAKING.						1	G	7	2 	3U			NC	H9SW 					 
1995051900128	19950519	00128	SW 	1995	5	19	HEEA954977 	1	19950512	G	6230	206010336005	LINK ASSY 			BELL 	206 	206L 	1181522	SW 										M/R PYLON	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W					52033				DRIVE LINK BUSHINGS WORN. LISTED BELOW ARE REPLACEMENT PART INFORMAITON: P/N 206-010-337-001, BUSHING, 4 EACH, PO# 950	0130, P/N 206-010-338-001, SPACER, 4 EACH, P/N 20-057-5-64D, BOLT, 2 EACH, P/N 20-057-4-9, BOLT, 2 EACH, P/N MS14144L-	5, NUT, 2 EACH, P/N MS21042L-4, NUT, 2 EACH,				1	G	7	1 	3U				H2SW 					 
1995051900129	19950519	00129	EU 	1995	5	19	HEEA954978 	1	19950512	G	6230	350A37116200	YOKE ASSY 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1098 				2771				DROOP RING FORK SUPPORTS WORN AND ONE BROKEN.						1	G	7	1 	3U				H9EU 					 
1995051900130	19950519	00130	EU 	1995	5	19	HEEA954979 	1	19950512	G	6730	SC50811	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R CONTROL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	60951	1219 				2771				LEAKING BETWEEN SERVO BODY AND SERVO SHAFT. ALSO LEAKING FROM SMALL HOLE IN SERVO SHAFT.						1	G	7	1 	3U				H9EU 					 
1995051900131	19950519	00131	EU 	1995	5	19	HEEA954980 	1	19950512	G	3340	356H2801	LIGHT 			SNIAS 	350 	AS350B2 	8680813	EU 										ANTI COLL	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1161 				2771				ANTI-COLLISION LIGHT INOPERATIVE AND MOUNTING BRACKET WORN & BROKEN.						1	G	7	1 	3U				H9EU 					 
1995051900132	19950519	00132		1995	5	19	HEEA954981 	4	19950512	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268X					3607				NEEDS BENCH CHECK. INSPECTED. INSTALLED HEATSINK BEHIND TRANSISTOR Q415 AS PER KING SERVICE BULLETIN KT76-A-6. REPLACE	D PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. UNIT HAS WEAK POWER OUT AND UNABLE TO ADJUST FREQUENCY TO SPECS. REPLACED CA	VITY TUBE V101. REPAIRED.CLEANED CONTACTS ON WAFER SWITCHES. ADJUSTED PULSE WIDTH AND FREQUENCY. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995051900133	19950519	00133		1995	5	19	HEEA954982 	4	19950512	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B3 	1181506	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2270G					3610				DOES NOT REPLY. REPLACED V101 (CAVITY OSCILLATOR), REPAIRED. BENCH CHECK GOOD.						1	G	7	1 	3U				H2SW 					 
1995051900134	19950519	00134		1995	5	19	HEEA954983 	4	19950512	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4193R					S851				FACE COVER BROKE AND FALLING OFF. REPLACED FACEPLATE ASSY. FOUND UNIT TO HAVE WEAK POWER OUT. REPLACED CAVITY TUBE V10	1. REPAIRED. ADJUSTED PULSE WIDTH. BENCH CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995051900135	19950519	00135		1995	5	19	HEEA954984 	4	19950512	G	3457	0110005400	GPS 150 			BELL 	212 	212 	1181420	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5736D					31135				GPS DOES NOT TURN ON.						1	G	7	1 	4U				H4SW 					 
1995051900136	19950519	00136	EU 	1995	5	19	HEEA954985 	1	19950512	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5421E	8145 				S806				NOSE AND NECK SHELLS CRACKED.						1	G	7	2 	3U				H3EU 					 
1995051900137	19950519	00137	EU 	1995	5	19	HEEA954986 	1	19950512	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5421E	8145 				S806				NOSE AND NECK SHELLS CRACKED.						1	G	7	2 	3U				H3EU 					 
1995051900138	19950519	00138		1995	5	19	HEEA954987 	4	19950512	G	3457	0845000000	SKYNAV 5000 			BEECH 	200 	200CBEECH 	1152926	CE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	39PH					BL3				SKYNAV 5000 HAS LOOSE PART INSIDE CABINET. ON FIRST POWER UP, DISPLAY LOCKED UP. FOUND BROKEN PIECE OF DATA CARD READER	.					1	L	7	2 	4T				A24CE 					 
1995051900139	19950519	00139	SW 	1995	5	19	HEEA954988 	1	19950512	G	6220	412010145103	DAMPER SET 		412010100193	BELL 	412 	412 	1182202	SW 										M/R	REQ REPLACEMENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	21498				AAD50055	36003				REMOVED TO INSTALL NEW STYLE DAMPER SET P/N 412-010-145-105. S/N 2326 & 2311						1	G	7	2 	4U				H4SW 					 
1995051900140	19950519	00140	SW 	1995	5	19	HEEA954989 	1	19950512	G	6220	412010145103	DAMPER SET 		412010100193	BELL 	412 	412 	1182202	SW 										M/R	SEPERATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7128R	3796 			AAD50026	36007				SEPARATION BEYOND LIMITS. S/N 1801, 1791 & 2313						1	G	7	2 	4U				H4SW 					 
1995051900141	19950519	00141		1995	5	19	HEEA954990 	4	19950512	G	3414	8000A	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT A/S	NEEDLE LOOSE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5000K					45167				NEEDLE APPEARS TO BE LOOSE ON HANDSTAFF.						1	G	7	1 	3U				H2SW 					 
1995051900142	19950519	00142	EU 	1995	5	19	HEEA954991 	1	19950512	G	2840	BSE20660G1	TRANSDUCER 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL PRESS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7136J					S830				NO INDICATION WHEN CONNECTED TO AIRCRAFT.						1	G	7	2 	3U				H3EU 					 
1995051900143	19950519	00143	SW 	1995	5	19	HEEA954992 	1	19950512	G	6320	206040004107	TRANSMISSION 			BELL 	206 	206L3 	1182108	SW 										M/R	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8590X	3091 				51494				TRANSMISSION MAKING METAL. CAUSE OF METAL: BEARING SPALLED. REPAIRED AND REPLACED BEARING AND RETURNED AIRCRAFT TO SER	VICE.					1	G	7	1 	3U				H2SW 					 
1995051900144	19950519	00144	SW 	1995	5	19	HEEA954993 	1	19950512	G	6320	206031509101	DRAG PIN ASSY 			BELL 	206 	206B 	1181511	SW 										TRANSMISSION	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3181J					3771				BEARING BECAME UNSTAKED. REPLACED WITH SERVICEABLE DRAG PIN.						1	G	7	1 	3U				H2SW 					 
1995051900145	19950519	00145	NE 	1995	5	19	HEEA954994 	1	19950512	G	3260	7655200904043	WIRING HARNESS 			SKRSKY	S76 	S76A 	8143006	NE 										MLG	DEFECTIVE 	E			HEEA	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			SW	03	707AE					760276				#1 AND #2 SERVO CAUTION LIGHTS STAY ON AND WOULD NOT EXTINGUISH. REPLACED LEFT HAND LANDING GEAR WIRING HARNESS AND THE 	PROBLEM WAS CURED. THE WEIGHT ON WHEELS SENSOR HAD AN OPEN CIRCUIT WHEN IT SHOULD HAVE BEEN ABLE TO FIND A GROUND. THU	S GIVING THE FALSE INDICATION THAT NO WEIGHT WAS ON THE LANDING GEAR.				1	G	7	2 	3U				H1NE 					 
1995051900146	19950519	00146		1995	5	19	HEEA954995 	4	19950512	G	3422	5050010902	GYRO 		200 	SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT DG	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951					2771				DG SPINS INTERMITTENTLY. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H9EU 					 
1995051900147	19950519	00147		1995	5	19	HEEA954996 	4	19950512	G	3452	066106200	TRANSCEIVER 		KT76 	SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	60951					2771				TRANSPONDER WILL NOT TEST. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H9EU 					 
1995051900148	19950519	00148		1995	5	19	HEEA954997 	4	19950512	G	3455	066107700	RECEIVER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT ADF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				BENCH CHECK NEEDED. INSPECTED. FOUND UNIT TO HAVE NO RECEIVER AUDIO. REPLACED TRANSFORMER T113. REPAIRED PROBLEM. RE	PLACED HEADERS J301, J302, J306 AND J307. APPLIED HUMISEAL TO HEADERS FOR CORROSION CONTROL. REPLACED BROKEN BNC SPACE	R. INSTALLED MISSING HEX NUTAND SCREW IN POWER SUPPLY. BENCH CHECK GOOD.				2	G	7	2 	4U				H10SW 					 
1995051900149	19950519	00149		1995	5	19	HEEA954998 	4	19950512	G	3457	0845000000	SKYNAV 5000 			BELL 	412 	412 	1182202	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2014K					33020				SKY NAV 5000 INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995051900150	19950519	00150		1995	5	19	HEEA954999 	4	19950512	G	3421	7660002113103	GYRO 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VG	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1545X					760050				SLOW TO SCROLL AFTER START UP.						1	G	7	2 	3U				H1NE 					 
1995042800670	19950428	00670	SW 	1995	4	28	HEEA955 	1	19950419	G	6310	289052017	SEAL 		206040270009	BELL 	206 	206L1 	1182107	SW 										FREEWHEEL	LEAKING 	B			ZV1R	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2618	151 			B46243	45503				FRONT SEAL LEAKING. FOUND SEAL WAS FLAT AND HAD LOST ELASTICITY. REPLACED FRONT SEAL.						1	G	7	1 	3U				H2SW 					 
1995051900151	19950519	00151	EU 	1995	5	19	HEEA955000 	1	19950512	G	6320	4638201003	CENTER CASE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R XMSN	WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5421E					S806				CENTER CASE TAIL ROTOR BORE WORN BEYOND LIMITS.						1	G	7	2 	3U				H3EU 					 
1995052600104	19950526	00104	SW 	1995	5	26	HEEA955001 	1	19950515	G	6230	206010452109	SUPPORT 			BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	REQ REPLACEMENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	20898	1819 				45721				REMOVED TO COMPLY WITH ASB 206L-93-89 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995052600105	19950526	00105	SW 	1995	5	26	HEEA955002 	1	19950515	G	5320	206031314091S	CHANNEL 			BELL 	206 	206L1 	1182107	SW 										FUSELAGE	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	2251A					45755				CHANNEL HAS PILOT HOLES DRILLED ON AFT END. THEY DO NOT LINE UP WITH THE HOLES ON THE CHANNEL THAT WAS REMOVED. (NO ED	GE DISTANCE)					1	G	7	1 	3U				H2SW 					 
1995052600106	19950526	00106	SW 	1995	5	26	HEEA955003 	1	19950515	G	6200	214031601107	RESTRAINT ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				BEARING WORN. RECEIVED INSTALLED ON N5748M ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995052600107	19950526	00107	SW 	1995	5	26	HEEA955004 	1	19950515	G	6710	214001970111	ACTUATOR ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R CONTROL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				KEEPS FALLING OFF LINE. RECEIVED INSTALLED ON N5748M ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995052600108	19950526	00108	SW 	1995	5	26	HEEA955005 	1	19950517	G	6230	206010452109	SUPPORT 		206010450113	BELL 	206 	206B 	1181511	SW 										SWASHPLATE	REQ REPLACEMENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	39122	1893 			JIJG09264	3312				REMOVED TO COMPLY WITH ASB 206-93-74 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995052600109	19950526	00109	SW 	1995	5	26	HEEA955006 	1	19950517	G	6420	205012710001	BEARING 		212011701101	BELL 	412 	412 	1182202	SW 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N	999 			A802	33010				ANODIZED SURFACE WORN THROUGH AND CORROSION. BEARINGS SCRAPPED LOCALLY.						1	G	7	2 	4U				H4SW 					 
1995052600110	19950526	00110	SW 	1995	5	26	HEEA955007 	1	19950517	G	6220	206011154107	STRAP 		206011100149	BELL 	206 	206B 	1181511	SW 										M/R	REQ REPLACEMENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268X	518 			A2047	3607				REMOVED DUE TO 2 YEAR RETIREMENT AS PER AD 78-11-02R1. S/N'S LK8068 & LK8052						1	G	7	1 	3U				H2SW 					 
1995052600111	19950526	00111	SW 	1995	5	26	HEEA955008 	1	19950518	G	6410	212010750105	BLADE 		212011701101	BELL 	412 	412 	1182202	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N	999 			A802	33010				CRACK BETWEEN PHENOLIC BLOCK AT GRIP PLATE.						1	G	7	2 	4U				H4SW 					 
1995052600112	19950526	00112	NE 	1995	5	26	HEEA955009 	1	19950518	G	6410	7610105101041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	PAD MISSING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5435V	6320 				760158				BUMPER PAD MISSING ON THE SPAR ON THE INBOARD SIDE OF PADDLE "A".						1	G	7	2 	3U				H1NE 					 
1995052600113	19950526	00113	EU 	1995	5	26	HEEA955010 	1	19950518	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911FL	3104 				S717				NOSE AND NECK SHELL CRACK NEAR THE ROOT END.						1	G	7	2 	3U				H3EU 					 
1995052600114	19950526	00114	SW 	1995	5	26	HEEA955011 	1	19950518	G	2436	206075447007	REGULATOR 			BELL 	206 	206L3 	1182108	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3116L					51529				GENERATOR WOULD NOT COME ON LINE.						1	G	7	1 	3U				H2SW 					 
1995052600115	19950526	00115		1995	5	26	HEEA955012 	4	19950518	G	2312	064105430	TRANSCEIVER 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC					7152				LIGHTS WILL NOT GET BRIGHT. FOUND 25K KNOB INOPERATIVE. REPLACED SWITCH S501. REPAIRED. BENCH CHECK GOOD.						1	G	7	2 	3U				H13EU 					 
1995052600116	19950526	00116		1995	5	26	HEEA955013 	4	19950518	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7171A									DOESN'T RECEIVE ON TRANSMIT. REPLACED CAVITY TUBE V101. REPAIRED. ADJUSTED PULSE WIDTH, FREQUENCY AND POWER OUT. BENC	H CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995052600117	19950526	00117	SW 	1995	5	26	HEEA955014 	1	19950518	G	6220	412010145103	DAMPER SET 		412010100193	BELL 	412 	412 	1182202	SW 										M/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6559Z	3112 			AAD00018	36019				SEPARATION BEYOND LIMITS. SERIAL NUMBERS REMOVED ARE 1913, 1886, 2418 AND 2414.						1	G	7	2 	4U				H4SW 					 
1995052600118	19950526	00118		1995	5	26	HEEA955015 	4	19950518	G	3457	0110010600	GPS 	GARMIN INTL 	GPS165 															COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										CRACKED EPROM SOCKET.																			 
1995052600119	19950526	00119	EU 	1995	5	26	HEEA955016 	1	19950518	G	7722	1179405107	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT TOT	READS HIGH 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC					7152				INDICATOR READS 40 DEGREES HIGH.						1	G	7	2 	3U				H13EU 					 
1995052600120	19950526	00120		1995	5	26	HEEA955017 	4	19950518	G	2200	2593996333	TARSYN 333 			BELL 	212 	212 	1181420	SW 										AUTO FLIGHT	FAILS TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	5736J					31140				FAILS FAST SYNC RATE #8.5 ON SST.						1	G	7	1 	4U				H4SW 					 
1995052600121	19950526	00121	EU 	1995	5	26	HEEA955018 	1	19950518	G	7931	1176131203	SWITCH 			BOLKMS	117 	BK117B2 	5626013	EU 										OIL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	134AE	1110 				7237				SWITCH WILL NOT CLOSE.						1	G	7	2 	3U			NC	H13EU 					 
1995052600122	19950526	00122	SW 	1995	5	26	HEEA955019 	1	19950518	G	5330	205031282058	PANEL ASSY 			BELL 	212 	212 	1181420	SW 										RT FUEL CELL	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5736J					31140				R/H LOWER FUEL CELL PANEL DOES NOT FIT CONTOUR OF AIRCRAFT.						1	G	7	1 	4U				H4SW 					 
1995052600123	19950526	00123		1995	5	26	HEEA955020 	4	19950518	G	3421	1113034	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT ATTITUDE	FLAG STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				ATT. FLAG STICKING. TIME SINCE REPAIR 412:10.						1	G	7	2 	4U				H4SW 					 
1995052600124	19950526	00124	SW 	1995	5	26	HEEA955021 	1	19950518	G	5620	M206R309L2	WINDOW 			BELL 	206 	206L1 	1182107	SW 										RT AFT SLIDER	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2754W					45260				AFT LOWER EDGE OF WINDOW AT AFT END OF SLIDING WINDOW TRACK SEPARATED FROM GLASS. CANNOT REMOVE SLIDING WINDOW. ALSO T	OP SECTION OF TRACK AT AFT END COLLAPSED AGAINST WINDOW.					1	G	7	1 	3U				H2SW 					 
1995052600125	19950526	00125	SW 	1995	5	26	HEEA955022 	1	19950518	G	2841	393008047	INDICATOR 			BELL 	412 	412 	1182202	SW 										FUEL QTY	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3911L					33023				NEEDLE INTERMITTENTLY STICKS AT 100 POUNDS GOING DOWN SCALE.						1	G	7	2 	4U				H4SW 					 
1995052600126	19950526	00126	SW 	1995	5	26	HEEA955023 	1	19950518	G	6240	206070265101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										DUAL TACH	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1073W					45386				TURBINE NEEDLE INTERMITTENTLY STICKS THROUGHOUT SCALE.						1	G	7	1 	3U				H2SW 					 
1995052600127	19950526	00127	GL 	1995	5	26	HEEA955024 	2	19950518	G	7421	CH34269	IGNITER PLUG 			BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	105WK	281 				S812				TIP WORN AND CORRODED, NO IGNITION.						1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995052600128	19950526	00128	EU 	1995	5	26	HEEA955025 	1	19950518	G	6340	KDW02	RPM WARNING BOX 			BOLKMS	105 	BO105S 	5626006	EU 										ROTOR DRIVE	CASE CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	205BB					1234				CRACKED CASE. TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H3EU 					 
1995052600129	19950526	00129		1995	5	26	HEEA955026 	4	19950518	G	2562	ELT910	ELT 	NARCO 		BELL 	206 	206B3 	1181506	SW 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2270G					3610				ELT MALFUNCTION. DISCONNECTED BATTERY, WON'T SHUT OFF.						1	G	7	1 	3U				H2SW 					 
1995052600130	19950526	00130	SW 	1995	5	26	HEEA955027 	1	19950518	G	2810	206064611001	FUEL CELL 			BELL 	206 	206L1 	1182107	SW 										MOUNT INSERT	UNBONDED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5007N					45184				FUEL CELL UNBONDED MOUNTING INSERT AS MARKED IN RED.						1	G	7	1 	3U				H2SW 					 
1995052600131	19950526	00131	EU 	1995	5	26	HEEA955028 	1	19950518	G	3610	704A32113019	VALVE 			AEROSP	AS355 	AS355F1 	8680810	EU 										PNEUMATIC SYS	DISCONNECTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5796S					5164				FLAPPER VALVE DISCONNECTED.						1	G	7	2 	3U				H11EU 					 
1995052600132	19950526	00132	SW 	1995	5	26	HEEA955029 	1	19950518	G	6410	214015700115	BLADE 			BELL 	214 	214ST 	1182106	SW 										T/R	SEPARATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N	1162 				28106				TRAILING EDGE SEPARATED.						2	G	7	2 	4U				H10SW 					 
1995052600133	19950526	00133		1995	5	26	HEEA955031 	4	19950519	G	3421	7660002113102	GYRO 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VG	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546K					760082				CO-PILOT GYRO RATCHETY.						1	G	7	2 	3U				H1NE 					 
1995052600134	19950526	00134	NE 	1995	5	26	HEEA955032 	1	19950519	G	7810	7630507003044	EJECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										EXHAUST	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5426U					760167				EJECTOR CRACKED.						1	G	7	2 	3U				H1NE 					 
1995052600135	19950526	00135		1995	5	26	HEEA955033 	4	19950519	G	3416	5035P2P44	ALTIMETER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT ENCODER	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5435V					760158				HUNDREDS NEEDLE INTERMITTENTLY AT 10,000 FEET AND ABOVE. TIME SINCE REPAIR 1286:45.						1	G	7	2 	3U				H1NE 					 
1995052600136	19950526	00136	EU 	1995	5	26	HEEA955034 	1	19950519	G	3350	1179204201	IMPACT SWITCH 			BOLKMS	117 	BK117B1 	5626012	EU 										EEL LIGHTS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC					7152				SWITCH CAUSING EMERGENCY LIGHTS TO COME IN FLIGHT.						1	G	7	2 	3U				H13EU 					 
1995052600137	19950526	00137		1995	5	26	HEEA955035 	4	19950519	G	3416	1003511424	ALTIMETER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	CASE LEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545X					760050				UNIT HAS EXCESSIVE CASE LEAK.						1	G	7	2 	3U				H1NE 					 
1995052600138	19950526	00138	SW 	1995	5	26	HEEA955036 	1	19950519	G	7714	206070265101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										DUAL TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5019F					45244				NEEDLE SPLIT.						1	G	7	1 	3U				H2SW 					 
1995052600139	19950526	00139	SW 	1995	5	26	HEEA955037 	1	19950519	G	7722	212075067109	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT ITT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22608					33075				NEEDLE INTERMITTENTY STICKS WHEN POWER IS APPLIED. TIME SINCE REPAIR 573:50.						1	G	7	2 	4U				H4SW 					 
1995052600140	19950526	00140	EU 	1995	5	26	HEEA955038 	1	19950519	G	6340	1179403605	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										XMSN OIL	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8765J					7054				#2 GAUGE DOESN'T READ PROPERLY- READS LOW. TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H13EU 					 
1995052600141	19950526	00141	SW 	1995	5	26	HEEA955039 	1	19950519	G	6730	C4264268	BEARING 		206076062003	BELL 	206 	206L3 	1182108	SW 										SERVO	LOOSE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X	16 			RH1829	51495				FOUND BOTH BEARINGS UNSTAKED. REPLACED BOTH BEARINGS AND RETURNED SERVO TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995052600142	19950526	00142	SW 	1995	5	26	HEEA955040 	1	19950519	G	5343	206030104001	FITTING ASSY 			BELL 	206 	206L1 	1182107	SW 										CROSSTUBE	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5000K					45167				CORROSION BEYOND LIMITS ON TOP SIDE AND WHERE CROSS TUBE RIDES. REPLACED WITH SERVICEABLE FITTING ASSEMBLY.						1	G	7	1 	3U				H2SW 					 
1995052600143	19950526	00143	SW 	1995	5	26	HEEA955041 	1	19950519	G	6320	206040004107	TRANSMISSION 			BELL 	206 	206L3 	1182108	SW 										MAST BEARING	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	31073	4374 				51519				MAST BEARING HOUSING LEAKING. (LOWER) REPLACED TRANSMISSION AND RETURNED TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995052600144	19950526	00144	NE 	1995	5	26	HEEA955042 	2	19950519	G	7412	9580113800	HE GENERATOR 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1C 	60030	NE 					ENGINE	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6097Z	451 				2820				HE GENERATOR INOPERATIVE.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995052600145	19950526	00145	EU 	1995	5	26	HEEA955043 	1	19950519	G	6220	704A33633153	LAMINATES STOP 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57908					5091				RUBBER SEPARATION. SERIAL NUMBERS REMOVED PHI995, PHI1251, PHI1213. REPLACED WITH SERVICEABLE MEMBERS.						1	G	7	2 	3U				H11EU 					 
1995052600146	19950526	00146	EU 	1995	5	26	HEEA955044 	1	19950519	G	6220	704A33633152	LAMINATES STOP 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57908					5091				RUBBER SEPARATION. SERIAL NUMBERS REMOVED PHI1025, PHI1496, PHI1290, PHI1410. REPLACED WITH SERVICEABLE MEMBERS.						1	G	7	2 	3U				H11EU 					 
1995052600147	19950526	00147	EU 	1995	5	26	HEEA955045 	1	19950519	G	6330	350A37113120	PIN 			AEROSP	AS355 	AS355F1 	8680810	EU 										XMSN MOUNT	SHOULDERED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57908					5091				CORROSION PITS. REPLACED WITH SERVICEABLE BOLT.						1	G	7	2 	3U				H11EU 					 
1995052600148	19950526	00148	EU 	1995	5	26	HEEA955047 	1	19950519	G	6330	350A38102021	MOUNT 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R XMSN	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	57908					5091				CORROSION PITS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U				H11EU 					 
1995052600149	19950526	00149	EU 	1995	5	26	HEEA955048 	1	19950519	G	6240	10594575	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										ROTOR TORQUE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	9190Y	312 				S669				NO INDICATION.						1	G	7	2 	3U				H3EU 					 
1995052600150	19950526	00150	EU 	1995	5	26	HEEA955049 	1	19950519	G	6240	10594564	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	9190Y	312 				S669				NO INDICATION.						1	G	7	2 	3U				H3EU 					 
1995052600151	19950526	00151	SW 	1995	5	26	HEEA955050 	1	19950519	G	7712	412075008111	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT TORQUE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				#1 NEEDLE CHATTERS AND RATCHETY.						1	G	7	2 	4U				H4SW 					 
1995052600152	19950526	00152	EU 	1995	5	26	HEEA955051 	1	19950519	G	3340	A413A	POWER SUPPLY 			BOLKMS	105 	BO105S 	5626006	EU 										STROBE	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	86CH	364 				S557				POWER SUPPLY INOPERATIVE.						1	G	7	2 	3U				H3EU 					 
1995052600153	19950526	00153	EU 	1995	5	26	HEEA955052 	1	19950519	G	5610	04011340990	WINDOW 			SNIAS 	350 	AS350B2 	8680813	EU 										OUTB LOWER	RAIL CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1066 				2771				OUTBOARD LOWER SLIDE RAIL CRACKED FROM FORWARD END 1/2 LENGTH OF RAIL.						1	G	7	1 	3U				H9EU 					 
1995052600154	19950526	00154		1995	5	26	HEEA955053 	4	19950519	G	2562	ELT10	ELT 	NARCO 		BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	50293					S677				ELT WILL NOT TEST. TIME SINCE REPAIR 64:35.						1	G	7	2 	3U				H3EU 					 
1995052600155	19950526	00155		1995	5	26	HEEA955054 	4	19950519	G	2562	ELT910	ELT 	NARCO 		BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3535T					S113				ELT ACTIVATES WHEN WET. TIME SINCE REPAIR 94:50.						1	G	7	2 	3U				H3EU 					 
1995052600156	19950526	00156	SW 	1995	5	26	HEEA955056 	1	19950519	G	6210	212015501005	BLADE 			BELL 	212 	212 	1181420	SW 										M/R	WT MISSING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5736D	2827 				31135				M/R BLADE INSTALLED AND DURING THE BALANCE CHECK IT WAS DISCOVERED THE BLADE WAS EXTREMELY LIGHT AT THE TIP DUE TO THE A	BSENCE OF THE TIP WEIGHTS. BLADE WAS SENT TO COMPOSITE TECHNICS 4-29-94 FOR TIP WEIGHT STUD STRIPPED OUT. CTI WAS UNAB	LE TO REPLACE THE STUD, SO THE BLADE WAS SHIPPED TO BELL FOR STUD REPAIR. THEN RETURNED TO CTI FOR COMPLETION OF THE REP	AIR TO THE BLADE WITH THE EXCEPTION OF REFINISHING. AT SOME POINT DURING THE REPAIR, THE TIP WEIGHTS WERE REMOVED AND N	EVER REINSTALLED BEFORE THE BLADE WAS RETURNED TO PHI. THIS BLADE WAS THEN PAINTED FORSERVICE. PHI OBTAINED THE ORIGIN	AL WEIGHT HISTORY FROM BELL	1	G	7	1 	4U				H4SW 					 
1995060900149	19950609	00149	GL 	1995	6	9	HEEA955057 	2	19950523	G	7250	23032345	COUPLING 		23035128 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C30P 	03013	GL 					ENG N1	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2135V	683 			CAT97841	45657	CAE895561			ENGINE REMOVED DUE TO TURBINE OVERHAUL AND COMPRESSOR 1750 HOUR INSPECTION. UPON INSPECTION OF TURBINE PARTS NOTED THE 	FOLLOWING: STEP WEAR BEYOND LIMITS ON N1 COUPLING I.D. SPLINES. INSTALLED NEW N1 COUPLING.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995060900150	19950609	00150	SW 	1995	6	9	HEEA955058 	1	19950523	G	5320	205030280127	DECK ASSY 			BELL 	412 	412 	1182202	SW 										LOWER SKIN	UNBONDED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2258F					33073				LOWER SKIN UNBONDED APPROXIMATELY 4" X 6" ON FORWARD END. RECEIVED REPAIRED FROM NORDAM 9-17-93. INSTALLED ON AIRCRAFT	 8-14-94. REPAIRED SERVICE DECK.					1	G	7	2 	4U				H4SW 					 
1995060900151	19950609	00151	SW 	1995	6	9	HEEA955059 	1	19950523	G	7810	230063301101	DUCT 			BELL 	230 	230 	1182149	SW 										EXHAUST	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2073 				23009				EXHAUST DUCT CRACK.						1	G	7	2 	3U			NC	H9SW 					 
1995060900152	19950609	00152	NE 	1995	6	9	HEEA955060 	2	19950523	G	7261	0292005220	ENGINE 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1 	60030	NE 					OIL SYS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1294 				2771				OIL BLOWING OUT EXHAUST AND OIL PSI FELL TO ZERO.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995060900153	19950609	00153	SW 	1995	6	9	HEEA955061 	1	19950523	G	6510	204040623003	BEARING 		212040600005	BELL 	412 	412 	1182202	SW 										T/R DRIVE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N	496 			A2007742	33010				ASB 412-95-84 T/R DRIVE BEARING SHIELD SPINNING.						1	G	7	2 	4U				H4SW 					 
1995060900154	19950609	00154	SW 	1995	6	9	HEEA955062 	1	19950523	G	6510	204040623003	BEARING 		212040600005	BELL 	412 	412 	1182202	SW 										T/R DRIVE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7128R	31 			A2012085	36007				OUTER RADIUS OF BEARING GREATER THAN SHOULD BE. GREASE WILL ENTER BEARING BUT WILL NOT LET IT PURGE OUT. GREASE WILL P	URGE OUT AROUND BEARING AND HOUSING.					1	G	7	2 	4U				H4SW 					 
1995060900155	19950609	00155	SW 	1995	6	9	HEEA955063 	1	19950523	G	6510	204040623003	BEARING 		212040600005	BELL 	412 	412 	1182202	SW 										T/R DRIVE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03					A2007411					REMOVED FROM SERVICE DUE TO BEARING S/N AS PER ASB 412-95-84 --- ASB 212-95-95.						1	G	7	2 	4U				H4SW 					 
1995060900156	19950609	00156	SW 	1995	6	9	HEEA955064 	1	19950523	G	6510	204040623003	BEARING 			BELL 	412 	412 	1182202	SW 										T/R DRIVE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										REMOVED FROM SERVICE DUE TO BEARING S/N AS PER ASB 412-95-84 --- ASB 212-95-95.						1	G	7	2 	4U				H4SW 					 
1995060900157	19950609	00157	SW 	1995	6	9	HEEA955065 	1	19950523	G	6510	204040623003	BEARING 			BELL 	412 	412 	1182202	SW 										T/R DRIVE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										REMOVED FROM SERVICE DUE TO BEARING S/N AS PER ASB 412-95-84 --- ASB 212-95-95.						1	G	7	2 	4U				H4SW 					 
1995060900158	19950609	00158	SW 	1995	6	9	HEEA955066 	1	19950523	G	6230	206010452109	SUPPORT 		206010450113	BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	REQ REPLACEMENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5742H	982 			REJG10726	45476				AS PER ASB 206L-93-89 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995060900159	19950609	00159	SW 	1995	6	9	HEEA955067 	1	19950524	G	6400	222035168101	FITTING ASSY 			BELL 	230 	230 	1182149	SW 										T/R	RIVETS LOOSE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2042 				23009				TAIL ROTOR GUARD FWD FITTING P/N 222-035-168-101 HAS SEVERAL WORKING RIVETS. THE TOP CLIP P/N 222-035-167-117 IS CRACKE	D IN RADIUS. THE DOUBLER P/N 222-035-167-115 IS ALSO CRACKED IN RADIUS. REPAIRED BY PHI.					1	G	7	2 	3U			NC	H9SW 					 
1995060900160	19950609	00160	SW 	1995	6	9	HEEA955068 	1	19950524	G	5320	206033410101	INTERCOSTAL 			BELL 	206 	206L 	1181522	SW 										TAIL BOOM	LOOSE RIVETS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7077F	795 				52038				WORKING RIVETS IN MOUNT FITTINGS.						1	G	7	1 	3U				H2SW 					 
1995060900161	19950609	00161	SW 	1995	6	9	HEEA955069 	1	19950524	G	6420	214011801117	HUB 			BELL 	214 	214ST 	1182106	SW 										T/R	PEELING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M	2561 				28102				PAINT AND NICKEL STRIP PEELING.						2	G	7	2 	4U				H10SW 					 
1995060900162	19950609	00162	GL 	1995	6	9	HEEA955071 	2	19950524	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE BLADES	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	54197	1691 			CAT37782	S805	CAE802035F			ENGINE REMOVED DUE TO TURBINE 1750 HOUR INSPECTION AND BURNT 1ST STAGE NOZZLE. UPON INSPECTION OF TURBINE PARTS NOTED T	HE FOLLOWING: MINOR SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995060900163	19950609	00163	GL 	1995	6	9	HEEA955072 	2	19950524	G	7250	6895801	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					1ST STAGE BLADES	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2758N	1373 			CAT70546	45267	CAE860213			ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION ON ALL 1ST S	TAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995060900164	19950609	00164	SW 	1995	6	9	HEEA955073 	1	19950525	G	6710	206001392001	STICK ASSY 			BELL 	206 	206L1 	1182107	SW 										CO-PILOT CYCLIC	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5000K					45167				CO-PILOT'S QUICK DISONNECT CYCLIC STICK NOT FULLY SEATED IN MOUNT. FOUND LOWER KNURL NUT BINDING ON LEVER ASSEMBLY BEFO	RE STICK FULLY SEATED. APPEARS THREADS IN NUT NOT MFG PROPERLY. STICK ASSEMBLY RECEIVED IN KIT P/N 206-706-127-117.					1	G	7	1 	3U				H2SW 					 
1995060900165	19950609	00165	EU 	1995	6	9	HEEA955074 	1	19950525	G	6210	355A11002011	BLADE 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R	CRACK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5785Y	1322 				5105				CRACK ON THE LOWER SURFACE AT STATION 1835MM. THE CRACK STARTS 20MM FROM THE TRAILING EDGE AND EXTENDS 157MM FROM THE T	RAILING EDGE.					1	G	7	2 	3U				H11EU 					 
1995060900166	19950609	00166	SW 	1995	6	9	HEEA955075 	1	19950525	G	5320	206033201249	PANEL 			BELL 	206 	206L1 	1182107	SW 										ROOF	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2251A					45755				SEVERAL AREAS OF PANEL ALONG AFT EDGE HAVE INSUFFICIENT EDGE DISTANCE TO LOCATE RIVETS. PANEL HAS 4 EACH 1/4" INSERTS O	N L/H AND 4 EACH 1/4" INSERTS ON R/H WING WALK AREA THAT ARE NOT REQUIRED. INSERTS IN CENTER AREA OF PANEL APPEAR TO BE	 3/16" TOO FAR TO THE R/H SIDE OF THE PANEL. IF PANEL IS MOVED LEFT TO COMPENSATE FOR 3/16" DIFFERENCE THE CONTOUR OF T	HE PANEL AND TRANSIITON AREAS DO NOT FIT AIRFRAME.			1	G	7	1 	3U				H2SW 					 
1995060900167	19950609	00167	SW 	1995	6	9	HEEA955076 	1	19950525	G	2841	393008047	INDICATOR 			BELL 	212 	212 	1181420	SW 										COCKPIT FUEL	STUCK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										NEEDLE STUCK AT 2900 LBS.						1	G	7	1 	4U				H4SW 					 
1995060900168	19950609	00168	SW 	1995	6	9	HEEA955077 	1	19950525	G	2841	393008047	INDICATOR 			BELL 	212 	212 	1181420	SW 										COCKPIT FUEL	STUCK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										NEEDLE STUCK AT 2650 LBS.						1	G	7	1 	4U				H4SW 					 
1995060900169	19950609	00169	SW 	1995	6	9	HEEA955078 	1	19950525	G	5210	206033600103	DOOR 			BELL 	206 	206L1 	1182107	SW 										LT FOREWARD	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5007N					45184				FLAT AREA JUST BELOW WINDOW APPROXIMATELY 8" DOWN THE FULL WIDTH OF DOOR.						1	G	7	1 	3U				H2SW 					 
1995060900170	19950609	00170		1995	6	9	HEEA955079 	4	19950525	G	3414	8000	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT AIRSPEED	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2754W					45260				NEEDLE INDICATES 4 KNOTS LOW THROUGHOUT SCALE.						1	G	7	1 	3U				H2SW 					 
1995060900171	19950609	00171		1995	6	9	HEEA955080 	4	19950525	G	3452	066106200	TRANSCEIVER 	KING 	KT76 	BELL 	206 	206B3 	1181506	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268V					3605				THE DIALED IN NUMBERS ARE NOT THE ONES RECEIVED. FOUND EXTRA NUMBERS ON SCOPE WHEN DIALING IN NUMBERS. CLEANED CONTACTS	 ON ALL WAFER SWITCHES. REPAIRED. ADJUSTED POWER OUT AND PULSE WIDTH. REPLACED WEAK PHOTOCELL V301. REPLACED CRACKED	 FACEPLATE. UNIT HAD WEAK RECEIVE. REPLACED MIXER DIODE CR202 AND ALIGNED RECEIVER. REPAIRED. INSTALLED HEATSINK BEH	IND TRANSISTOR Q415 AS PER KING SERVICE BULLETIN KT76A-6. BENCH CHECK GOOD.			1	G	7	1 	3U				H2SW 					 
1995060900172	19950609	00172		1995	6	9	HEEA955081 	4	19950525	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	39122					3312				ATC UNABLE TO READ IDENT. FOUND EXTRA NUMBERS ON SCOPE WHEN DIALING IN NUMBERS. CLEANED CONTACTS ON ALL WAFER SWITCHES.	 REPAIRED. FOUND POWER OUT VERY LOW. REPLACED CAVITY OSCILLATOR V101. REPAIRED. FOUND UNABLE TO SWITCH FROM ON TO 	STANDBY MODE. CLEANED CONTACTS ON ALL WAFERS. REPAIRED. ADJUSTED PULSE WIDTH. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995060900173	19950609	00173	EU 	1995	6	9	HEEA955082 	1	19950525	G	2436	51565000R	REGULATOR 			BOLKMS	105 	BO105S 	5626006	EU 										DC SYS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	617					S578				GENERATOR DOES NOT COME ON LINE. REPLACED R65 RESISTOR P/N 05-508624 ON CIRCUIT BOARD 51565-312R. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995060900174	19950609	00174	EU 	1995	6	9	HEEA955083 	1	19950525	G	2436	51565000R	REGULATOR 			BOLKMS	105 	BO105S 	5626006	EU 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	54197					S805				DELAY IN COMING ON LINE. REPLACED R65 RESISTOR P/N 05-508624 ON CIRCUIT BOARD 51565-312R. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995060900175	19950609	00175		1995	6	9	HEEA955084 	4	19950525	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	2148K	2803 				36001				CVR INOPERATIVE. WILL NOT TEST. TIME SINCE REPAIR 337:45.						1	G	7	2 	4U				H4SW 					 
1995060900176	19950609	00176		1995	6	9	HEEA955085 	4	19950525	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	7128R	3789 				36007				CVR DOES NOT TEST. NO LIGHTS - NO TONE.						1	G	7	2 	4U				H4SW 					 
1995060900177	19950609	00177		1995	6	9	HEEA955086 	4	19950525	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3911L					33023				COURSE SET 3 DEGREES OFF. TIME SINCE REPAIR 203:30.						1	G	7	2 	4U				H4SW 					 
1995060900178	19950609	00178		1995	6	9	HEEA955087 	4	19950525	G	3457	0845000000	SKYNAV 5000 																	COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										FOUND NUMBERS TO SKIP WHEN ENTERING WAYPOINTS. SENT TO MAGELLAN SYSTEMS FOR WARRANTY REPAIR OR EXCHANGE.																			 
1995060900179	19950609	00179	NE 	1995	6	9	HEEA955088 	1	19950525	G	6520	7635705006041	FLANGE 		763570500004	SKRSKY	S76 	S76A 	8143006	NE 										INTERMED GR BOX	WORN SPLINES 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5426U				A07300105	760167				WORN SPLINES. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U				H1NE 					 
1995060900180	19950609	00180	NE 	1995	6	9	HEEA955089 	1	19950525	G	6520	7635705011102	OUTPUT GEAR 		763570500004	SKRSKY	S76 	S76A 	8143006	NE 										INTERMED GR BOX	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5426U	9655 			A07300105	760167				WORN SPLINES. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U				H1NE 					 
1995110200013	19951102	00013	NE 	1995	11	2	HEEA955090 	2	19950525	G	7300	0164248800	FUEL CONTROL 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1D 		NE 					ENGINE	DEFECTIVE 	E			HEEA	A				UNSCHED LANDING 				R			PARTIAL RPM/PWR LOSS 			TO	TAKEOFF 	1			SW	03	6097Z	572 				2820	9353			ROTOR DROOPED ON TAKEOFF ABOVE 80% TORQUE AND SLOW TO RESPOND DURING LET DOWN.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995060900181	19950609	00181	GL 	1995	6	9	HEEA955091 	2	19950525	G	7230	23007208	DIFFUSER VANE 		23033192 						ALLSN 	250C 	250C28C 	03013	GL 					ENGINE	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03					CAC28048		CAE280047			ENGINE REMOVED DUE TO TURBINE OVERHAUL, COMPRESSOR N1 SHAFTING INSPECTION AND UPGRADE CEB'S. UPON INSPECTION OF COMPRES	SOR PARTS NOTED THE FOLLOWING: TURNING VANE APPEARS TO BE SEPARATING FROM FORWARD AND AFT PLATES ON DIFFUSER VANE ASSY 	AND MATING SURFACES ARE DEFLECTED CAUSING LOW POWER DURING TEST CELL RUN.									3	U			E1GL				 
1995060900182	19950609	00182	SW 	1995	6	9	HEEA955092 	1	19950525	G	6230	206010452109	SUPPORT 		206010450113	BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	REQ REPLACEMENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2251A	1120 			JIJG07950	45755				ASB 206L-93-89 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995060900183	19950609	00183	SW 	1995	6	9	HEEA955093 	1	19950525	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										START GEN	BURNT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				HOLE BURNT THROUGH SIDE OF STARTER.						2	G	7	2 	4U				H10SW 					 
1995060900184	19950609	00184	SW 	1995	6	9	HEEA955094 	1	19950525	G	6230	222010400127	SWASHPLATE 			BELL 	230 	230 	1182149	SW 										M/R	BEARING ROUGH 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	3312 				23009				ON BI-ANNUAL INSPECTION FOUND ROUGHNESS IN THE SWASHPLATE DUPLEX BEARING.						1	G	7	2 	3U			NC	H9SW 					 
1995060900185	19950609	00185	SW 	1995	6	9	HEEA955095 	1	19950525	G	2435	200SGL124Q	STARTER 			BELL 	230 	230 	1182149	SW 										START GEN	BRUSH WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	386 				23009				BRUSHES WORN TO ABOUT 1/4						1	G	7	2 	3U			NC	H9SW 					 
1995060900116	19950609	00116	SW 	1995	6	9	HEEA955099 	1	19950529	G	6230	206010452109	SUPPORT 		206010450113	BELL 	206 	206L1 	1182107	SW 										M/R	REQ REPLACEMENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y	4280 			JIJG09785	45751				COMPLY WITH ASB 206L-93-89 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995060900117	19950609	00117	SW 	1995	6	9	HEEA955100 	1	19950529	G	2121	214073917101	BLOWER 			BELL 	214 	214ST 	1182106	SW 										AIR DIST	INOP 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				BLOWER INOPERATIVE.						2	G	7	2 	4U				H10SW 					 
1995060900118	19950609	00118	SW 	1995	6	9	HEEA955101 	1	19950529	G	5330	N206031004125	SKIN 		206031004115	BELL 	206 	206B3 	1181506	SW 										FUSELAGE	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03					BCJN08724					SKIN ROLLED TOO TIGHT TO FIT PROPERLY ON DIAMETER OF BULKHEADS AND FRAMES. AFT END 5 /2" SHOULD BE 7" AND FORWARD END 	11 3/4" SHOULD BE 14 3/4".					1	G	7	1 	3U				H2SW 					 
1995060900119	19950609	00119	SW 	1995	6	9	HEEA955102 	1	19950529	G	6330	214031614128	PLATE ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN MOUNT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				RUBBER TORN. RECEIVED INSTALLED ON AIRCRAFT.						2	G	7	2 	4U				H10SW 					 
1995060900120	19950609	00120	SW 	1995	6	9	HEEA955103 	1	19950529	G	6330	214031614127	PLATE ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN MOUNT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				RUBBER TORN. RECEIVED INSTALLED ON AIRCRAFT.						2	G	7	2 	4U				H10SW 					 
1995060900121	19950609	00121	SW 	1995	6	9	HEEA955104 	1	19950529	G	5260	206033433102	FITTING ASSY 			BELL 	206 	206L 	1181522	SW 										STEP	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										RECEIVED FITTINGS WITH ONE BUSHING, P/N 22H006-16-29-16 AND CLIP SPRING P/N 206-033-421-101 MISSING FROM FITTINGS.						1	G	7	1 	3U				H2SW 					 
1995060900122	19950609	00122	SW 	1995	6	9	HEEA955105 	1	19950529	G	5260	206033433101	FITTING ASSY 			BELL 	206 	206L 	1181522	SW 										STEP	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										RECEIVED FITTINGS WITH ONE BUSHING, P/N 22H006-16-29-16 AND CLIP SPRING P/N 206-033-421-101 MISSING FROM FITTINGS.						1	G	7	1 	3U				H2SW 					 
1995060900123	19950609	00123	SW 	1995	6	9	HEEA955106 	1	19950531	G	6220	214010558101	LINK 			BELL 	214 	214ST 	1182106	SW 										M/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M	3478 				28102				ELASTOMERIC BEARING WORN. RECEIVED INTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995060900124	19950609	00124	SW 	1995	6	9	HEEA955107 	1	19950531	G	6420	214010851103	BEARING ASSY 			BELL 	214 	214ST 	1182106	SW 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				WORN; CAUSING BUZZ IN PEDALS. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995060900125	19950609	00125	SW 	1995	6	9	HEEA955108 	1	19950531	G	6420	214010850101	BEARING ASSY 			BELL 	214 	214ST 	1182106	SW 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				WORN; CAUSING BUZZ IN PEDALS. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995060900126	19950609	00126	SW 	1995	6	9	HEEA955109 	1	19950531	G	3210	214031839101	STRAP ASSY 			BELL 	214 	214ST 	1182106	SW 										MLG	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				WORN RUBBER. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995060900127	19950609	00127	SW 	1995	6	9	HEEA955110 	1	19950531	G	6720	214010825101	BEARING ASSY 			BELL 	214 	214ST 	1182106	SW 										T/R	LEAKS 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	5748M					28102				BEARING ASSY LEAKS. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995060900128	19950609	00128	SW 	1995	6	9	HEEA955111 	1	19950531	G	5340	214031458102	FITTING 			BELL 	214 	214ST 	1182106	SW 										FUSELAGE	HOLES WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				BUSHING HOLES ARE WORN. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995060900129	19950609	00129		1995	6	9	HEEA955112 	4	19950531	G	2312	A21800094202	SWITCH 			BELL 	206 	206L 	1181522	SW 										COCKPIT VHF	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W	1683 				52033				CANNOT TRANSMIT ON RADIOS.						1	G	7	1 	3U				H2SW 					 
1995060900130	19950609	00130	SW 	1995	6	9	HEEA955113 	1	19950531	G	2841	206063633103	INDICATOR 			BELL 	206 	206L 	1181522	SW 										FUEL QTY	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W	1717 				52033				OIL ON GLASS IN INDICATOR.						1	G	7	1 	3U				H2SW 					 
1995060900131	19950609	00131	SW 	1995	6	9	HEEA955114 	1	19950531	G	6320	206033517007	BEARING 			BELL 	206 	206L 	1181522	SW 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7074W	1683 				52033				AIRCRAFT EXPERIENCES A MILD SHUDDER IN CRUUISE FLIGHT. THIS SHUDDER HAS A DURATION OF 2-3 SECONDS AND THERE IS NO PREDI	CTING HOW OFTEN OR WHEN IT WILL OCCUR. THE ROTOR SYSTEM HAS BEEN CHECKED FOR TRACK AND BALANCE.					1	G	7	1 	3U				H2SW 					 
1995060900132	19950609	00132	SW 	1995	6	9	HEEA955115 	1	19950531	G	6320	206033506103	RESTRAINT 			BELL 	206 	206L 	1181522	SW 										TRANSMISSION	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			CR	CRUISE 	1			SW	03	7074W	548 				52033				AIRCRAFT EXPERIENCES A MILD SHUDDER IN CRUISE FLIGHT. THIS SHUDDER HAS A DURATION OF 2-3 SECONDS AND THERE IS NO PREDIC	TING HOW OFTEN OR WHEN IT WILL OCCUR. THE ROTOR SYSTEM HAS BEEN CHECKED FOR TRACK AND BALANCE.					1	G	7	1 	3U				H2SW 					 
1995060900133	19950609	00133	SW 	1995	6	9	HEEA955116 	1	19950531	G	6420	206310105101	BEARING 		206011810013	BELL 	206 	206L1 	1182107	SW 										T/R HUB	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3905B	641 			AFS5604	45598				2 EACH BEARINGS CRACKED; ONE EACH BEARING WORN BEYOND LIMITS AND ONE EACH BEARING ANODIZED COATING WORN OFF.						1	G	7	1 	3U				H2SW 					 
1995060900134	19950609	00134	GL 	1995	6	9	HEEA955117 	2	19950602	G	7250	23032345	COUPLING 		23035128 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					ENG N1	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1546K	826 			CAT90437	760082	CAE890431S			ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS 	ON N1 COUPLING FORWARD I.D. SPLINES. INSTALLED NEW N1 COUPLING.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995060900135	19950609	00135	GL 	1995	6	9	HEEA955118 	2	19950602	G	7250	23055438	NOZZLE 		23035128 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					2ND STAGE	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	2743E				CAT90644	760155	CAE890476S			RECEIVING INSPECTION OF NEW, NEVER INSTALLED 2ND STAGE NOZZLE INDICATES .009" RUNOUT IN BOTH TIP PATHS, DIAPHRAGM OFF C	ENTER. NOTE: DAMAGE TO KEYS AND TANGS BY ADJUSTMENT PRIOR TO RECEIPT BY PHI. INSTALLED NEW 2ND STAGE NOZZLE.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995060900136	19950609	00136	GL 	1995	6	9	HEEA955119 	2	19950602	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81832	1000 			CAT25276	S828	CAE836418			ENGINE REMOVED DUE TO CYCLED OUT 1ST AND 2ND STAGE WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR	 SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995060900137	19950609	00137	GL 	1995	6	9	HEEA955120 	2	19950602	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE	BLADES FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	54191	30 			CAT32744F	S804	CAE836073			ENGINE REMOVED DUE TO ENGINE FAILURE ON RUN-UP. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 100% OF 1ST STAG	E WHEEL BLADE TIPS FAILED .450" OUTBOARD FROM HUB TO BLADE TIP LEADING EDGE DUE TO THERMAL FATIGUE CAUSED BY ENGINE OPER	ATING IN AN OVERTEMPERATURE CONDITION AND 94% OF 2ND STAGE WHEEL BLADE TIPS FAILED .781" OUTBOARD FROM HUB TO BLADE TIP 	LEADING EDGE. SCRAPPED 1ST AND 2ND STAGE WHEELS. SEE MMIR #5121 FOR 2ND STAGE WHEEL INFORMATION.			1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995060900138	19950609	00138	GL 	1995	6	9	HEEA955121 	2	19950602	G	7250	6898782	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					2ND STAGE	BLADES FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	54191	30 			CAT32744F	S804	CAE836073			ENGINE REMOVED DUE TO ENGINE FAILURE ON RUN-UP. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 100% OF 1ST STAG	E WHEEL BLADE TIPS FAILED .450" OUTBOARD FROM HUB TO BLADE TIP LEADING EDGE DUE TO THERMAL FATIGUE CAUSED BY ENGINE OPER	ATING IN AN OVERTEMPERATURE CONDITION AND 94% OF 2ND STAGE WHEEL BLADE TIPS FAILED .781" OUTBOARD FROM HUB TO BLADE TIP 	LEADING EDGE. SCRAPPED 1ST AND 2ND STAGE WHEELS. SEE MMIR #5120 FOR 2ND STAGE WHEEL INFORMATION.			1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995060900139	19950609	00139	EU 	1995	6	9	HEEA955122 	1	19950602	G	7722	TM43553	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										EXHAUST TEMP	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										TERMINAL STUDS POTTED IN INDICATOR INCORRECTLY. SMALL TERMINAL STUD SHOULD BE POSITIVE SIDE AND LARGE STUD ON NEGATIVE 	SIDE.					1	G	7	2 	3U				H3EU 					 
1995060900140	19950609	00140	EU 	1995	6	9	HEEA955123 	1	19950602	G	2435	150SG122Q	GENERATOR 			SNIAS 	350 	AS350B2 	8680813	EU 										START/GEN	NOISY 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	6095S	974 				2777				STARTER GENERATOR HAS RUBBING NOISE AND VIBRATION.						1	G	7	1 	3U				H9EU 					 
1995060900141	19950609	00141	EU 	1995	6	9	HEEA955124 	1	19950602	G	2121	420800001	BLOWER 			SNIAS 	350 	AS350B2 	8680813	EU 										AIR DIST	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	697 				2777				BLOWER INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995060900142	19950609	00142	SW 	1995	6	9	HEEA955125 	1	19950602	G	2430	A1077V	CONTACTOR 			BELL 	230 	230 	1182149	SW 										DC SYS	STICKS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2059 				23009				CONTACTS ON TERMINALS 12 AND 13 STICK IN THE CLOSED POSITION. HELD AT PHI FOR CSR SIGNATURE.						1	G	7	2 	3U			NC	H9SW 					 
1995060900143	19950609	00143	SW 	1995	6	9	HEEA955126 	1	19950602	G	5320	206033201249	PANEL 			BELL 	206 	206L1 	1182107	SW 										ROOF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2251A					45755				FORWARD R/H SIDE OF ROOF PANEL HITTING R/H AIRFRAME PANEL TRANSITION AREA. PANEL NEEDS TO BE MOVED TO THE RIGHT APPROXI	MATELY 1/8" FOR INSERT ALIGNMENT. TRANSITION AREAS ON L/H AND R/H SIDES, FORWARD OF THE FORWARD ROLL OVER BEAM BULKHEAD	S, HITS THE BULKHEAD FROM TO BOX BEAM OUTBOARD APPROXIMATELY 2".				1	G	7	1 	3U				H2SW 					 
1995060900144	19950609	00144	EU 	1995	6	9	HEEA955127 	1	19950602	G	3340	6034745	SUPPLY UNIT 			BOLKMS	117 	BK117B2 	5626013	EU 										ANTI COLL LIGHT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE					7238				ANTI COLLISION LIGHT POWER SUPPLY QUIT WORKING BECAUSE CANNON PLUG RECEPTICAL AT FLASH TUBE SHORTED OUT.						1	G	7	2 	3U			NC	H13EU 					 
1995060900145	19950609	00145	EU 	1995	6	9	HEEA955128 	1	19950602	G	6220	827S115X140X12FP	SHAFT SEAL 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03										SHAFT SEAL STATIC LEAK.						1	G	7	2 	3U				H3EU 					 
1995060900146	19950609	00146	EU 	1995	6	9	HEEA955129 	1	19950602	G	3213	350A41108700	CROSS TUBE 			AEROSP	AS355 	AS355F1 	8680810	EU 										SKID REAR	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5796S					5164				CROSSTUBE BEND RADIUS NOT BENT CORRECTLY WHEN COMPARED TO ANOTHER SERVICEABLE CROSSTUBE. WHEN CROSSTUBE IS ATTACHED TO 	SKIDS, AFT AND FWD CORNERS OF LANDING GEAR DO NOT TOUCH THE GROUND (2 1/2" TO 3 1/2")					1	G	7	2 	3U				H11EU 					 
1995060900147	19950609	00147	EU 	1995	6	9	HEEA955130 	1	19950602	G	3213	350A41108601	CROSS TUBE 			AEROSP	AS355 	AS355F1 	8680810	EU 										SKID FRONT	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5796S					5164				CROSSTUBE BEND RADIUS NOT BENT CORRECTLY WHEN COMPARED TO ANOTHER SERVICEABLE CROSSTUBE. WHEN CROSSTUBE IS ATTACHED TO 	SKIDS, AFT AND FWD CORNERS OF LANDING GEAR DO NOT TOUCH THE GROUND (2 1/2" TO 3 1/2")					1	G	7	2 	3U				H11EU 					 
1995060900148	19950609	00148	SW 	1995	6	9	HEEA955131 	1	19950602	G	6330	206033554101	LINK ASSY 			BELL 	206 	206L 	1181522	SW 										PYLON	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W	1687 				52033				SEPARATED RUBBER ON RIGHT HAND FORWARD PYLON LINK.						1	G	7	1 	3U				H2SW 					 
1995062300671	19950623	00671	SW 	1995	6	23	HEEA955132 	1	19950609	G	3212	222025879101	BRACKET ASSY 			BELL 	230 	230 	1182149	SW 										FLOAT BOTTLE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2099 				23009				RIGHT HAND BRACKET FOR FLOAT BOTTLE CRACKED.						1	G	7	2 	3U			NC	H9SW 					 
1995062300672	19950623	00672	SW 	1995	6	23	HEEA955133 	1	19950609	G	6310	206340104101	SEAL 		206040270003	BELL 	206 	206B3 	1181506	SW 										FREEWHEEL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2145C	1412 			BMB00086	3456				AFT SEAL LEAKING. RECEIVED FROM BELL ON A FIELD EVALUATION BASIS ON 10-20-92.						1	G	7	1 	3U				H2SW 					 
1995062300673	19950623	00673	SW 	1995	6	23	HEEA955134 	1	19950609	G	6310	206340105101	SEAL 		206040270003	BELL 	206 	206B3 	1181506	SW 										FREEWHEEL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2145C	1412 			BMB00086	3456				FWD SEAL LEAKING. RECEIVED FROM BELL ON A FIELD EVALUATION BASIS ON 10-20-92.						1	G	7	1 	3U				H2SW 					 
1995062300674	19950623	00674	SW 	1995	6	23	HEEA955135 	1	19950609	G	6330	214031614107	PLATE ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN MOUNT	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				PLATE ASSY WORN AND WEAK. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995062300675	19950623	00675	SW 	1995	6	23	HEEA955136 	1	19950609	G	6330	214031614108	PLATE ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN MOUNT	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M					28102				PLATE ASSY WORN AND WEAK. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995062300676	19950623	00676	SW 	1995	6	23	HEEA955137 	1	19950609	G	6330	214031615106	CLEVIS ARM 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN	DEFECTIVE 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5748M					28102				MAIN ROTOR VIBRATIONS. CLEVIS ARM ASSY RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995062300677	19950623	00677	SW 	1995	6	23	HEEA955138 	1	19950609	G	6330	214031614105	ARM ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN MOUNT	DEFECTIVE 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5748M					28102				MAIN ROTOR VIBRATIONS. ARM ASSY RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94. SENT TO BELL HELICOPTER TEXTRON FOR WARRANT	Y CREDIT AGAINST REPLACEMENT PART PURCHASED.					2	G	7	2 	4U				H10SW 					 
1995062300678	19950623	00678	SW 	1995	6	23	HEEA955139 	1	19950609	G	6330	214031614125	TORSION ARM 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN MOUNT	DEFECTIVE 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5748M					28102				MAIN ROTOR VIBRATIONS. TORSION ARM ASSY RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94. SENT TO BELL HELICOPTER TEXTRON FOR	 WARRANTY CREDIT AGAINST REPLACEMENT PART PURCHASED.					2	G	7	2 	4U				H10SW 					 
1995062300679	19950623	00679	SW 	1995	6	23	HEEA955140 	1	19950609	G	6330	214031615105	CLEVIS ARM 			BELL 	214 	214ST 	1182106	SW 										M/R XMSN	DEFECTIVE 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5748M					28102				MAIN ROTOR VIBRATIONS. CLEVIS ARM ASSY RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995062300605	19950623	00605	SW 	1995	6	23	HEEA955141 	1	19950612	G	6220	206011147007	STRAP 		206011100159	BELL 	206 	206L3 	1182108	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8593X	6 			A1989	51509				UNABLE TO TRACK AND BALANCE ON AIRCRAFTS. (THREE EACH DIFFERENT A/C - N6610C, N5742H, AND N8593X. SERIAL NUMBERS REMOVE	D ARE BT16714 AND BT16728.					1	G	7	1 	3U				H2SW 					 
1995062300606	19950623	00606	SW 	1995	6	23	HEEA955142 	1	19950612	G	6230	206010452109	SUPPORT 		206010450113	BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2775A	2023 			REJG20023	45297				AS PER ASB 206L-93-89 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995062300607	19950623	00607	SW 	1995	6	23	HEEA955143 	1	19950612	G	6230	206010452109	SUPPORT 		206010450113	BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5737T	2595 			JIJG09771	45454				AS PER ASB 206L-93-89 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995062300608	19950623	00608	SW 	1995	6	23	HEEA955144 	1	19950612	G	6230	206010452109	SUPPORT 		206010450113	BELL 	206 	206B 	1181511	SW 										SWASHPLATE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2275Q	3119 			GDJG10479	3625				AS PER ASB 206-73-74 REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995062300609	19950623	00609		1995	6	23	HEEA955145 	4	19950612	G	3416	066030640001	ENCODER 			BELL 														COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2052 				23009				ENCODER JUMPS FROM 10K READING BACK TO 9K (ENCODER IS BAD)																			 
1995062300610	19950623	00610		1995	6	23	HEEA955146 	4	19950613	G	2312	4000103000	TRANSCEIVER 		RT45 	BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911NC					7026				OCCASIONALLY CUTTING OUT ON TRANSMIT. MIKE AUDIO IS INTERMITTENT. REPLACED BAD CR2 AND CR3 DIODES. REPAIRED.						1	G	7	2 	3U				H13EU 					 
1995062300611	19950623	00611	SW 	1995	6	23	HEEA955147 	1	19950613	G	2436	206075447007	VOLT REGULATOR 			BELL 	206 	206L1 	1182107	SW 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5000K					45167				GENERATOR WOULD NOT COME ON LINE. REPLACED CR8 DIODE P/N 3056 ON CIRCUIT BOARD A1. BENCH CHECK GOOD.						1	G	7	1 	3U				H2SW 					 
1995062300612	19950623	00612		1995	6	23	HEEA955148 	4	19950613	G	3452	066106200	TRANPONDER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5742N					45477				TOP BROKEN. REPLACED BROKEN SWITCH BOARD ASSY AND BROKEN FACEPLATE. INSTALLED MISSING IDENT PUSH BUTTON. UNIT HAD WEAK	 POWER OUT. REPLACED CAVITY TUBE V101. REPAIRED. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. FOUND UNIT TO HAVE	 WEAK RECEIVE. ALIGNED RECEIVER. REPAIRED AND BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995062300613	19950623	00613		1995	6	23	HEEA955149 	4	19950613	G	3452	071119208	CONTROL UNIT 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21498					36003				FUNCTION SWITCH HAS NO STOPS. REPLACED BROKEN SWITCH CONTACT ASSY DUE TO STOPS BROKEN OFF. ALSO REPLACED DEFECTIVE TRAN	SFER SWITCH S103 AND I306 INTERGRATED CIRCUIT DUE TO STB AND ALT WOULD NOT LIGHT ON DISPLAY. REPAIRED.					1	G	7	2 	4U				H4SW 					 
1995062300614	19950623	00614	SW 	1995	6	23	HEEA955150 	1	19950613	G	5321	206033099181	PANEL ASSY 			BELL 	206 	206L1 	1182107	SW 										FS 154	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5007N					45184				PANEL DOES NOT HAVE CORRECT CONTOUR ALONG LEFT HAND SIDE, AFT EDGE, WHERE IT ATTACHES ALONG L/H SIDE OF FORWARD BAGGAGE	 COMPARTMENT WALL. CUT 2 EACH DIAGONAL SLITS, 1/4" SIDE IN L/H INNER SKIN OF PANEL. SLITS RUN FROM WL30.25/F STA. 154.2	5 TO WL 49.25/F STA. 143.00 (WATER LINES AND FUSELAGE STATIONS APPROXIMATE) FILLED SLITS AND BONDED WITH MAGNOLIA 6398 	ADHESIVE. CURED AND SANDED SMOOTH. OVERLAYED WITH 2 LAYERS FIBERGLASS CLOTH USING MAGNOLIA 6367 RESIN. CURED AND SAND	ED SMOOTH AND PRIMED.		1	G	7	1 	3U				H2SW 					 
1995062300615	19950623	00615	SW 	1995	6	23	HEEA955151 	1	19950613	G	3210	206323001	CROSSTUBE 			BELL 	206 	206L3 	1182108	SW 										SKIDS	PAD SLIPPING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6160Z					51610				PADS SLIPPING. ASB NO. 94046 WAS COMPLIED WITH 1-13-95 BY PHI SHEETMETAL SHOP.						1	G	7	1 	3U				H2SW 					 
1995062300616	19950623	00616	NE 	1995	6	23	HEEA955152 	2	19950613	G	7260	3036526	SEAL 		3017470 	BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					ACCESSORY GR BOX	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	2298Z					33077				ON POST-FLIGHT INSPECTION, FOUND EXCESSIVE OIL LEAKING FROM NR 2 ENGINE EJECTOR ACCESSORY GEARBOX VENT FITTING. REMOVED	 HOSE AT NR 2 ENGINE ACCESSORY GEARBOX VENT AND VERIFIED LEAK AT VENT. SCRAPPED SEAL AND REPLACED WITH SERVICEABLE SEAL	.				1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995062300617	19950623	00617	EU 	1995	6	23	HEEA955153 	1	19950613	G	6310	4638202007	CLUTCH 		4638001001 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	CAGE WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	967MB	315 			965	S737				INNER CAGE WORN BEYOND LIMITS. REPLACED WITH SERVICEABLE CLUTCH.						1	G	7	2 	3U				H3EU 					 
1995062300618	19950623	00618	EU 	1995	6	23	HEEA955154 	1	19950613	G	3340	30050423	LIGHT 			BOLKMS	117 	BK117B2 	5626013	EU 										ANTI COLL LIGHT	WIRE BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	978 				7238				WIRE BROKEN AT FLASH TUBE. REPLACED WITH SERVICEABLE LIGHT ASSY.						1	G	7	2 	3U			NC	H13EU 					 
1995062300619	19950623	00619		1995	6	23	HEEA955155 	4	19950613	G	3452	066106200	TRANSPONDER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	03	2249Z					45753				WILL NOT TEST; DOES NOT APPEAR TO HAVE POWER. UNIT WON'T TURN ON. REPLACED SWITCH BOARD ASSY. REPAIRED. UNIT WON'T TR	ANSMIT. REPAIRED BROKEN FOIL ON HIGH VOLTAGE POWER SUPPLY. REPAIRED. REPLY LIGHT TOO DIM. REPLACED V301 PHOTOCELL. R	EPAIRED.				1	G	7	1 	3U				H2SW 					 
1995062300620	19950623	00620		1995	6	23	HEEA955156 	4	19950613	G	2312	4000106010	CONTROL UNIT 		C10 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	90752					S156				FACE PLATE HAS LOOSE SCREWS. TIGHTENED LOOSE SCREWS AND REPLACED THREE EACH MISSING SCREWS ON FACEPLATE. "TEST" SWITCH 	INTERMITTENT. REPLACED S6 SWITCH. REPAIRED.					1	G	7	2 	3U				H3EU 					 
1995062300621	19950623	00621		1995	6	23	HEEA955157 	4	19950613	G	2312	4000106010	CONTROL UNIT 		C10 	BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911LK					7168				THUMBWHEEL LIGHTS POSITIONS 4 AND 6 ARE INOPERATIVE. REPLACED S1 THUMBWHEEL. REPAIRED. REPLACED 5 EACH DETERIORATED SW	ITCH BOOTS. REPAIRED.					1	G	7	2 	3U			NC	H13EU 					 
1995062300622	19950623	00622		1995	6	23	HEEA955158 	4	19950613	G	2210	7683431	POTIENTIOMETER 	HAMSTD 																AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										POTIENTIOMETER CAUSES VOLTAGE FROM J1-B OR J1-E TO GROUND ON BOTH EXTEND AND RETRACT POSITIONS OF ACTUATOR TO BE TOO LOW	 AND OUT OF LIMTS. SENT TO HAMILTON STANDARD FOR WARRANTY EXCHANGE.																		 
1995062300623	19950623	00623	NE 	1995	6	23	HEEA955159 	1	19950613	G	5320	7620303001054	PANEL 			SKRSKY	S76 	S76A 	8143006	NE 										ROOF	MIS REPAIRED 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										TRANSITION AREA TOO TIGHT ON 2ND, 3RD, AND 4TH BULKHEAD AREA. TIME SINCE REPAIR -0-.						1	G	7	2 	3U				H1NE 					 
1995062300624	19950623	00624	EU 	1995	6	23	HEEA955161 	1	19950613	G	6520	350A33020005	GEAR BOX 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1339 				2771				GEAR BOX MAKING METAL.						1	G	7	1 	3U				H9EU 					 
1995062300625	19950623	00625	EU 	1995	6	23	HEEA955162 	1	19950613	G	6320	704A33651157	BEARING 		350A37000402	SNIAS 	350 	AS350B2 	8680813	EU 										TRANSMISSION	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	478 			M452	2771				BEARING SLINGING GREASE. REPLACED WITH NEW BEARING						1	G	7	1 	3U				H9EU 					 
1995062300626	19950623	00626	EU 	1995	6	23	HEEA955163 	1	19950613	G	2820	209072433105	VALVE 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL SYS	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	9190Y					S669				INTERMITTENTLY INOPERATIVE. INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND SOLENOID OPERATES, BUT THE VALVE STICKS AFTE	R VALVE WARMS UP.					1	G	7	2 	3U				H3EU 					 
1995062300627	19950623	00627	SW 	1995	6	23	HEEA955164 	1	19950613	G	5210	206033600103	DOOR 			BELL 	206 	206L1 	1182107	SW 										LT FORWARD	WONT FIT 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5007N					45184				DOOR DOES NOT FIT CONTOUR OF AIRCRAFT.						1	G	7	1 	3U				H2SW 					 
1995062300628	19950623	00628	NE 	1995	6	23	HEEA955165 	1	19950613	G	6220	7610608000048	DAMPER 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	31219					760230				M/R DAMPER HAS WEAR GROOVE ON INNER CYLINDER WALL.						1	G	7	2 	3U				H1NE 					 
1995062300629	19950623	00629	NE 	1995	6	23	HEEA955166 	1	19950613	G	6220	7610608000048	DAMPER 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122G					760232				M/R DAMPER HAS WEAR GROOVE ON INNER CYLINDER WALL.						1	G	7	2 	3U				H1NE 					 
1995062300630	19950623	00630	NE 	1995	6	23	HEEA955167 	1	19950613	G	6220	7610608000045	DAMPER 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122G					760232				METAL PARTICLES IN FLUID AND CYLINDER, ALSO VALVE ASSY PLUG TANGS WORN OFF.						1	G	7	2 	3U				H1NE 					 
1995062300631	19950623	00631	NE 	1995	6	23	HEEA955168 	1	19950613	G	6220	7610608000044	DAMPER 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22342					760096				METAL FOUND IN CYLINDER AND VALVE ASSY PLUG TANGS WORN OFF.						1	G	7	2 	3U				H1NE 					 
1995062300632	19950623	00632	SW 	1995	6	23	HEEA955170 	1	19950613	G	6710	212076005103	SERVO 			BELL 	412 	412 	1182202	SW 										CYCLIC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				CYCLIC HARD TO MOVE TO RH POSITION.						1	G	7	2 	4U				H4SW 					 
1995062300633	19950623	00633	NE 	1995	6	23	HEEA955171 	1	19950613	G	7810	7630507003044	EJECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										EXHAUST	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545X					760050				EJECTORS CRACKED IN SEVERAL PLACES.						1	G	7	2 	3U				H1NE 					 
1995062300634	19950623	00634	EU 	1995	6	23	HEEA955172 	1	19950613	G	6240	117945641	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										MAST MOMENT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC					7152				INDICATOR WILL NOT CALIBRATE AND NEEDLE DROPS TO ZERO.						1	G	7	2 	3U				H13EU 					 
1995062300635	19950623	00635	EU 	1995	6	23	HEEA955173 	1	19950613	G	7712	10594575	TRANSMITTER 			BOLKMS	117 	BK117B1 	5626012	EU 										ENG TORQUE	WONT CALIB 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC					7152				TRANSMITTER WILL NOT CALIBRATE AND NEEDLE DROPS TO ZERO.						1	G	7	2 	3U				H13EU 					 
1995062300636	19950623	00636		1995	6	23	HEEA955174 	4	19950613	G	3444	7001840913	TRANSCEIVER 			BELL 	412 	412 	1182202	SW 										RADIO ALT	FAILED TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	22608	870 				33075				FAILED OUTPUT TEST 5.2 ON SST.						1	G	7	2 	4U				H4SW 					 
1995062300637	19950623	00637	SW 	1995	6	23	HEEA955175 	1	19950613	G	7810	212061201011	EJECTOR ASSY 			BELL 	412 	412 	1182202	SW 										LT EXH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2149S					36002				RIVETS MISSING FROM SEAMS, EJECTOR SUPPORT CRACKED IN WELD AREA. INNER PORTION OF EJECTOR SOCKLED. SENT TO ALPINE AEROT	ECH LTD. FOR INSPECTION AND REPAIR.					1	G	7	2 	4U				H4SW 					 
1995062300638	19950623	00638		1995	6	23	HEEA955176 	4	19950613	G	3444	066104800	ALTIMETER 		KRA405 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT RAD ALT	ERROR 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22342					760096				150 FEET INDICATION ERROR. UNIT INOPERATIVE. REPLACED C102 CAPACITOR ON POWER SUPPLY. REPAIRED. UNIT HAS NO SELF TEST	. REPLACED DS401 BULB ON CAL-LOOP BOARD. REPAIRED. ALIGNED TO SPECS. BENCH CHECK GOOD.					1	G	7	2 	3U				H1NE 					 
1995062300639	19950623	00639	NE 	1995	6	23	HEEA955177 	1	19950613	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5435V					760158				TWO CRACKS IN THE ABRASION STRIP AND SEPARATION. THE FIBERGLASS BETWEEN THE INNER AND OUTER DOUBLER ON THE UPPER SURFAC	E IS CRACKED.					1	G	7	2 	3U				H1NE 					 
1995062300640	19950623	00640	EU 	1995	6	23	HEEA955178 	1	19950613	G	6720	11731822	PITCH LINK ASSY 			BOLKMS	117 	BK117B2 	5626013	EU 										T/R	BEARINGS WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	940 				7238				T/R P/C LINKS BEARINGS WORN. REPLACED WITH SERVICEABLE T/R P/C LINKS AND RETURNED AIRCRAFT TO SERVICE.						1	G	7	2 	3U			NC	H13EU 					 
1995062300641	19950623	00641	NE 	1995	6	23	HEEA955179 	2	19950613	G	7321	25491281	FUEL CONTROL 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC	2405 				7152				ENGINE HOT STARTS. REPLACED WITH SERVICEABLE FUEL CONTROL AND RETURNED AIRCRAFT TO SERVICE.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995062300642	19950623	00642	EU 	1995	6	23	HEEA955180 	1	19950613	G	7714	1179405303	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										TRIPLE TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911NC	120 				7026				#1 NEEDLE READ 4% LOW AFTER 10 MINUTES OPERATION.						1	G	7	2 	3U				H13EU 					 
1995062300643	19950623	00643	SW 	1995	6	23	HEEA955181 	1	19950613	G	2823	206063640103	VALVE 			BELL 	206 	206L1 	1182107	SW 										FUEL SYS	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	5748Q					45499				FUEL VALVE LEAKING FUEL AT ROTATING SHAFT OF OPEN AND CLOSE SECTION OF VALVE. REPLACED WITH SERVICEABLE VALVE.						1	G	7	1 	3U				H2SW 					 
1995062300644	19950623	00644	EU 	1995	6	23	HEEA955182 	1	19950613	G	3243	01005101	MASTER CYLINDER 			BOLKMS	105 	BO105S 	5626006	EU 										BRAKES	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4302G					S853				MASTER CYLINDER WILL NOT DEVELOP ANY PRESSURE. POSSIBLE INTERNAL LEAKAGE. REPLACED WITH SERVICEABLE MASTER CYLINDER.						1	G	7	2 	3U				H3EU 					 
1995062300645	19950623	00645	EU 	1995	6	23	HEEA955183 	1	19950613	G	3242	AHA1121M0D1234	BRAKE HEAD ASSY 			BOLKMS	105 	BO105S 	5626006	EU 										PUCKS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4302G					S853				BRAKE PUCKS ARE WORN. ALSO POSSIBLE INTERNAL RESTRICTION. UNABLE TO GET PROPER FLUID FLOW FROM BLEED PORT IN ORDER TO 	BLEED SYSTEM. REPLACED WITH SERVICEABLE CALIPER ASSY.					1	G	7	2 	3U				H3EU 					 
1995062300646	19950623	00646	EU 	1995	6	23	HEEA955184 	1	19950613	G	6330	5952022752	RING WASHER 			BOLKMS	105 	BO105S 	5626006	EU 										TRANSMISSION MT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	624MB					S751				CLAW OVERLAPS AND DOESN'T SIT FLUSH IN TRANSMISSION MOUNT PAD. UNABLE TO GET BEARING IN CLAW.						1	G	7	2 	3U				H3EU 					 
1995062300647	19950623	00647		1995	6	23	HEEA955185 	4	19950613	G	2312	4000106010	CONTROL UNIT 		C10 	BELL 	206 	206L1 	1182107	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	27766					45312				100MHZ THUMBWHEEL INTERMITTENT. REPLACED S1 THUMBWHEEL. REPAIRED.						1	G	7	1 	3U				H2SW 					 
1995062300648	19950623	00648	SW 	1995	6	23	HEEA955186 	1	19950613	G	3242	94501031	BRAKE ASSY 			BELL 	214 	214ST 	1182106	SW 										CALIPER	WRONG PART 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5748M					28102				P/N 9450103-1 CALIPER NOT APPROVED FOR USE ON 214ST'S. RECEIVED INSTALLED ON AIRCRAFT ON 12-26-94.						2	G	7	2 	4U				H10SW 					 
1995062300649	19950623	00649	SW 	1995	6	23	HEEA955187 	1	19950613	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27766	2869 				45312				SEVERAL AREAS OF INNER GRANULAR CORROSION ON THE LEADING EDGE SPAR. BLADE HELD IN BLADE SHOP						1	G	7	1 	3U				H2SW 					 
1995062300650	19950623	00650		1995	6	23	HEEA955188 	4	19950613	G	3416	214175278101	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N	600 				28106				ENCODER HAS AN ERRATIC OUTPUT AT LOW ALTITUDE.						2	G	7	2 	4U				H10SW 					 
1995062300651	19950623	00651	EU 	1995	6	23	HEEA955189 	1	19950613	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	721MB	6417 				S752				NOSE AND NECK SHELL CRACKED.						1	G	7	2 	3U				H3EU 					 
1995062300652	19950623	00652	EU 	1995	6	23	HEEA955190 	1	19950613	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	721MB	6417 				S752				NOSE AND NECK SHELL CRACKED.						1	G	7	2 	3U				H3EU 					 
1995062300653	19950623	00653	GL 	1995	6	23	HEEA955191 	2	19950615	G	7250	6895801	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50182	951 			CAT70556	45242	CAE860771			ENGINE REMOVED DUE TO LOW POWER. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SEVERLY SULFIDATED BLADE TIP ON	 #1 WHEEL CAUSING WHEEL AND NOZZLE CONTACT WITH TRAILING EDGE TIPS OF 8 EACH BLADES MISSING. SCRAPPED #1 WHEEL.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995062300654	19950623	00654		1995	6	23	HEEA955192 	4	19950615	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5737T					45454				PILOT REPORTS INTERMITTENT OPERATION. FOUND POWER OUT TO BE 100 WATTS BELOW SPECS. ADJUSTED POWER OUT TO SPECS. REPAI	RED. ADJUSTED FREQUENCY AND PULSE WIDTH. REPLACED DETERIORATED RESISTOR R477. REPLACED PHOTOCELL V301 DUE TO WEAK REP	LY LIGHT. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995062300655	19950623	00655		1995	6	23	HEEA955193 	4	19950615	G	3444	066304400	ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				DH LIGHT REVERSED. WHEN NEEDLE IS ABOVE BUG. LIGHT IS ON. FOUND DH LIGHT TO BE TOO DIM. REPLACED V101 PHOTOCELL. REPA	IRED.					1	G	7	2 	4U				H4SW 					 
1995062300656	19950623	00656		1995	6	23	HEEA955194 	4	19950615	G	2312	064105430	TRANSCEIVER 			BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6160Z					51610				TAKES AWHILE FOR DISPLAY TO COME ON AND A LOT OF BACKGROUND NOISE WHEN TRANSMITTING. VERIFIED DISPLAY HAD MISSING SEGMEN	TS. REPLACED DISPLAY DS901 P/N 037-5060-01. REPAIRED PROBLEM. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995062300657	19950623	00657	NE 	1995	6	23	HEEA955195 	1	19950615	G	6410	7610105101041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1547D	9099 				760077				PADDLE "A" OF THIS ASSEMBLY HAS A HOLE IN THE LEADING EDGE WITH SEVERAL CRACKS AROUND THE HOLE.						1	G	7	2 	3U				H1NE 					 
1995062300658	19950623	00658	NE 	1995	6	23	HEEA955196 	1	19950615	G	6210	7615009000049A	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1547D	11745				760077				SKIN SEPARATION ON THE UPPER SURFACE NEAR THE TIP. THE SEPARATION IS NEARLY 32 INCHES SPANWISE BY 3 TO 4 INCH CHORDWISE	. BLADE IS ALSO UP FOR TIME EXTENSION.					1	G	7	2 	3U				H1NE 					 
1995062300659	19950623	00659	SW 	1995	6	23	HEEA955197 	1	19950615	G	5260	FYLM735023	MOTOR ASSY 		SYLC502281 	BELL 	412 	412 	1182202	SW 										STEP	INOP 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2298Z				92794	33077				MOTOR INOPERATIVE. INSPECTED BY ACCESSORY SHOP AND FOUND MOTOR ARMATURE HAS A DEAD SPOT AND INTERMITTENT OPERATION.						1	G	7	2 	4U				H4SW 					 
1995062300660	19950623	00660		1995	6	23	HEEA955198 	4	19950615	G	3416	066304400	ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				RADAR ALTIMETER SPINS INTERMITTENTLY.						1	G	7	2 	4U				H4SW 					 
1995062300661	19950623	00661	EU 	1995	6	23	HEEA955199 	1	19950615	G	3340	356H2801	LIGHT 			SNIAS 	350 	AS350B2 	8680813	EU 										ANTI COLL	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6097Z	437 				2820				ANTI COLLISION LIGHT INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995062300662	19950623	00662		1995	6	23	HEEA955200 	4	19950615	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	6559Z	3113 				36019				CVR WILL NOT TEST PROPERLY.						1	G	7	2 	4U				H4SW 					 
1995062300663	19950623	00663		1995	6	23	HEEA955201 	4	19950615	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31217	3652 				760229				CVR INOPERATIVE. TIME SINCE REPAIR 974:30.						1	G	7	2 	3U				H1NE 					 
1995062300664	19950623	00664		1995	6	23	HEEA955203 	4	19950615	G	3413	RC30VIL	INDICATOR 			BELL 	412 	412 	1182202	SW 										RATE OF CLIMB	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				NEEDLE WILL NOT RETURN TO ZERO ALSO INTERMITTENTLY STICKS.						1	G	7	2 	4U				H4SW 					 
1995062300665	19950623	00665		1995	6	23	HEEA955204 	4	19950615	G	3451	066106901	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				WON'T SHUT OFF. FOUND UNIT NEEDED HEADER MOD. PERFORMED HEADER MODIFICATION AND APPLIED HUMISEAL BETWEEN HEADER AND P/C	 BOARD. BENCH CHECK GOOD.					2	G	7	2 	4U				H10SW 					 
1995062300666	19950623	00666		1995	6	23	HEEA955205 	4	19950615	G	3451	066106901	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				SEGMENTS WEAK. REPLACED WEAK DS901 DISPLAY AND WEAK V901 PHOTOCELL. BENCH CHECK GOOD.						2	G	7	2 	4U				H10SW 					 
1995062300667	19950623	00667		1995	6	23	HEEA955207 	4	19950616	G	3414	8000	INDICATOR 			BELL 	206 	206B3 	1181506	SW 										COCKPIT A/S	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268W					3606				NEEDLE INDICATES 5 KNOTS LOW REPORTED NEED FLUCTUATES. TIME SINCE REPAIR 51:50.						1	G	7	1 	3U				H2SW 					 
1995062300668	19950623	00668		1995	6	23	HEEA955208 	4	19950616	G	3454	071143100	ANTENNA 		KA83 	BELL 	206 	206L3 	1182108	SW 										VOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8592X					51508				LOSES SIGNAL INTERMITTENTLY.						1	G	7	1 	3U				H2SW 					 
1995062300669	19950623	00669		1995	6	23	HEEA955209 	4	19950616	G	3453	066402600	LORAN 		KLN88 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	WEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7136H					S833				LORAN SIGNAL WEAK.						1	G	7	2 	3U				H3EU 					 
1995062300670	19950623	00670		1995	6	23	HEEA955210 	4	19950616	G	3453	066402600	LORAN 		KLN88 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4302G					S853				LORAN WOULDN'T POWER UP.						1	G	7	2 	3U				H3EU 					 
1995063000136	19950630	00136	EU 	1995	6	30	HEEA955211 	1	19950622	G	6210	355A11002011	BLADE 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	1090 				2653				M/R BLADE CRACKED AT STATION 1810.						1	G	7	1 	3U				H9EU 					 
1995063000137	19950630	00137	SW 	1995	6	30	HEEA955212 	1	19950622	G	2434	A1077V	CONTACTOR 			BELL 	230 	230 	1182149	SW 										NR 1 GEN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2099 				23009				#1 GENERATOR WILL NOT COME ON LINE.						1	G	7	2 	3U			NC	H9SW 					 
1995063000138	19950630	00138	SW 	1995	6	30	HEEA955213 	1	19950622	G	6310	214040841101	SEAL 			BELL 	206 	206L 	1181522	SW 										FREEWHEEL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	7077F	828 				52038				SEAL LEAKING ON AFT CAP OF FREEWHEELING UNIT. SEAL SCRAPPED LOCALLY.						1	G	7	1 	3U				H2SW 					 
1995063000139	19950630	00139	SW 	1995	6	30	HEEA955214 	1	19950622	G	6230	206010452109	SUPPORT 		206010452109	BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27766	3520 			RIJG10021	45312				PER ASB 206L-93-89N REV. B (REPLACEMENT OF -109 SUPPORT WITH -113 SUPPORT)						1	G	7	1 	3U				H2SW 					 
1995063000140	19950630	00140	EU 	1995	6	30	HEEA955215 	1	19950622	G	2841	VT044	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL QTY	SHORTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	721MB					S752				INTERNAL SHORT MAKES GAUGE READ BACKWARDS.						1	G	7	2 	3U				H3EU 					 
1995063000141	19950630	00141	SW 	1995	6	30	HEEA955216 	1	19950622	G	6720	222312702101	PITCH LINK 			BELL 	230 	230 	1182149	SW 										T/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	270 				23009				PITCH LINK BEARINGS WORN.						1	G	7	2 	3U			NC	H9SW 					 
1995063000142	19950630	00142	SW 	1995	6	30	HEEA955217 	1	19950622	G	6720	222312702101	PITCH LINK 			BELL 	230 	230 	1182149	SW 										T/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	270 				23009				PITCH LINK BEARINGS WORN.						1	G	7	2 	3U			NC	H9SW 					 
1995063000143	19950630	00143	SW 	1995	6	30	HEEA955218 	1	19950622	G	2436	222375060115	REGULATOR 			BELL 	230 	230 	1182149	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2144 				23009				GENERATOR LIGHT STAYS ON WITH GENERATOR ON LINE.						1	G	7	2 	3U			NC	H9SW 					 
1995063000144	19950630	00144	SW 	1995	6	30	HEEA955219 	1	19950622	G	2460	1101461	RELAY 			BELL 	230 	230 	1182149	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2144 				23009				CAUSES INTERMITTENT BUSS RELAY TO REMAIN ON WITH BOTH GENERATORS ON LINE.						1	G	7	2 	3U			NC	H9SW 					 
1995063000145	19950630	00145	SW 	1995	6	30	HEEA955220 	1	19950623	G	6420	214011801117	HUB 			BELL 	214 	214ST 	1182106	SW 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M	2803 				28102				TRUNNION BEARING ROUGH. INBOARD BLADE BEARING'S LINER BEING CRACKED.						2	G	7	2 	4U				H10SW 					 
1995063000146	19950630	00146	EU 	1995	6	30	HEEA955221 	1	19950623	G	2430	1059084701	CIRCUIT BOARD 			BOLKMS	105 	BO105S 	5626006	EU 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3071K					S859				FOUND SEVERAL OPEN OR SHORTED DIODES.						1	G	7	2 	3U				H3EU 					 
1995072800235	19950728	00235	GL 	1995	7	28	HEEA955222 	2	19950626	G	7250	6895801	WHEEL 		23031899 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5745S	1494 			CAT70036	45491	CAE860022			ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON ALL	 BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995072800236	19950728	00236	GL 	1995	7	28	HEEA955223 	2	19950626	G	7250	23032280	WHEEL 		23035128 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					2ND STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545K	1685 			CAT95464	760047	CAE890643			ENGINE DISASSEMBLED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION O	N OUTER TIP PATH AREAS OF ALL BLADES. SCRAPPED 2ND STAGE WHEEL.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995072800237	19950728	00237	GL 	1995	7	28	HEEA955224 	2	19950626	G	7250	6898911	WHEEL 		23035128 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545K	1685 			CAT95464	760047	CAE890643			ENGINE DISASSEMBLED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION O	N ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995072800238	19950728	00238		1995	7	28	HEEA955225 	4	19950626	G	2312	064102300	TRANSCEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				SQUELCH INOPERATIVE. STAYS ON. ALIGNED UNIT SEVERAL TIMES. REPLACED TRANSISTOR Q318. REPLACED RECEIVER BOARD. REPAIR	ED PROBLEM. ADJUSTED SQUELCH AND MODULATION. BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995072800239	19950728	00239		1995	7	28	HEEA955226 	4	19950626	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31077					51520				TRANSPONDER INOPERATIVE. REPLACED DETERIORATED RESISTOR R477. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. FOUND S	LS TO BE OUT OF SPECIFICATIONS. ALIGNED RECEIVER. REPAIRED. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995072800240	19950728	00240	SW 	1995	7	28	HEEA955227 	1	19950626	G	5330	206031004123	SKIN 		206031004115	BELL 	206 	206B3 	1181506	SW 										TAILBOOM	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03					BCJN08724					SKIN RECEIVED WITH EXCESSIVE WAVINESS ON SKIN EDGES ALONG FULL LENGTH.						1	G	7	1 	3U				H2SW 					 
1995072800241	19950728	00241	SW 	1995	7	28	HEEA955228 	1	19950626	G	5330	206031004125	SKIN 		206031004115	BELL 	206 	206B3 	1181506	SW 										TAILBOOM	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03					BCJN08724					SKIN RECEIVED WITH EXCESSIVE WAVINESS ON SKIN EDGES ALONG FULL LENGTH.						1	G	7	1 	3U				H2SW 					 
1995072800242	19950728	00242	EU 	1995	7	28	HEEA955229 	1	19950626	G	6210	117150081	BLADE 			BOLKMS	117 	BK117B2 	5626013	EU 										M/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911LK	3456 				7168				NOSE SHELL SEPARATED NEAR THE LEADING EDGE STRIP.						1	G	7	2 	3U			NC	H13EU 					 
1995072800243	19950728	00243	NE 	1995	7	28	HEEA955230 	1	19950626	G	6410	7610105101042	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	GROOVED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	706AE	2159 				760275				GROOVE ON THE PITCH HORN OF PADDLE "A" WHICH IS BEYOND LIMITS.						1	G	7	2 	3U				H1NE 					 
1995072800244	19950728	00244		1995	7	28	HEEA955231 	4	19950626	G	3416	59341	ALTIMETER 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	CASELEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5007N					45184				ALTIMETER EXCESSIVE CASE LEAK.						1	G	7	1 	3U				H2SW 					 
1995072800245	19950728	00245	SW 	1995	7	28	HEEA955232 	1	19950626	G	5302	206032308103S	FRAME 			BELL 	206 	206L1 	1182107	SW 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y					45751				LOOSE FITTING CAUSED TAILBOOM RING P/N 206-032-308-103S AND LONGERON P/N 206-031-314-037S TO CRACK. SEE MMIR # 5233 FOR 	LONGERON INFORMATION.					1	G	7	1 	3U				H2SW 					 
1995072800246	19950728	00246	SW 	1995	7	28	HEEA955233 	1	19950626	G	5313	206031314037S	LONGERON 			BELL 	206 	206L1 	1182107	SW 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y					45751				LOOSE FITTING CAUSED TAILBOOM RING P/N 206-032-308-103S AND LONGERON P/N 206-031-314-037S TO CRACK. SEE MMIR # 5232 FOR	 FRAME INFORMATION.					1	G	7	1 	3U				H2SW 					 
1995072800247	19950728	00247		1995	7	28	HEEA955234 	4	19950626	G	3416	5934P1	ALTIMETER 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	CASE LEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2251A					45755				ALTIMETER EXCESSIVE CASE LEAK.						1	G	7	1 	3U				H2SW 					 
1995072800248	19950728	00248		1995	7	28	HEEA955235 	4	19950626	G	3416	5035P2P44	ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT ENCODE	CASE LEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2149S					36002				EXCESSIVE CASE LEAK. TIME SINCE REPAIR 345:55.						1	G	7	2 	4U				H4SW 					 
1995072800249	19950728	00249	SW 	1995	7	28	HEEA955236 	1	19950626	G	6340	214074280107	LIMIT DETECTOR 			BELL 	412 	412 	1182202	SW 										ROTOR DRIVE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21498	54 				36003				RPM LIGHT AND AUDIO COMES ON INTERMITTENTLY.						1	G	7	2 	4U				H4SW 					 
1995072800250	19950728	00250		1995	7	28	HEEA955237 	4	19950626	G	3421	7660002113103	GYRO 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VERT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546K					760082				V GYRO CAUSES ADI TO OSCILLATE.						1	G	7	2 	3U				H1NE 					 
1995072800251	19950728	00251	SW 	1995	7	28	HEEA955238 	1	19950626	G	7810	212061201012	EJECTOR 			BELL 	412 	412 	1182202	SW 										RT EXH	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2298Z					33077				EJECTOR CRACKED AT MOUNT POINT.						1	G	7	2 	4U				H4SW 					 
1995072800252	19950728	00252	SW 	1995	7	28	HEEA955239 	1	19950626	G	7810	212061201012	EJECTOR 			BELL 	412 	412 	1182202	SW 										RT EXH	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2149S					36002				RT EJECTOR CRACKED.						1	G	7	2 	4U				H4SW 					 
1995072800253	19950728	00253	EU 	1995	7	28	HEEA955240 	1	19950626	G	7722	TM42739	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										EXH TEMP	ERROR 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5418A					S800				EXCESSIVE FRICTION ERROR. TIME SINCE REPAIR 5:35.						1	G	7	2 	3U				H3EU 					 
1995072800254	19950728	00254		1995	7	28	HEEA955241 	4	19950627	G	2210	7690001802106	POTIENTIOMETER 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS ACTUATOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1546K	6738 				760082				POTENTIOMETERS CHECKED BAD ON STRIP CHART.						1	G	7	2 	3U				H1NE 					 
1995072800255	19950728	00255	SW 	1995	7	28	HEEA955242 	1	19950627	G	5260	FYLM735023	MOTOR ASSY 		SYLC502281 	BELL 	412 	412 	1182202	SW 										STEP	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	33008				1818	36004				ACTUATOR IS INOPERATIVE. INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND MOTOR HAS INTERMITTENT OPERATION. ARMATURE SEE	MS TO HAVE A DEAD SPOT ON COMMUTATOR.					1	G	7	2 	4U				H4SW 					 
1995072800256	19950728	00256		1995	7	28	HEEA955243 	4	19950627	G	2210	7683431	POTENTIOMETER 	HAMSTD 																AUTO FLIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										CAUSES VOLTAGE FROM J1B AND J1E TO GROUND ON BOTH EXTEND AND RETRACT POSITIONS OF ACTUATOR TO BE LOW AND OUT OF LIMITS. 	SENT TO HAMILTON STANDARD																		 
1995072800257	19950728	00257	SW 	1995	7	28	HEEA955244 	1	19950627	G	6710	214001347005	ACTUATOR ROTARY 			BELL 	412 	412 	1182202	SW 										AFCS	BRAKE HANGS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S					36002				BRAKE WILL NOT RELEASE WHEN AFCS ROLL IS ACTUATED.						1	G	7	2 	4U				H4SW 					 
1995072800258	19950728	00258	SW 	1995	7	28	HEEA955245 	1	19950627	G	6730	212076005011	ACTUATOR 			BELL 	212 	212 	1181420	SW 										M/R SERVO	LEAKS 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	5736J	9463 				31140				UPON INSTALLATION BOTH PILOT VALVES WERE FOUND TO HAVE STATIC LEAKS ON SYSTEM #1.						1	G	7	1 	4U				H4SW 					 
1995072800259	19950728	00259	SW 	1995	7	28	HEEA955246 	1	19950627	G	6320	212070116009	INDICATOR 			BELL 	212 	212 	1181420	SW 										XMSN	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5736J					31140				NO INDICATION WITH A-C RUNNING.						1	G	7	1 	4U				H4SW 					 
1995072800260	19950728	00260	SW 	1995	7	28	HEEA955247 	1	19950627	G	6320	212070116009	INDICATOR 			BELL 	212 	212 	1181420	SW 										XMSN OIL	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5736J					31140				NEEDLE ON PRESSURE SIDE HAS NO INDICATION.						1	G	7	1 	4U				H4SW 					 
1995072800261	19950728	00261	EU 	1995	7	28	HEEA955248 	1	19950627	G	7722	25490391	TEMP SENSOR 			BOLKMS	117 	BK117B1 	5626012	EU 										ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			SW	03	217UC					7152				LOW ENGINE POWER. TEMP SENSOR DEFECTIVE						1	G	7	2 	3U				H13EU 					 
1995072800262	19950728	00262		1995	7	28	HEEA955249 	4	19950627	G	3450	214075268101	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	UNRELIABLE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				INDICATOR UNRELIABLE IN FLIGHT.						2	G	7	2 	4U				H10SW 					 
1995072800263	19950728	00263	NE 	1995	7	28	HEEA955250 	1	19950627	G	6220	7610608003042	PISTON 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										ADJUSTMENT SCREW OF CHECK VALVES NOT FLUSH.						1	G	7	2 	3U				H1NE 					 
1995072800264	19950728	00264		1995	7	28	HEEA955251 	4	19950627	G	3421	RCA26BK7	GYRO 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT HORIZ	DEFECTIVE 	E			HEEA	K				NONE 				P			NO WARNING INDICATION 			NR	NOT REPORTED 	1			SW	03	967MB					S737				GYRO PRECESSES IN PITCH, SLOW TO ERECT, LIGHTS INOPERATIVE.						1	G	7	2 	3U				H3EU 					 
1995072800265	19950728	00265		1995	7	28	HEEA955253 	4	19950627	G	2210	7683431	POTENTIOMETER 	HAMSTD 																AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										POTIENTIOMETER CAUSES VOLTAGE FROM J1-B TO GROUND ON BOTH EXTEND AND RETRACT POSITIONS OF ACTUATOR TO BE TOO LOW AND OUT	 OF LIMITS. SENT TO HAMILTON STANDARD																		 
1995072800266	19950728	00266	EU 	1995	7	28	HEEA955255 	1	19950627	G	7400	355A72302300	SENSOR ASSY 			AEROSP	AS355 	AS355F1 	8680810	EU 										AUTO RELIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y					5141				UNIT TRANSMITS LOW OUT OF TOLERANCE.						1	G	7	2 	3U				H11EU 					 
1995072800267	19950728	00267	SW 	1995	7	28	HEEA955256 	1	19950627	G	6340	206075739113	TORQUEMETER 			BELL 	206 	206L 	1181522	SW 										COCKPIT	FLUCTUATES 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7074W					52033				TORQUE INDICATION FLUCTUATES 5% TO 8% AND WORSENS AT HIGHER TORQUE SETTINGS.						1	G	7	1 	3U				H2SW 					 
1995072800268	19950728	00268	EU 	1995	7	28	HEEA955258 	1	19950627	G	7400	355A72302300	SENSOR ASSY 			AEROSP	AS355 	AS355F1 	8680810	EU 										AUTO RELIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y					5141				SENSOR READS HIGH OUT OF TOLERANCE.						1	G	7	2 	3U				H11EU 					 
1995072800269	19950728	00269	EU 	1995	7	28	HEEA955259 	1	19950627	G	7714	6503A3101	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT N1	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911TL					7198				INDICATOR READS HIGH OUT OF TOLERANCE AT HIGH RANGE.						1	G	7	2 	3U				H13EU 					 
1995072800270	19950728	00270	EU 	1995	7	28	HEEA955260 	1	19950627	G	7930	6607190A	SWITCH 			BOLKMS	105 	BO105S 	5626006	EU 										OIL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	352TT	22 				S59				OIL PRESS CONTACTS FLUCTUATES.						1	G	7	2 	3U				H3EU 					 
1995072800271	19950728	00271		1995	7	28	HEEA955261 	4	19950627	G	3422	258719342	GYRO COMPASS 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	792CH					760193				GYRO WILL NOT SPIN UP OR BECOME VALID.						1	G	7	2 	3U				H1NE 					 
1995072800272	19950728	00272	SW 	1995	7	28	HEEA955262 	1	19950627	G	2840	384178091	SELECTOR 			BELL 	212 	212 	1181420	SW 										FUEL QTY	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1079U					31122				SWITCH STICKS IN RIGHT POSITION.						1	G	7	1 	4U				H4SW 					 
1995072800273	19950728	00273	SW 	1995	7	28	HEEA955263 	1	19950627	G	2432	40155002	CAN ASSY 		3055401C 	BELL 	206 	206L1 	1182107	SW 										BATTERY	PAINT PEEL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	406EH				9303191	45183				BATTERY INSPECTED BY ACCESSORY SHOP AND FOUND PAINT SEPARATING FROM CASE.						1	G	7	1 	3U				H2SW 					 
1995072800274	19950728	00274	SW 	1995	7	28	HEEA955264 	1	19950627	G	6340	214074280107	LIMIT DETECTOR 			BELL 	412 	412 	1182202	SW 										ROTOR RPM	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21498					36003				AUDIO ERRATIC.						1	G	7	2 	4U				H4SW 					 
1995072800275	19950728	00275	SW 	1995	7	28	HEEA955265 	1	19950627	G	7100	4069T14P04	HOSE 			BELL 	214 	214ST 	1182106	SW 										ENG SYS	LEAKS 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	8045T					28101				HOSE LEAKS AT B-NUT FACING.						2	G	7	2 	4U				H10SW 					 
1995072800276	19950728	00276	SW 	1995	7	28	HEEA955266 	1	19950627	G	6710	214001970111	ACTUATOR ASSY 			BELL 	214 	214ST 	1182106	SW 										M/R	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				ELEVATOR ACTUATOR IS INOPERATIVE.						2	G	7	2 	4U				H10SW 					 
1995072800277	19950728	00277	NE 	1995	7	28	HEEA955267 	1	19950627	G	3040	7655001013103	WIPER MOTOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22342					760096				HEATING UP AND POPPING CIRCUIT BREAKER ON AIRCRAFT. SENT TO HELICOPTER SUPPORT FOR EXCHANGE...THEIR PROPERTY BEING RETUR	NED.					1	G	7	2 	3U				H1NE 					 
1995072800278	19950728	00278	SW 	1995	7	28	HEEA955268 	1	19950627	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENG	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N					28106				KICKED OFF DURING START AT 45% N1, ON SECOND START ATTEMPT, WOULD NOT ENGAGE AT ALL.						2	G	7	2 	4U				H10SW 					 
1995072800279	19950728	00279		1995	7	28	HEEA955269 	4	19950627	G	3444	7001840913	TRANSCEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2347	177 				36005				TRANSCEIVER INTERMITTENTLY ERRATIC.						1	G	7	2 	4U				H4SW 					 
1995072800280	19950728	00280	SW 	1995	7	28	HEEA955271 	1	19950627	G	2824	L88010491	VALVE 			BELL 	212 	212 	1181420	SW 										FUEL XSFER	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1079U					31122				VALVE INOPERATIVE.						1	G	7	1 	4U				H4SW 					 
1995072800281	19950728	00281	SW 	1995	7	28	HEEA955272 	1	19950627	G	2824	L88010491	VALVE 			BELL 	212 	212 	1181420	SW 										FUEL XSFER	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1079U					31122				VALVE INOPERATIVE.						1	G	7	1 	4U				H4SW 					 
1995072800282	19950728	00282	CE 	1995	7	28	HEEA955273 	1	19950627	G	2820	1036484	VALVE 			BEECH 	200 	200BEECH 	1152920	CE 										FUEL SYS	BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	30PH					BB635				VALVE BROKEN AT FILTER FITTING.						1	L	7	2 	4T				A24CE 					 
1995072800283	19950728	00283	EU 	1995	7	28	HEEA955275 	1	19950627	G	6300	SKCP24563	DRIVESHAFT 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	105WK	1970 				S812				6 EACH NUT PLATES DO NOT HAVE LOCKING QUALITY AND S/N AND P/N DECAL PEELING.						1	G	7	2 	3U				H3EU 					 
1995072800284	19950728	00284	SW 	1995	7	28	HEEA955276 	1	19950627	G	6320	206040032011	BEARING 		206040004111	BELL 	206 	206L1 	1182107	SW 										M/R XMSN	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5742N				BMC00214	45477				INNER AND OUTER RACES AND BALL SPALLING. REPLACED WITH NEW BEARING SET AND RETURNED TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995072800285	19950728	00285	SW 	1995	7	28	HEEA955277 	1	19950627	G	6720	206011731001	BEARING 		206011721009	BELL 	206 	206L1 	1182107	SW 										T/R CONTROL	FAILED 	E			HEEA	K				NONE 				F			FLT CONT AFFECTED 			IN	INSP/MAINT 	1			SW	03	2764F					45279				PILOT REPORTED LIMITED TRAVEL OF LEFT TAIL ROTOR PEDAL WITH LEFT PEDAL NOT REACHING THE NORMAL STOP POSITION. WITH REFE	RENCE TO BELL HELICOPTER 206L-1 IPC, FIGURE 64-1. FOUND 1 EACH ROLLER FROM BEARING ITEM #70 MISSING FROM BEARING CAGE. 	 THE ROLLER WORKED ITS WAY DOWN CONTROL TUBE P/N 206-011-724-005 (ITEM #73) AND WAS FOUND LODGED IN THE SLOT OF THIS CO	NTROL TUBE. CONTROL TUBE MOVEMENT WAS LIMITED WHEN THE ROLLER CONTACTED THE KEY P/N 206-011-704-001 (ITEM #27). THE FA	CE OF THE KEYSHOWED PEENING MARKS FROM REPEATED CONTACT WITH THE ROLLER. REPLACED THE T/R GEARBOX ASSEMBLY AND PITCH CHA	NGE ASSEMBLY FOR INSPECTION AND REPAIR.	1	G	7	1 	3U				H2SW 					 
1995072800286	19950728	00286	SW 	1995	7	28	HEEA955278 	1	19950627	G	6300	206040015103	SHAFT 			BELL 	206 	206B3 	1181506	SW 										M/R DRIVE	INDICATOR DARK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268W	9302 				3606				YELLOW TEMP INDICATORS DARK. INSTALLED SERVICEABLE DRIVESHAFT.						1	G	7	1 	3U				H2SW 					 
1995072800287	19950728	00287	SW 	1995	7	28	HEEA955279 	1	19950627	G	6330	206033506101	RESTRAINT 			BELL 	206 	206L1 	1182107	SW 										TRANSMISSION	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	406EH					45183				BOTH BEARINGS IN RESTRAINT WERE WORN AND THE BEARING ON R/H SIDE OF TRANSMISSION RESTRAINT WAS UNSTAKED.						1	G	7	1 	3U				H2SW 					 
1995072800288	19950728	00288	SW 	1995	7	28	HEEA955280 	1	19950627	G	6220	16549011	YAW DAMPERS 			HUGHES	500N 	500N 	3027374	SW 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	9213P	99 				90000013				FOUND LH END PLATES HAD A LOT OF PLAY DURING 100 HOUR INSPECTION. FOUND PLAY TO BE AT LH YAW DAMPER SHAFT AT INBOARD SI	DE.					1	G	7	1 	3U			NC	H3WE 					 
1995072800289	19950728	00289	NE 	1995	7	28	HEEA955281 	1	19950627	G	7603	7630103034042	ARM ASSY 			SKRSKY	S76 	S76A 	8143006	NE 										CONTROL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										TURBINE CONTROL STUD TOO LONG AND TOO SMALL.						1	G	7	2 	3U				H1NE 					 
1995072800290	19950728	00290	EU 	1995	7	28	HEEA955282 	1	19950629	G	2121	420800001	BLOWER 			SNIAS 	350 	AS350B2 	8680813	EU 										AIR DIST	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	350BZ	1093 				2653				BLOWER BRUSHES STICK.						1	G	7	1 	3U				H9EU 					 
1995072800291	19950728	00291	GL 	1995	7	28	HEEA955283 	2	19950629	G	7250	23038212	INTERNAL SUMP 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					ENG N2	SEAL DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5737T				CAT70180	45454	CAE860136			ENGINE REMOVED DUE TO N2 SEIZURE. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 50% OF GRAPHITE LIFTING IN INT	ERNAL SUMP 9/12 SEAL, CAUSING N2 SEIZURE.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995072800292	19950728	00292		1995	7	28	HEEA955284 	4	19950629	G	3416	214175278101	ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				KOLSMAN KNOB WILL NOT ADJUST BAROMETRIC PRESSURE.						1	G	7	2 	4U				H4SW 					 
1995072800293	19950728	00293		1995	7	28	HEEA955285 	4	19950629	G	2210	7683431	POTENTIOMETER 	HAMSTD 																AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										POTIENTIOMETER CAUSES VOLTAGE FROM J1-B OR J1-E TO GROUND ON BOTH EXTEND AND RETRACT POSITIONS OF ACTUATOR TO BE TOO LOW	 AND OUT OF LIMITS. SENT TO HAMILTON STANDARD FOR WARRANTY EXCHANGE.																		 
1995072800294	19950728	00294	SW 	1995	7	28	HEEA955286 	1	19950629	G	6220	206011149105	YOKE 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R HUB	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1072T	1200 			A2327	45385				BEARING JOURNALS ON YOKE BREAKING DOWN ALONG WITH FOUR BEARINGS P/N 206-011-118-001 AND TWO EACH TRUNNION BEARING/RACE A	SSEMBLIES P/N 206-011-111-001. GREASE REMOVED FROM M/R WAS PARTIALLY LIQUEFIED AND CONTAMINATED WITH METAL PARTICLES. T	OTAL TIME ON ALL PARTS REMOVED 1200:35.				1	G	7	1 	3U				H2SW 					 
1995072800295	19950728	00295	SW 	1995	7	28	HEEA955288 	1	19950630	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENGINE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M	507 				28102				STARTER SPINS BUT WOULD NOT ENGAGE.						2	G	7	2 	4U				H10SW 					 
1995072800296	19950728	00296	SW 	1995	7	28	HEEA955289 	1	19950630	G	6220	206011154107	STRAP 		206011100159	BELL 	206 	206L 	1181522	SW 										M/R HUB	SEALS DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7077F	869 			HB438	52038				STRAPS S/N LK7796 AND LK7807 REMOVED DUE TO 2 YEAR RETIREMENT AS PER AD 78-11-02R1. AT DISASSEMBLY FOUND 1 EACH PILLOW 	BLOCK SEAL P/N 450351 DAMAGED. FOUND GRIP SEALS LEAKING AND RETAINER LOOSE. FOUND TRUNNION PLUGS DETERIORATED.					1	G	7	1 	3U				H2SW 					 
1995072800297	19950728	00297	SW 	1995	7	28	HEEA955290 	1	19950630	G	6220	206011125001	PIN STRAP 		206011100159	BELL 	206 	206L 	1181522	SW 										M/R	SEALS FAULTY 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	7077F	869 			HB438	52038				STRAPS S/N LK7796 AND LK7807 REMOVED DUE TO 2 YEAR RETIREMENT AS PER AD 78-11-02R1. AT DISASSEMBLY FOUND 1 EACH PILLOW 	BLOCK SEAL P/N 450351 DAMAGED. FOUND GRIP SEALS LEAKING AND RETAINER LOOSE. FOUND TRUNNION PLUGS DETERIORATED. PIN SE	RIALNUMBERS REMOVED DI14392 AND DI14340.				1	G	7	1 	3U				H2SW 					 
1995072800298	19950728	00298	SW 	1995	7	28	HEEA955292 	1	19950630	G	6320	206040032011	BEARING 		206040004101	BELL 	206 	206L1 	1182107	SW 										M/R	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	10814				BMC45219	45415				TRANSMISSION REMOVED DUE TO EXCESSIVE METAL ON CHIP PLUG. BEARING SPALLED. REPAIRED TRANSMISSION AND REPLACED BEARING W	ITH NEW PART.					1	G	7	1 	3U				H2SW 					 
1995072800299	19950728	00299		1995	7	28	HEEA955293 	4	19950630	G	2210	7690001802106	ACTUATOR 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	STICKS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1547D	2356 				760077				ACTUATOR STICKS, INTERMITTENTLY INOPERATIVE. INSPECTED BY ACCESSORY SHOP AND FOUND JUST BEFORE AND AFTER NULL POSITION 	#2 (J1-E) POTENTIOMETER VOLTAGE DROPS TO ZERO (HAS AN OPEN SPOT)					1	G	7	2 	3U				H1NE 					 
1995072800300	19950728	00300	SW 	1995	7	28	HEEA955294 	1	19950630	G	6220	206010110105	WASHER 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R THRUST	DETERIORATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50182	345 			A2028	45242				MATERIAL DETERIORATION CAUSING EXCESSIVE LOAD. LOWERED TORQUE ON ADJUSTMENT SCREWS AND LOWERED PRELOAD ON THRUST PLUGS.						1	G	7	1 	3U				H2SW 					 
1995072800301	19950728	00301	SW 	1995	7	28	HEEA955295 	1	19950630	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENGINE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M	277 				28102				STARTER DOES NOT ENGAGE.						2	G	7	2 	4U				H10SW 					 
1995072800302	19950728	00302	EU 	1995	7	28	HEEA955296 	1	19950630	G	7930	6607190A	SWITCH 			BOLKMS	105 	BO105S 	5626006	EU 										XMSN OIL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	205UC	71 				S668				TRANSMISSION OIL LIGHT WILL NOT COME ON. STUCK BETWEEN PIN B AND A. SENT TO CONSOLIDATED CONTROLS FOR WARRANTY REPAIR.						1	G	7	2 	3U				H3EU 					 
1995072800311	19950728	00311	EU 	1995	7	28	HEEA955297 	1	19950705	G	6210	355A11002011	BLADE 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1489 				2771				CRACK IN SKIN ON TOP APPROXIMATELY 6'8" OUTBOARD OF ATTACH POINT.						1	G	7	1 	3U				H9EU 					 
1995072800312	19950728	00312	EU 	1995	7	28	HEEA955298 	1	19950705	G	6210	355A11002011	BLADE 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1489 				2771				CRACK IN SKIN ON TOP APPROXIMATELY 5'9" OUTBOARD OF ATTACH POINT.						1	G	7	1 	3U				H9EU 					 
1995072800313	19950728	00313	SW 	1995	7	28	HEEA955299 	1	19950705	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										ENGINE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				STARTER WOULD NOT ENGAGE.						2	G	7	2 	4U				H10SW 					 
1995072800314	19950728	00314	EU 	1995	7	28	HEEA955300 	1	19950705	G	7931	BSE206150G3	TRANSDUCER 			BOLKMS	105 	BO105S 	5626006	EU 										NR 1 ENG OIL	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5418A					S800				WHILE ADVANCING #1 THROTTLE FROM FLIGHT IDLE TO FULL OPEN #1 ENGINE OIL PRESSURE DROPPED TO ZERO. REPLACED WITH SERVICEA	BLE TRANSMITTER AND RETURNED TO SERVICE.					1	G	7	2 	3U				H3EU 					 
1995072800315	19950728	00315	EU 	1995	7	28	HEEA955301 	1	19950705	G	3340	G62504	LIGHT 			BOLKMS	105 	BO105S 	5626006	EU 										SEARCH	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	205UC					S668				SEARCHLIGHT WILL NOT RETRACT. REPLACED WITH SERVICEABLE SEARCHLIGHT ASSEMBLY.						1	G	7	2 	3U				H3EU 					 
1995072800316	19950728	00316	SW 	1995	7	28	HEEA955302 	1	19950705	G	6320	524919	SEAL 			BELL 	206 	206L1 	1182107	SW 										ENG GR BOX	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2245Y					45751				TRANSFERRING OIL FROM ENGINE TO TRANSMISSION. REPLACED FWD AND AFT DOUBLE LIP SEALS IN ENGINE GEARBOX.						1	G	7	1 	3U				H2SW 					 
1995072800317	19950728	00317	SW 	1995	7	28	HEEA955303 	1	19950705	G	7712	206075185101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										ENG TORQUE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	10778					45391				TORQUE INDICATOR READING 4% LOW. GIVING INDICATION OF HIGH TOT ON POWER CHECK. REPLACED WITH SERVICEABLE TORQUE IND.						1	G	7	1 	3U				H2SW 					 
1995072800318	19950728	00318	EU 	1995	7	28	HEEA955304 	1	19950705	G	7712	43511209	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										DUAL TORQUE	MIS MARKED 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			NR	NOT REPORTED 	1			SW	03	967MB					S737				TORQUE IND. WORKS WELL, BUT RANGE MARKING OFF AS PER FLIGHT MANUAL. REPLACED WITH SERVICEABLE TORQUE IND.						1	G	7	2 	3U				H3EU 					 
1995072800319	19950728	00319	SW 	1995	7	28	HEEA955305 	1	19950705	G	5230	047382128009	HINGE ASSY 			BELL 	412 	412 	1182202	SW 										BAG DOOR	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	23023	258 				33080				MODIFIED BAGGAGE DOOR UPPER HINGE CRACKED BETWEEN RIVET THAT KEEPS ABRASION BUMPER IN PLACE. REMOVED AND REPLACED HINGE.						1	G	7	2 	4U				H4SW 					 
1995072800320	19950728	00320	NE 	1995	7	28	HEEA955306 	1	19950705	G	2430	A1077D	RELAY 			SKRSKY	S76 	S76A 	8143006	NE 										NR 1 DC SYS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5128					760181				#1 GEN WOULD NOT COME ON LINE AFTER START. FOUND SCREWS THAT HOLD RELAY HALVES TOGETHER HAD BACKED COMPLETELY OUT ALLOW	ING SOLENOID PLUNGER TO JAM NOT ALLOWING MICRO SWITCHES TO GO TO REST. REPLACED WITH SERVICEABLE RELAY. SUGGEST LOCK TI	GHT BE APPLIED TO ALL RELAY SCREWS IF NOT BEING DONE ALREADY.				1	G	7	2 	3U				H1NE 					 
1995072800321	19950728	00321	EU 	1995	7	28	HEEA955307 	1	19950705	G	7931	DK040	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										NR 1 ENG OIL	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	724MB	107 				S756				#1 ENGINE OIL PRESSURE INDICATOR PEGS ON HIGH SIDE IN FLIGHT. REPLACED #1 OIL PRESSURE TRANSMITTER AND RETURNED TO SERVI	CE.					1	G	7	2 	3U				H3EU 					 
1995072800322	19950728	00322		1995	7	28	HEEA955308 	4	19950705	G	3453	4530103	LORAN 		ARNAV21 	AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5785Y					5105				INTERMITTENTLY LOSES STATIONS AND SWITCHES ON AND OFF.						1	G	7	2 	3U				H11EU 					 
1995072800323	19950728	00323	SW 	1995	7	28	HEEA955309 	1	19950705	G	6300	206030539101	MOUNT 			BELL 	206 	206B3 	1181506	SW 										INPUT DRIVE	OVER TEMP DOT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268W					3606				INPUT DRIVE SHAFT FORWARD AND COUPLING YELLOW TEMPERATURE INDICATOR DOTS TURNED BLACK INDICATING ELEVATED TEMPERATURE.						1	G	7	1 	3U				H2SW 					 
1995072800324	19950728	00324		1995	7	28	HEEA955310 	4	19950705	G	3453	4530093	RECEIVER 		ARNAV20 	AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5786D					5113				LORAN HARD TO SEE THROUGH FACEPLATE.						1	G	7	2 	3U				H11EU 					 
1995072800325	19950728	00325		1995	7	28	HEEA955311 	4	19950705	G	2312	063100700	TRANSCEIVER 		KTR993 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893S					33022				TRANSCEIVER WILL NOT TUNE.						1	G	7	2 	4U				H4SW 					 
1995072800326	19950728	00326		1995	7	28	HEEA955312 	4	19950705	G	3453	453105004	LORAN 	ARNAV 		SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	792CH					760193				ENTER BUTTON INTERMITTENT.						1	G	7	2 	3U				H1NE 					 
1995072800327	19950728	00327		1995	7	28	HEEA955313 	4	19950705	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	2014K	2803 				33020				CVR WILL NOT TEST; RATTLE INSIDE. TIME SINCE REPAIR 0:00.						1	G	7	2 	4U				H4SW 					 
1995072800328	19950728	00328		1995	7	28	HEEA955314 	4	19950705	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	21498	3135 				36003				CVR WILL NOT TEST.						1	G	7	2 	4U				H4SW 					 
1995072800329	19950728	00329		1995	7	28	HEEA955315 	4	19950705	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	2014K	2405 				33020				CVR WILL NOT TEST.						1	G	7	2 	4U				H4SW 					 
1995072800330	19950728	00330	EU 	1995	7	28	HEEA955316 	1	19950705	G	6240	10594575	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										M/R MAST	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	81992					S827				TORQUE FLUCTUATES.						1	G	7	2 	3U				H3EU 					 
1995072800331	19950728	00331	EU 	1995	7	28	HEEA955317 	1	19950705	G	6240	10594564	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	81992					S827				INDICATOR FLUCTUATES.						1	G	7	2 	3U				H3EU 					 
1995072800332	19950728	00332		1995	7	28	HEEA955318 	4	19950705	G	3416	5035P2P44	ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT ENCODE	ERROR 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				ENCODER IS 100 FEET OFF AT 10,000 FEET. SENT TO ALLIED SIGNAL AVIONICS FOR WARRANTY REPAIR. TIME SINCE REPAIR 213:15.						1	G	7	2 	4U				H4SW 					 
1995072800333	19950728	00333	SW 	1995	7	28	HEEA955319 	1	19950705	G	7714	212075037101	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT N1	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				NEEDLE ERRATIC ON LOW END.						1	G	7	2 	4U				H4SW 					 
1995072800334	19950728	00334	EU 	1995	7	28	HEEA955320 	1	19950705	G	6240	10594565	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	105WK					S812				TRANSMITTER CAUSES NEEDLE TO DROP TO YELLOW ARC WHEN TEST BUTTON IS DEPRESSED.						1	G	7	2 	3U				H3EU 					 
1995072800335	19950728	00335	EU 	1995	7	28	HEEA955321 	1	19950706	G	6240	10594575	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	105WK					S812				TRANSMITTER CAUSES NEEDLE TO DROP TO YELLOW ARC WHEN TEST BUTTON IS DEPRESSED.						1	G	7	2 	3U				H3EU 					 
1995072800336	19950728	00336		1995	7	28	HEEA955322 	4	19950706	G	3453	066402600	LORAN 		KLN88 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6603X					51412				SLOW TO INITIALIZE UP TO 20 MINUTES.						1	G	7	1 	3U				H2SW 					 
1995072800337	19950728	00337		1995	7	28	HEEA955323 	4	19950706	G	3453	453105004	LORAN 	ARNAV 		BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4391S					S787				ENTER BUTTON IS INTERMITTENT.						1	G	7	2 	3U				H3EU 					 
1995072800338	19950728	00338		1995	7	28	HEEA955324 	4	19950706	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268G					3603				OFF FREQUENCY. FOUND UNIT DID NOT POWER UP. REPLACED TRANSISTOR Q415. REPAIRED PROBLEM. INSTALLED HEAT SINK BEHIND TR	ANSISTOR Q415. REPLACED DETERIORATED RESISTOR R477. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. ALSO ADJUSTED FR	EQUENCY TO SPECS.CLEANED CONTACTS ON WAFERS. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995072800339	19950728	00339		1995	7	28	HEEA955325 	4	19950706	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3108E					51498				APPEARS INOPERATIVE AND LIGHT DOES NOT COME ON DURING TEST. REPLACED PHOTOCELL V301. REPAIRED. REPLACED CRACKED FACEPL	ATE ASSY. REPLACED CAVITY TUBE V101 DUE TO LOW POWER OUT. INSTALLED HEATSINK BEHIND TRANSISTOR Q415 AND REPLACED DETER	IORATED RESISTOR R477. ADJUSTED FREQUENCY, PULSE WIDTH AND ALIGNEDRECEIVER TO SPECS. CLEANED CONTACTS ON ALL WAFERS. B	ENCH CHECK GOOD.			1	G	7	1 	3U				H2SW 					 
1995072800340	19950728	00340		1995	7	28	HEEA955326 	4	19950706	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2251Z					45756				INOPERATIVE. WONT IDENT. REPLACED TRANSISTOR Q415. REPAIRED. REPLACED DETERIORATED RESISTOR R477. INSTALLED HEATSINK	 BEHIND TRANSISTOR Q415. ADJUSTED FREQUENCY AND POWER OUT TO SPECS. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995072800341	19950728	00341		1995	7	28	HEEA955327 	4	19950706	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B3 	1181506	SW 										COCKPIT	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268W					3606				FACEPLATE BROKEN. REPLACED FACEPLATE. REPAIRED. FOUND MTL TO BE WAY BELOW SPECS. REPLACED TRANSISTOR Q415. REPLACED 	DIODE CR407. REPAIRED. FOUND UNIT TO HAVE WEAK POWER OUT. TRIED ADJUSTING POWER OUT TO SPECS. NO HELP. REPLACED CAV	ITY TUBE 101. REPAIRED.ADJUSTED FREQUENCY. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995072800342	19950728	00342		1995	7	28	HEEA955328 	4	19950706	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5007Q					45187				INOPERATIVE. FOUND THAT UNIT WOULD NOT RECEIVE OR TRANSMIT. REPLACED CAVITY TUBE V101. REPAIRED PROBLEM. ADJUSTED FRE	QUENCY AND ALIGNED RECEIVER TO SPECS. CLEANED CONTACTS ON ALL WAFERS. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995072800343	19950728	00343		1995	7	28	HEEA955329 	4	19950706	G	3455	066107200	RECEIVER 		KR87 	BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT ADF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	132AE					7238				DISPLAY IS BAD. FOUND SEGMENTS TO BE MISSING IN DISPLAY. REPLACED DISPLAY. REPAIRED PROBLEM. LOWER DOT ON COLON IS BR	IGHT AND IS CONSTANTLY LIT. REPLACED INTEGRATED CIRCUIT I507. REPAIRED PROBLEM. BENCH CHECK GOOD.					1	G	7	2 	3U			NC	H13EU 					 
1995072800344	19950728	00344		1995	7	28	HEEA955330 	4	19950706	G	2312	4000106010	CONTROL 		C10 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	105WK					S812				SQUELCH INOPERATIVE. REPLACED S6 SWITCH. REPAIRED.						1	G	7	2 	3U				H3EU 					 
1995072800345	19950728	00345	GL 	1995	7	28	HEEA955331 	2	19950706	G	7313	5233600	FUEL NOZZLE 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5742N	4990 				45477				ENGINE HARD TO START. REQUIRED BATTERY CART ON 2 OR 3 STARTS. REPLACED WITH SERVICEABLE FUEL NOZZLE.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995072800346	19950728	00346	EU 	1995	7	28	HEEA955332 	1	19950706	G	6321	419210	BRAKE 			BOLKMS	105 	BO105S 	5626006	EU 										ROTOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	205UC					S668				PUCKS ON ROTOR BRAKE CALIPER WILL NOT RETRACT. REPLACED WITH SERVICEABLE ROTOR BRAKE CALIPER.						1	G	7	2 	3U				H3EU 					 
1995072800347	19950728	00347	SW 	1995	7	28	HEEA955335 	1	19950706	G	2430	1101461	RELAY 			BELL 	230 	230 	1182149	SW 										NR 1 GEN	FAULTY 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2122 				23009				BUS INHIBIT RELAY CAUSING #1 GENERATOR TO KICK OFF LINE WHEN #2 ENGINE IS STARTED.						1	G	7	2 	3U			NC	H9SW 					 
1995080400001	19950804	00001	GL 	1995	8	4	HEEA955336 	2	19950710	G	7320	1564T1005	SERVOMOTOR 			BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					ENG CONTROL	TRIPS BREAKER 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3071K	1395 				S859				POPS CIRCUIT BREAKER. INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND MOTOR HAS INTERMITTENT OPERATION.						1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995080400002	19950804	00002	SW 	1995	8	4	HEEA955338 	1	19950710	G	5330	206072154103	PANEL 			BELL 	230 	230 	1182149	SW 										FUSELAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2083 				23009				PANEL CRACKED. PARTS SCRAPPED IN FIELD.						1	G	7	2 	3U			NC	H9SW 					 
1995080400003	19950804	00003	SW 	1995	8	4	HEEA955339 	1	19950710	G	6330	222331617101	MOUNT 			BELL 	230 	230 	1182149	SW 										XMSN ISOLATION	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	326 				23009				TRANSMISSION LATERAL ISOLATION MOUNT FAILED IN FLIGHT.						1	G	7	2 	3U			NC	H9SW 					 
1995080400004	19950804	00004	SW 	1995	8	4	HEEA955341 	1	19950711	G	7714	412075010109	INDICATOR 			BELL 	412 	412 	1182202	SW 										TRIPLE TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				TRIPLE TACH HAS 2% SPLIT BETWEEN NEEDLES.						1	G	7	2 	4U				H4SW 					 
1995080400005	19950804	00005	EU 	1995	8	4	HEEA955342 	1	19950711	G	7931	6607190A	SWITCH 			BOLKMS	105 	BO105S 	5626006	EU 										OIL PRESS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	50293	146 				S677				SWITCH WILL NOT CLOSE.						1	G	7	2 	3U				H3EU 					 
1995080400006	19950804	00006		1995	8	4	HEEA955343 	4	19950711	G	2370	9806019001	CVR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5748M	3701 				28102				CVR WILL NOT TEST.						2	G	7	2 	4U				H10SW 					 
1995080400007	19950804	00007		1995	8	4	HEEA955344 	4	19950711	G	2370	9806019001	CVR 			BEECH 	200 	200BEECH 	1152920	CE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	30PH	2116 				BB635				CVR WILL NOT TEST.						1	L	7	2 	4T				A24CE 					 
1995080400008	19950804	00008	SW 	1995	8	4	HEEA955345 	1	19950711	G	7722	206375006101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1078D	326 				45397				TOT NEEDLE INTERMITTENTLY STICKS THROUGHOUT SCALE.						1	G	7	1 	3U				H2SW 					 
1995080400009	19950804	00009	NE 	1995	8	4	HEEA955346 	1	19950711	G	6410	7610105101041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	PITTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5435V	6320 				760158				EXCESSIVE PITTING IN THE BOX BEAM OF PADDLE "B". (REPLACEMENT OF BOX BEAM AND PITCH HORN ONLY)						1	G	7	2 	3U				H1NE 					 
1995080400010	19950804	00010	NE 	1995	8	4	HEEA955347 	1	19950711	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545K					760047				FIBERGLASS SKIN BROKEN BETWEEN THE INNER AND OUTER DOUBLER ON BOTH SURFACES.						1	G	7	2 	3U				H1NE 					 
1995080400011	19950804	00011	EU 	1995	8	4	HEEA955348 	1	19950711	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	54197	7525 				S805				NOSE AND NECK SHELL CRACKED IN ROOT END AREA.						1	G	7	2 	3U				H3EU 					 
1995080400012	19950804	00012	EU 	1995	8	4	HEEA955349 	1	19950711	G	7330	81141010010	TRANSMITTER 			AEROSP	AS355 	AS355F2 	8680812	EU 										FUEL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6040U					5474				PRESSURE DROPS TO ZERO IN FLIGHT. (INTERMITTENTLY) TIME SINCE REPAIR 262:50.						1	G	7	2 	3U				H11EU 					 
1995080400013	19950804	00013	EU 	1995	8	4	HEEA955350 	1	19950711	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117B2 	5626013	EU 										NR 2 FUEL QTY	FLUCTUATES 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911LK					7168				#2 SUPPLY NEEDLE FLUCTUATES UP AND DOWN AFTER ABOUT 15 MINUTES (WHEN GAUGE WARMS UP)						1	G	7	2 	3U			NC	H13EU 					 
1995080400014	19950804	00014		1995	8	4	HEEA955351 	4	19950711	G	2312	064105430	TRANSCEIVER 			BELL 	206 	206L3 	1182108	SW 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	206FS					51506				SWITCHES CHANNELS BY ITSELF AND HARD TO CHANGE FREQUENCY.						1	G	7	1 	3U				H2SW 					 
1995080400015	19950804	00015	SW 	1995	8	4	HEEA955352 	1	19950711	G	6520	206040420101	SPACER 			BELL 	206 	206L 	1181522	SW 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	7077B					52037				SEAL LEAKING. REPLACED WITH NEW SPACER AND RETURNED TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995080400016	19950804	00016	EU 	1995	8	4	HEEA955353 	1	19950713	G	2810	10270	TANK COVER 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL SYS	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3071K	1289 				S859				TANK COVER CRACKED. SCRAPPED IN FIELD.						1	G	7	2 	3U				H3EU 					 
1995080400017	19950804	00017	SW 	1995	8	4	HEEA955355 	1	19950713	G	6320	206040032011	BEARING 		206040004111	BELL 	206 	206L1 	1182107	SW 										M/R	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50182				BMC45124	45242				METAL IN OIL. CAUSE OF METAL IN OIL DUE TO BEARING SPALLED. REPLACED WITH SERVICEABLE BEARING. REPAIRED TRANSMISSION.						1	G	7	1 	3U				H2SW 					 
1995080400018	19950804	00018		1995	8	4	HEEA955356 	4	19950713	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	206LS					51070				ON/OFF KNOB BROKEN. REPLACED FACEPLATE ASSY. REPAIRED. FOUND UNIT TO HAVE NO BACKLIGHTING. REPLACED BURNT BULB DS302.	 REPAIRED. UNIT HAD LOW POWER OUT. TRIED ADJUSTING BUT COULD NOT ADJUST POWER OUT TO SPECS. REPLACED CAVITY TUBE V10	1. REPAIRED. ADJUSTEDFREQUENCY. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995080400019	19950804	00019		1995	8	4	HEEA955357 	4	19950713	G	2210	7683431	POTENTIOMETER 	HAMSTD 																AUTO FLIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										POTIENTIOMETER CAUSES VOLTAGE FROM J1-B OR J1-E TO GROUND ON BOTH EXTEND AND RETRACT POSITIONS OF ACTUATOR TO BE TOO LOW	 AND OUT OF LIMITS.																		 
1995080400020	19950804	00020	SW 	1995	8	4	HEEA955359 	1	19950713	G	7714	412075010109	INDICATOR 			BELL 	412 	412 	1182202	SW 										TRIPLE TACH	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				#1 NEEDLE INTERMITTENTLY STICKS BETWEEN 50-60%. TIME SINCE REPAIR 143:10.						1	G	7	2 	4U				H4SW 					 
1995080400021	19950804	00021		1995	8	4	HEEA955360 	4	19950713	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22425					45743				DOESN'T REPLY. FOUND UNIT DOES NOT TRANSMIT OR RECEIVE. REPLACED OPEN RESISTOR R429 AND BAD DIODE CR404. REPAIRED RECE	IVER PROBLEM. REPLACED CAVITY TUBE V101 DUE TO NO POWER OUT. REPAIRED. ALIGNED RECEIVER TO SPECS. REPLACED PHOTOCELL	 V301 DUE TO WEAK REPLYLIGHT. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995080400022	19950804	00022	SW 	1995	8	4	HEEA955361 	1	19950713	G	7722	212075037105	INDICATOR 			BELL 	412 	412 	1182202	SW 										GAS PRODUCER	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S					36002				NEEDLE INTERMITTENTLY STICKS THROUGHOUT SCALE. TIME SINCE REPAIR 2:35.						1	G	7	2 	4U				H4SW 					 
1995080400232	19950804	00232	SW 	1995	8	4	HEEA955364 	1	19950718	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										CRACK ON THE LEADING EDGE NEAR THE TIP IN A CHORDWISE DIRECTION.						1	G	7	1 	3U				H2SW 					 
1995080400233	19950804	00233	SW 	1995	8	4	HEEA955365 	1	19950718	G	6330	222331618105	ISOLATION MOUNT 			BELL 	230 	230 	1182149	SW 										M/R GR BOX	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	351 				23009				ISOLATION MOUNT REMOVED TO TROUBLESHOOT VIBRATION. SEE MMIR# HEEA0005366 FOR ADDITIONAL ISOLATION MOUNT REPLACED.						1	G	7	2 	3U			NC	H9SW 					 
1995080400234	19950804	00234	SW 	1995	8	4	HEEA955366 	1	19950718	G	6330	222331618105	ISOLATION MOUNT 			BELL 	230 	230 	1182149	SW 										M/R GR BOX	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	300 				23009				RUBBER DETERIORATED AND CRACKED. SEE MMIR# HEEA0005365 FOR ADDITIONAL ISOLATION MOUNT REPLACED.						1	G	7	2 	3U			NC	H9SW 					 
1995080400235	19950804	00235	EU 	1995	8	4	HEEA955367 	1	19950718	G	5210	10523397	HINGE 			BOLKMS	105 	BO105S 	5626006	EU 										DOOR	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4302G	1681 				S853				HINGE BEARING WORN.						1	G	7	2 	3U				H3EU 					 
1995080400236	19950804	00236		1995	8	4	HEEA955368 	4	19950720	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008	4449 				36004				CVR INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995080400237	19950804	00237		1995	8	4	HEEA955369 	4	19950720	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	22342	2908 				760096				CVR DOES NOT TEST.						1	G	7	2 	3U				H1NE 					 
1995080400238	19950804	00238		1995	8	4	HEEA955370 	4	19950720	G	3453	453105004	LORAN 	ARNAV 	R501 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2743E					760155				LIGHTS WILL NOT DIM. SENT TO ARNAV SYSTEMS FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H1NE 					 
1995080400239	19950804	00239		1995	8	4	HEEA955371 	4	19950720	G	3442	MI5852013	INDICATOR 		P4001 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5426U					760167				IN TEST MODE IN MAP POSITION, SECOND BAND FROM TOP IS YELLOW AND BLUE. ALSO SCREEN IS RED AT NIGHT AND CANNOT BE ADJUST	ED. FOUND CRT BROKEN IN HALF AND BROKEN WIRE ON P1 CONNECTOR OF POWER SUPPLY.					1	G	7	2 	3U				H1NE 					 
1995080400240	19950804	00240	EU 	1995	8	4	HEEA955372 	1	19950720	G	7722	56265550011	INDICATOR 			AEROSP	AS355 	AS355F1 	8680810	EU 										ENG T4	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5786D	482 				5113				ERRATIC READING = LOW AT HIGH SIDE - HIGH AT LOW SIDE.						1	G	7	2 	3U				H11EU 					 
1995080400241	19950804	00241	EU 	1995	8	4	HEEA955373 	1	19950720	G	2436	GC1342221	REGULATOR 			AEROSP	AS355 	AS355F1 	8680810	EU 										RT GEN	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	57908					5091				TROUBLESHOOTING R/H GENERATOR TO COME ON LINE.						1	G	7	2 	3U				H11EU 					 
1995080400242	19950804	00242	SW 	1995	8	4	HEEA955374 	1	19950720	G	6330	206033554101	LINK ASSY 			BELL 	206 	206L1 	1182107	SW 										M/R XMSN MT	DELAMINATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50182					45242				BEARING DELAMINATED. REPLACED WITH SERVICEABLE LINK ASSEMBLY.						1	G	7	1 	3U				H2SW 					 
1995080400243	19950804	00243	SW 	1995	8	4	HEEA955375 	1	19950720	G	6230	206010336005	LINK ASSY 			BELL 	206 	206L1 	1182107	SW 										SWASHPLATE	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5017G					45228				SWASHPLATE DRIVE LINK ASSY. WORN. REPLACED WITH SERVICEABLE DRIVE LINK AND RETURNED TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995080400244	19950804	00244	SW 	1995	8	4	HEEA955376 	1	19950720	G	5302	206032308103S	FRAME 			BELL 	206 	206L3 	1182108	SW 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6610Y					51419				TAILBOOM RING CRACKED AT UPPER R/H ATTACHMENT POINT. REMOVED CRACKED RING AND REPLACED WITH SERVICEABLE RING AND RETURNE	D AIRCRAFT TO SERVICE.					1	G	7	1 	3U				H2SW 					 
1995080400245	19950804	00245	SW 	1995	8	4	HEEA955377 	1	19950720	G	2911	212076007003	ACCUMULATOR 			BELL 	412 	412 	1182202	SW 										HYD	LEAKING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2014K	6258 				33020				LEAKING FROM WEEP HOLE. REPLACED WITH SERVICEABLE ACCUMULATOR.						1	G	7	2 	4U				H4SW 					 
1995080400246	19950804	00246	GL 	1995	8	4	HEEA955378 	2	19950720	G	7532	23053176	BLEED VALVE 			AEROSP	AS355 	AS355F1 	8680810	EU 	ALLSN 	250C 	250C20F 	03013	GL 					ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y	6481 				5141				#1 ENGINE COMPRESSOR SURGES WITH THROTTLE APPLICATION. REPLACED BLEED VALVE AND RETURNED TO SERVICE.						1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1995080400247	19950804	00247	EU 	1995	8	4	HEEA955379 	1	19950720	G	6220	117775P	BALLJOINT 			AEROSP	AS355 	AS355F2 	8680812	EU 										STARFLEX	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6040U					5474				TEFLON WORN. REPLACED WITH SERVICEABLE BALL JOINT.						1	G	7	2 	3U				H11EU 					 
1995080400248	19950804	00248	EU 	1995	8	4	HEEA955380 	1	19950720	G	6420	350A33211905	YOKE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R HUB	BEARING LOOSE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951					2771				BEARING LOOSE IN BORE OF YOKE. REPLACED WITH SERVICEABLE T/R YOKE AND RETURNED AIRCRAFT TO SERVICE.						1	G	7	1 	3U				H9EU 					 
1995080400249	19950804	00249	EU 	1995	8	4	HEEA955381 	1	19950720	G	6420	350A33211904	HUB 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	BEARING FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951					2771				LAMINATED HINGE BEARING FAILED, SEPARATED 360 DEGREES AROUND. REMOVED AND REPLACED T/R YOKE ASSY WITH SERVICEABLE PART.						1	G	7	1 	3U				H9EU 					 
1995080400250	19950804	00250	EU 	1995	8	4	HEEA955382 	1	19950720	G	2435	150SG122Q	GENERATOR 			SNIAS 	350 	AS350B2 	8680813	EU 										START/GEN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	469 				2771				HAS HEADSET NOISE EVEN WITH CAPACITOR INSTALLED. REPLACED STARTER GENERATOR AND RETURNED AIRCRAFT TO SERVICE.						1	G	7	1 	3U				H9EU 					 
1995080400251	19950804	00251	EU 	1995	8	4	HEEA955383 	1	19950720	G	6700	350A25135003	CYLINDER 			SNIAS 	350 	AS350B2 	8680813	EU 										CONTROL LOCK	PIN SHEARED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951					2771				STUD PIN THAT CONTROL ROD CONNECTS TO ON LOCK ASSY SHEARED FROM LOCK ASSY. REPLACED WITH SERVICEABLE PART FROM STOCK.						1	G	7	1 	3U				H9EU 					 
1995080400252	19950804	00252	EU 	1995	8	4	HEEA955384 	1	19950720	G	3340	4580	LAMP 			SNIAS 	350 	AS350B2 	8680813	EU 										LANDING LIGHT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951					2771				BULB BURNT. REPLACED LANDING LIGHT BULB DUE TO BEING BURNT.						1	G	7	1 	3U				H9EU 					 
1995080400253	19950804	00253	EU 	1995	8	4	HEEA955385 	1	19950720	G	6720	350A33214501	ROD BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1489 				2771				BEARING WORN CAUSING HIGH FREQUENCY.						1	G	7	1 	3U				H9EU 					 
1995080400254	19950804	00254		1995	8	4	HEEA955386 	4	19950720	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3911L	2249 				33023				CVR INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995080400255	19950804	00255		1995	8	4	HEEA955391 	4	19950720	G	2312	064105430	TRANSCEIVER 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5014V					45217				DIMMER IS INOPERATIVE AND CHANNEL NUMBER DOES NOT APPEAR ON DISPLAY WHEN CHANNEL BUTTON IS PRESSED.						1	G	7	1 	3U				H2SW 					 
1995080400256	19950804	00256		1995	8	4	HEEA955393 	4	19950720	G	3453	4530103	LORAN 		ARNAV21 	BELL 	206 	206B3 	1181506	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22751					3627				ENTER BUTTON INTERMITTENT NUMERAL BACKLIGHT INOP ON 4 DIGITS. DOESN'T LOCK ON. SENT TO ARNAV SYSTEMS FOR INSPECTION AND	 REPAIR.					1	G	7	1 	3U				H2SW 					 
1995080400257	19950804	00257	EU 	1995	8	4	HEEA955394 	1	19950720	G	6240	10594575	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	WONT CALIB 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	624MB					S751				WILL NOT CALIBRATE.						1	G	7	2 	3U				H3EU 					 
1995080400258	19950804	00258	EU 	1995	8	4	HEEA955395 	1	19950720	G	6240	10594564	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	WONT CALIB 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	624MB					S751				INDICATOR WILL NOT CALIBRATE.						1	G	7	2 	3U				H3EU 					 
1995080400259	19950804	00259		1995	8	4	HEEA955396 	4	19950720	G	3444	066305401	INDICATOR 		KI250 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8590X					51494				LOOSE NUT IN WINDOW. FOUND BEZEL TO BE BROKEN. REPLACED BEZEL. REPAIRED. UNIT HAS NO SELF-TEST OR ALTITUDE READINGS. 	 REPLACED I301 INTERGRATED CIRCUIT. FOUND AND REPAIRED BROKEN "GROUND" FOIL. REPAIRED. PERFORMED COMPLETE ALIGNMENT. 	 BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995080400260	19950804	00260		1995	8	4	HEEA955397 	4	19950720	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4180F					51469				BENCH CHECK NEEDED. INSPECTED AND TESTED. REPLACED CRACKED FACEPLATE. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT.	 REPAIRED. REPLACED DETERIORATED RESISTOR R477. INSTALLED HEAT-SINK BEHIND TRANSISTOR Q415. FOUND UNIT TO HAVE WEAK 	POWER OUT. TRIED ADJUSTINGPOWER OUT TO SPECS. REPLACED CAVITY TUBE V101 AND REPAIRED PROBLEM. UNIT HAS INTERMITTENT R	ECEIVE. REPLACED INTEGRATED CIRCUIT I405. REPAIRED PROBLEM. BENCH CHECK GOOD.			1	G	7	1 	3U				H2SW 					 
1995080400261	19950804	00261		1995	8	4	HEEA955398 	4	19950720	G	3454	071143100	ANTENNA 		KA83 	BELL 	206 	206L3 	1182108	SW 										VOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8592X	121 				51508				ANTENNA FAULTY. WILL NOT RECEIVE STATIONS.						1	G	7	1 	3U				H2SW 					 
1995080400262	19950804	00262		1995	8	4	HEEA955399 	4	19950720	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				#1 NEEDLE WILL NOT MOVE.						1	G	7	2 	4U				H4SW 					 
1995080400263	19950804	00263		1995	8	4	HEEA955400 	4	19950720	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3116P					51530				INOPERATIVE. WILL NOT GIVE OR RECEIVE. FOUND UNIT DID NOT TRANSMIT. REPLACED CAVITY OSCILLATOR V101. REPAIRED. REPLA	CED DETERIORATED RESISTOR R477. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. REPAIRED. INSTALLED HEATSINK BEHIND 	TRANSISTOR Q415 AND ALIGNED RECEIVER AND ADJUSTEDFREQUENCY TO SPECS. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995080400264	19950804	00264		1995	8	4	HEEA955401 	4	19950720	G	2312	064105430	TRANSCEIVER 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5007Q					45187				LED DISPLAY INOPERATIVE. REPLACED DS901. STILL HAD INTERMITTENT DISPLAY WHEN BOTTOM OF UNIT PRESSED ON. FOUND THAT MOV	EMENT OF Q507 TRANSISTOR CAUSED DISPLAY TO FLICKER. RESOLDERED Q507 TRANSISTOR AND REPAIRED PROBLEM. UNIT BENCH CHECK 	GOOD.				1	G	7	1 	3U				H2SW 					 
1995080400265	19950804	00265		1995	8	4	HEEA955402 	4	19950720	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	31073					51519				CRACKED FACEPLATE. REPLACED FACEPLATE. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. INSTALLED HEATSINK BEHIND TRAN	SISTOR Q415 AS PER KING SERVICE BULLETIN KT76A-6. REPLACED DETERIORATED RESISTOR R477. FOUND UNIT TO HAVE WEAK POWER O	UT. REPLACED CAVITYOSCILLATOR V101. REPAIRED. ADJUSTED FREQUENCY. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995080400266	19950804	00266	NE 	1995	8	4	HEEA955403 	1	19950720	G	5610	7620710002144	WINDOW 			SKRSKY	S76 	S76A 	8143006	NE 										PILOT DOOR	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	1545X					760050				OPENABLE WINDOW NOT CUT OUT.						1	G	7	2 	3U				H1NE 					 
1995080400267	19950804	00267	EU 	1995	8	4	HEEA955404 	1	19950720	G	2436	GC1342221	REGULATOR 			AEROSP	AS355 	AS355F1 	8680810	EU 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	57908					5091				COULD NOT ADJUST VOLTAGE.						1	G	7	2 	3U				H11EU 					 
1995080400461	19950804	00461	GL 	1995	8	4	HEEA955405 	2	19950724	G	7250	6895801	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	406EH	877 			CAT70498	45183	CAE860655			ENGINE REMOVED DUE TO LOW POWER. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON ALL BLADES	. SCRAPPED 1ST STAGE WHEEL.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995080400462	19950804	00462	GL 	1995	8	4	HEEA955406 	2	19950724	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3071K	1055 			CAT33837	S859	CAE836510			ENGINE REMOVED DUE TO 1ST STAGE WHEEL RETIREMENT DUE. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULF	IDATION ON ALL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995080400463	19950804	00463		1995	8	4	HEEA955407 	4	19950724	G	2370	9806019001	CVR 			BELL 	212 	212 	1181420	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	27805	2303 				31106				CVR WILL NOT TEST.						1	G	7	1 	4U				H4SW 					 
1995080400464	19950804	00464		1995	8	4	HEEA955408 	4	19950724	G	3444	7001840913	TRANSCEIVER 			SKRSKY	S76 	S76A 	8143006	NE 										RADIO ALT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4253S	507 				760035				RADIO ALT RT UNIT HAS NO OUTPUT ON J1-W.						1	G	7	2 	3U				H1NE 					 
1995080400465	19950804	00465		1995	8	4	HEEA955409 	4	19950724	G	3457	0845000000	SKYNAV 5000 																	COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										PWR BUTTON IS BAD. SENT TO MAGELLAN SYSTEMS FOR WARRANTY EXCHANGE. TIME SINCE REPAIR 0:00.																			 
1995080400466	19950804	00466		1995	8	4	HEEA955410 	4	19950724	G	3457	0845000000	SKYNAV 5000 																	COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										POWER BUTTON HAS NO DETENT AND IS INTERMITTENT. SENT TO MAGELLAN SYSTEMS FOR WARRANTY EXCHANGE. TIME SINCE REPAIR 0:00.																			 
1995080400467	19950804	00467	SW 	1995	8	4	HEEA955413 	1	19950724	G	7722	206075680107	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	MALFUNCTION 	E			HEEA	K				NONE 				N			FALSE WARNING 			NR	NOT REPORTED 	1			SW	03	2135V					45657				TOT INDICATOR OVERTEMP LIGHT COMES ON TOO SOON.						1	G	7	1 	3U				H2SW 					 
1995080400468	19950804	00468	EU 	1995	8	4	HEEA955414 	1	19950724	G	6240	10594575	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	624MB					S751				READS LOW OUT OF TOLERANCE.						1	G	7	2 	3U				H3EU 					 
1995080400469	19950804	00469	EU 	1995	8	4	HEEA955415 	1	19950724	G	6240	10594565	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	OUT OF TOLERANCE	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	624MB					S751				INDICATOR READS LOW OUT OF TOLERANCE.						1	G	7	2 	3U				H3EU 					 
1995080400470	19950804	00470	EU 	1995	8	4	HEEA955416 	1	19950724	G	7714	1179405603	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										ENG N1	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911TL	16 				7198				WITH POWER APPLIED, NEEDLE WON'T RETURN TO ZERO.						1	G	7	2 	3U				H13EU 					 
1995080400471	19950804	00471	EU 	1995	8	4	HEEA955417 	1	19950724	G	7931	6607A2114	SWITCH 			BOLKMS	105 	BO105LSA3 	5626020	EU 										OIL PRESS WARN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	202LF	1803 				2014				OIL PRESS WARN CAUSES LIGHT TO COME ON TOO SOON.						1	G	7	2 	3U				H3AU 					 
1995080400472	19950804	00472	SW 	1995	8	4	HEEA955418 	1	19950724	G	7722	206375006101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		311 								INDICATOR READING 10 DEGREES HIGH AFTER ONE HOUR OF OPERATION.						1	G	7	1 	3U				H2SW 					 
1995080400473	19950804	00473	EU 	1995	8	4	HEEA955419 	1	19950724	G	6240	10594575	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7136J	4198 				S830				TRANSMITTER CAUSES INDICATOR TO READ LOW.						1	G	7	2 	3U				H3EU 					 
1995080400474	19950804	00474	EU 	1995	8	4	HEEA955420 	1	19950724	G	6240	10594564	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7136J	4198 				S830				TRANSMITTER CAUSES INDICATOR TO READ LOW.						1	G	7	2 	3U				H3EU 					 
1995080400475	19950804	00475	SW 	1995	8	4	HEEA955422 	1	19950724	G	3340	A490A	POWER SUPPLY 	WHELEN 		BELL 	206 	206L1 	1182107	SW 										STROBE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2250U					45754				POWER SUPPLY NO OUTPUT. TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW 					 
1995080400476	19950804	00476	SW 	1995	8	4	HEEA955423 	1	19950724	G	2824	L88010501	VALVE 			BELL 	412 	412 	1182202	SW 										FUEL SYS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				VALVE INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995080400477	19950804	00477		1995	8	4	HEEA955424 	4	19950724	G	3421	206075607103	GYRO 			BELL 	206 	206L3 	1182108	SW 										COCKPIT ATTITUDE	PRECESSES 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4180F					51469				GYRO PRECESSES IN PITCH AND ROLL.						1	G	7	1 	3U				H2SW 					 
1995080400478	19950804	00478		1995	8	4	HEEA955425 	4	19950724	G	3421	206075607103	GYRO 			BELL 	206 	206L3 	1182108	SW 										COCKPIT ATTITUDE	PRECESSES 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4180F					51469				GYRO PRECESSES AND PITCH ROLL ERECTION RATES SLOW.						1	G	7	1 	3U				H2SW 					 
1995080400479	19950804	00479		1995	8	4	HEEA955426 	4	19950724	G	3422	102005403	GYRO 			BELL 	206 	206L3 	1182108	SW 										COCKPIT HORIZ	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4180F					51469				PRECESSING IN ROLL AND PITCH AND ROLL ERECTION RATES SLOW.						1	G	7	1 	3U				H2SW 					 
1995080400480	19950804	00480	NE 	1995	8	4	HEEA955427 	1	19950724	G	7810	7630507003044	EJECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										EXHAUST	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5435V					760158				EJECTOR CRACKED ON BOTTOM FLANGE.						1	G	7	2 	3U				H1NE 					 
1995080400481	19950804	00481	GL 	1995	8	4	HEEA955428 	2	19950724	G	7261	174000103	FILTER ASSEMBLY 			BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20 	03013	GL 					OIL SYS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2271V	970 				3615				FILTER ASSY INOPERATIVE.						1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995080400482	19950804	00482	SW 	1995	8	4	HEEA955429 	1	19950724	G	2913	214076033101	PUMP 			BELL 	214 	214ST 	1182106	SW 										HYD	SEAL LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	03	3897N					28106				DRIVE SPLINE SEAL LEAKING.						2	G	7	2 	4U				H10SW 					 
1995080400483	19950804	00483	GL 	1995	8	4	HEEA955430 	3	19950724	G	6111		BLADE 			BEECH 	200 	200CBEECH 	1152926	CE 						HARTZL	HCB3T	HCB3TN3 	GL 	PROP	TIP DAMAGE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	500PH	2638 				BL29		BU12029		DAMAGE TO ONE BLADE TIP. TSO DUE 9-97.						1	L	7	2 	4T				A24CE 		6	C	P15EA	 
1995091500236	19950915	00236	EU 	1995	9	15	HEEA955432 	1	19950724	G	2822	2C273	CARTRIDGE 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL BOOST	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	86CH					S557				FUEL CARTRIDGE CAUSED CIRCUIT BREAKER TO EXTEND (POP).						1	G	7	2 	3U				H3EU 					 
1995080400484	19950804	00484	SW 	1995	8	4	HEEA955433 	1	19950724	G	7714	412075010109	INDICATOR 			BELL 	412 	412 	1182202	SW 										TRIPLE TACH	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				#1 AND #2 NEEDLES HAVE A 3% SPLIT AND ALL NEEDLES INTERMITTENTLY STICK. ALSO UNIT HAS LOOSE PARTS INSIDE.						1	G	7	2 	4U				H4SW 					 
1995080400485	19950804	00485	NE 	1995	8	4	HEEA955434 	1	19950724	G	6220	7610608000049	DAMPER 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	707AE					760276				DAMPER HAS WEAR GROOVES ON INNER CYLINDER.						1	G	7	2 	3U				H1NE 					 
1995080400486	19950804	00486		1995	8	4	HEEA955435 	4	19950724	G	2562	ELT910	ELT 	NARCO 		SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	350BZ	3354 				2653				ELT CAME ON IN FLIGHT. TIME SINCE REPAIR 359:45.						1	G	7	1 	3U				H9EU 					 
1995080400487	19950804	00487		1995	8	4	HEEA955436 	4	19950724	G	3422	5208100001	GYRO 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT DG	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	105WK					S812				GYRO WILL NOT RUN UP, WILL NOT BECOME VALID.						1	G	7	2 	3U				H3EU 					 
1995080400488	19950804	00488	SW 	1995	8	4	HEEA955437 	1	19950724	G	6330	206033506101	RESTRAINT 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3207Q					50540				BEARINGS IN RESTRAINT WERE WORN AND THE BEARING ON R/H SIDE OF RESTRAINT WAS UNSTAKED.						1	G	7	1 	3U				H2SW 					 
1995080400489	19950804	00489	EU 	1995	8	4	HEEA955438 	1	19950724	G	7334	BSE206150G3	TRANSDUCER 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	91070					S145				READS HIGH OUT OF TOLERANCE.						1	G	7	2 	3U				H3EU 					 
1995080400490	19950804	00490	EU 	1995	8	4	HEEA955439 	1	19950724	G	7722	50061036	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT EGT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8197X					S808				INDICATOR 30 DEGREES FRICTIONARY AT 600 DEGREES.						1	G	7	2 	3U				H3EU 					 
1995080400491	19950804	00491	NE 	1995	8	4	HEEA955440 	1	19950724	G	7810	7630507003044	EJECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										EXHAUST	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	706AE					760275				EJECTOR CRACKED.						1	G	7	2 	3U				H1NE 					 
1995080400492	19950804	00492		1995	8	4	HEEA955441 	4	19950724	G	2210	7000299901	CONTROL 			BELL 	412 	412 	1182202	SW 										AUTOPILOT	FAILS TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	2148K					36001				AUTO PILOT CONTROL FAILS TEST 4.2 ON SST, LED #2 IS OFF.						1	G	7	2 	4U				H4SW 					 
1995080400493	19950804	00493		1995	8	4	HEEA955442 	4	19950724	G	2200	2593996333	TARSYN 333 			BELL 	412 	412 	1182202	SW 										AUTOFLIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3911L					33023				VG WILL NOT BECOME VALID. TIME SINCE REPAIR 529:50.						1	G	7	2 	4U				H4SW 					 
1995080400494	19950804	00494		1995	8	4	HEEA955443 	4	19950724	G	3416	214175278101	ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT	CASE LEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				EXCESSIVE CASE LEAK.						1	G	7	2 	4U				H4SW 					 
1995080400495	19950804	00495		1995	8	4	HEEA955444 	4	19950724	G	3416	24929414	ALTIMETER 			BEECH 	200 	200CBEECH 	1152926	CE 										COCKPIT ENCODE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	39PH					BL3				ENCODER HAS NO VALID OUTPUT. TIME SINCE REPAIR 187:40.						1	L	7	2 	4T				A24CE 					 
1995080400496	19950804	00496	SW 	1995	8	4	HEEA955445 	1	19950724	G	5530	206020113163	FIN ASSY 			BELL 	206 	206L1 	1182107	SW 										STAB	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										NUT PLATE MISALIGN WITH FAIRING 1/4" TOO FAR FORWARD. RING ASSY IS NOT LINED UP WITH L ANGLE, ABOUT 1/8" OUT TOO FAR. 	TIME SINCE REPAIR 0:00.					1	G	7	1 	3U				H2SW 					 
1995080400497	19950804	00497	NE 	1995	8	4	HEEA955446 	2	19950724	G	7510	5044T08P05	VALVE 			BELL 	214 	214ST 	1182106	SW 	GE 	CT7TS 	CT72A 	30030	NE 					ENG ANTI ICE	FAULTY 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N					28106				ENGINE FLUCTUATES AT HIGH POWER SETTING. REPLACEMENT FROM GE CONSIGNMENT KIT S/N COM01447. ANTI ICE VALVE FAULTY.						2	G	7	2 	4U	4	U		H10SW 	E8NE				 
1995080400498	19950804	00498	SW 	1995	8	4	HEEA955447 	1	19950724	G	6322	6038T59P02	BLOWER ASSY 			BELL 	214 	214ST 	1182106	SW 										COOLING	SHAFT SHEARED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N					28106				BLOWER ASSY HAS SHEARED SHAFT.						2	G	7	2 	4U				H10SW 					 
1995080400499	19950804	00499	SW 	1995	8	4	HEEA955448 	1	19950724	G	6720	7001484	ACTUATOR 			BELL 	412 	412 	1182202	SW 										YAW CONTROL	STUCK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				YAW CONTROL STUCK IN RIGHT POSITION.						1	G	7	2 	4U				H4SW 					 
1995080400500	19950804	00500	SW 	1995	8	4	HEEA955450 	1	19950724	G	6310	406040541101	NUT 		406040500113	BELL 	206 	206L 	1181522	SW 										FREEWHEEL	STRIPPED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7077B	2973 			A1705	52037				STRIPPED SPLINE TEETH WHERE TOOL ENGAGES. REPLACED WITH SERVICEABLE NUT.						1	G	7	1 	3U				H2SW 					 
1995080400501	19950804	00501	SW 	1995	8	4	HEEA955466 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5745N	498 			CS6044CS604	45489				INBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS6948, T.T. 1152:30. ALSO REMOVED 2 EACH SLEEVE 206-010-733-003. 	PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400502	19950804	00502	SW 	1995	8	4	HEEA955467 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5745N	1153 			CS6044CS604	45489				OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS6948, T.T. 1152:30. ALSO REMOVED 2 EACH SLEEVE 206-010-733-003.	 PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400503	19950804	00503	SW 	1995	8	4	HEEA955468 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2772A	961 			CS4403CS436	45311				INBOARD AND OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS5784, T.T. 2090:15. ALSO REMOVED 4 EACH SLEEVES 206	-010-733-003. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400504	19950804	00504	SW 	1995	8	4	HEEA955469 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2253E	1116 			CS2425CS284	45758				INBOARD AND OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS5787, T.T. 1116:05. ALSO REMOVED 4 EACH SLEEVES 206	-010-733-003. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400505	19950804	00505	SW 	1995	8	4	HEEA955470 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2135V	509 			CS6801CS672	45657				INBOARD AND OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS7023, T.T. 509:40. ALSO REMOVED 4 EACH SLEEVES 206	-010-733-003. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400506	19950804	00506	SW 	1995	8	4	HEEA955471 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1078G	331 			CS3821CS405	45398				INBOARD AND OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS6342, T.T. 1868:40. ALSO REMOVED 4 EACH SLEEVES P/N	 206-010-733-003. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400507	19950804	00507	SW 	1995	8	4	HEEA955472 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1078D	728 			CS4711CS474	45397				INBOARD AND OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS4999, T.T. 3206:50. ALSO REMOVED 4 EACH SLEEVES P/N	 206-010-733-003. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400508	19950804	00508	SW 	1995	8	4	HEEA955473 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5000K	417 			CS6056CS604	45167				INBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS5139, T.T. 3119:20. ALSO REMOVED 2 EACH SLEEVES P/N 206-010-733-	003. PARTS SCRAPPED LOCALLY. 87.					1	G	7	1 	3U				H2SW 					 
1995080400509	19950804	00509	SW 	1995	8	4	HEEA955474 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5000K	688 			CS6056CS604	45167				OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS5139, T.T. 3119:20. ALSO REMOVED 2 EACH SLEEVES P/N 206-010-733	-003. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400510	19950804	00510	SW 	1995	8	4	HEEA955475 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2124Z	1310 			CS6041CS604	45646				INBOARD AND OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS6932, T.T. 1310:25. ALSO REMOVED 4 EACH SLEEVES P/N	 206-010-733-003. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400511	19950804	00511	SW 	1995	8	4	HEEA955476 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748Q	1233 			CS5505	45499				INBOARD BEARING CRACKED. REMOVED FROM T/R HUB S/N A4984, T.T. 3723:15. ALSO REMOVED 1 EACH SLEEVES P/N 206-010-733-003	. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400512	19950804	00512	SW 	1995	8	4	HEEA955477 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748Q	949 			CS5643	45499				INBOARD BEARING CRACKED. REMOVED FROM T/R HUB S/N A4984, T.T. 3723:15. ALSO REMOVED 1 EACH SLEEVES P/N 206-010-733-003	. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400513	19950804	00513	SW 	1995	8	4	HEEA955478 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748Q	1233 			CS5505CS564	45499				OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N A4984, T.T. 3723:15. ALSO REMOVED 2 EACH SLEEVES P/N 206-010-733-0	03. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400514	19950804	00514	SW 	1995	8	4	HEEA955479 	1	19950728	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206L1 	1182107	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	21240	1453 			CS4520CS412	45647				INBOARD OUTBOARD BEARINGS CRACKED. REMOVED FROM T/R HUB S/N AFS6082, T.T. 1453:05. ALSO REMOVED 4 EACH SLEEVES P/N 206	-010-733-003. PARTS SCRAPPED LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995080400515	19950804	00515	GL 	1995	8	4	HEEA955480 	2	19950728	G	7210	6876925A	TUBE ASSY 		23001938 	AEROSP	AS355 	AS355F1 	8680810	EU 	ALLSN 	250C 	250C20F 	03013	GL 					GEAR BOX	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5793Y	7930 			CAG40058	5141	CAE840058			ENGINE REMOVED DUE TO METAL IN OIL. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: BELOW CEB1307 REQUIREMENTS O	N TUBE ASSEMBLY. INSTALLED NEW TUBE ASSY. PART RETURNED TO ALLISON FOR CEB1307. REFERENCE: AFA#24405A (PART IS OUT O	F CALENDAR DATE AND TIME LIMITS)				1	G	7	2 	3U	3	U		H11EU 	E4CE				 
1995080400516	19950804	00516	GL 	1995	8	4	HEEA955481 	2	19950728	G	7230	23056634	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1546K	826 			CAC90436	760082	CAE890431S			ENGINE REMOVED DUE TO TURBINE OVERHAUL AND 1750 HOUR INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS, NOTED THE FOLLOWI	NG: STEPWEAR IN EXCESS OF MAINTENANCE MANUAL LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SP	UR ADAPTER GEARSHAFT.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995080400517	19950804	00517	GL 	1995	8	4	HEEA955482 	2	19950728	G	7230	23032345	N1 COUPLING 		23031899 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					COUPLING SPLINES	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5745S	467 			CAT70036	45491	CAE860022			ENGINE REMOVED DUE TO TURBINE OVERHAUL AND 1750 HOUR INSPECTION. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 	 STEPWEAR IN EXCESS OF MAINTENANCE MANUAL LIMITS ON N1 COUPLING FWD. INTERNAL SPLINES. INSTALLED NEW N1 COUPLING.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995080400518	19950804	00518	GL 	1995	8	4	HEEA955483 	2	19950728	G	7250	23004223	WHEEL 		23031899 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					2ND STAGE	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5745S				CAT70036	45491	CAE860022			UPON INSPECTION OF NEW NEVER INSTALLED #2 WHEEL NOTED THE FOLLOWING: RECEIVED OVERMACHINED PER O/H SPECS ON #2 WHEEL SP	LINES. INSTALLED NEW #2 WHEEL.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995081100260	19950811	00260	SW 	1995	8	11	HEEA955489 	1	19950731	G	2150	2730502	VALVE 			BELL 	230 	230 	1182149	SW 										AIR COND	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2224 				23009				ECU CIRCUIT BREAKER POPS.						1	G	7	2 	3U			NC	H9SW 					 
1995081100261	19950811	00261	SW 	1995	8	11	HEEA955490 	1	19950731	G	2436	222375060115	REGULATOR 			BELL 	230 	230 	1182149	SW 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				N			FALSE WARNING 			NR	NOT REPORTED 	1			SW	03	230UN	101 				23009				GENERATOR LIGHT STAYS ON WHILE GENERATOR IS OPERATING.						1	G	7	2 	3U			NC	H9SW 					 
1995081100262	19950811	00262	SW 	1995	8	11	HEEA955491 	1	19950731	G	6700	222382001105	ACTUATOR ASSY 			BELL 	230 	230 	1182149	SW 										FLIGHT CONTROL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	03	230UN	2245 				23009				HYDRAULIC FLUID LEAKING FROM PISTON.						1	G	7	2 	3U			NC	H9SW 					 
1995081100263	19950811	00263	SW 	1995	8	11	HEEA955492 	1	19950731	G	3213	222036030103	SKID SHOE 			BELL 	230 	230 	1182149	SW 										LT AFT	WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2230 				23009				L/H AFT SKID SHOE WORN.						1	G	7	2 	3U			NC	H9SW 					 
1995081100264	19950811	00264	GL 	1995	8	11	HEEA955493 	2	19950802	G	7230	23056634	GEARSHAFT 		23033191 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					SPUR ADAPTER	STEP WEAR 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	5737T	508 			CAC70569	45454	CAE860697			ENGINE REMOVED DUE TO HIGH COMPRESSOR VIBRATIONS. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEPWEAR BE	YOND MAINTENANCE MANUAL SPECS ON SPURGEAR FWD AND AFT SPLINES. INSTALLED NEW SPURGEAR. PART HELD AT EAI FOR WARRANTY AP	PLICATION. REFERENCE: AFA#24409A.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995081100265	19950811	00265	SW 	1995	8	11	HEEA955494 	1	19950802	G	2841	214175257105	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										FUEL QTY	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				INDICATOR DIGITS GO BLANK; INTERMITTENT.						2	G	7	2 	4U				H10SW 					 
1995081100266	19950811	00266	SW 	1995	8	11	HEEA955495 	1	19950802	G	6710	206062721109	ACTUATOR 			BELL 	206 	206L 	1181522	SW 										M/R	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7077F	402 				52038				ACTUATOR DOES NOT WORK IN EITHER DIRECTION. INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND MOISTURE IN UNIT. SHAFT WAS	 PITTED AND ARMATURE WAS BURNT. REPAIRED AS NECESSARY.					1	G	7	1 	3U				H2SW 					 
1995081100267	19950811	00267	SW 	1995	8	11	HEEA955496 	1	19950802	G	6200	222015522101	SPLICE COVER 			BELL 	230 	230 	1182149	SW 										M/R	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2245 				23009				SPLIT AND DETERIORATED.						1	G	7	2 	3U			NC	H9SW 					 
1995081100268	19950811	00268	SW 	1995	8	11	HEEA955497 	1	19950802	G	5210	222031375101	PIVOT SPRING 			BELL 	230 	230 	1182149	SW 										RT AFT DOOR	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2230 				23009				R/H AFT DOOR PIVOT PIN WORN.						1	G	7	2 	3U			NC	H9SW 					 
1995081100269	19950811	00269	SW 	1995	8	11	HEEA955498 	1	19950802	G	7110	NAS1375A08SB036	DUCT 			BELL 	230 	230 	1182149	SW 										RT ENG COWL	TORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	969 				23009				R/H ENG. COWL DUCT TORN. SCRAPPED IN FIELD.						1	G	7	2 	3U			NC	H9SW 					 
1995081100270	19950811	00270	SW 	1995	8	11	HEEA955499 	1	19950802	G	6320	214040002119FM	TRANSMISSION 			BELL 	214 	214ST 	1182106	SW 										M/R GR BOX	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N	5598 				28106				METAL IN OIL. METAL ON PLANETARY CHIP PLUG AND IN INTERNAL FILTER. POWER BY THE HOUR COMPONENT.						2	G	7	2 	4U				H10SW 					 
1995081100271	19950811	00271		1995	8	11	HEEA955500 	4	19950802	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31821					51076				DOES NOT REPORT. VERIFIED UNIT TO HAVE WEAK POWER OUT. REPLACED CAVITY OSCILLATOR V101. REPAIRED. REPLACED DETERIORAT	ED RESISTOR R477. INSTALLED HEATSINK BEHIND TRANSISTOR Q415 AS PER KING SERVICE BULLETIN KT76A-6. REPLACED PHOTOCELL V	301 DUE TO WEAK REPLYLIGHT. REPLACED CRACKED FACEPLATE. ADJUSTED FREQUENCY. CLEANED CONTACTS ON WAFER SWITCHES. BENCH	 CHECK GOOD.			1	G	7	1 	3U				H2SW 					 
1995081100272	19950811	00272		1995	8	11	HEEA955501 	4	19950802	G	3444	066104800	ALTIMETER 		KRA405 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT RAD ALT	DEFECTIVE 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	3122G					760232				NO SELF TEST. REPLACED I408, I409 AND I410 INTEGRATED CIRCUIT. REPAIRED.						1	G	7	2 	3U				H1NE 					 
1995081100273	19950811	00273		1995	8	11	HEEA955502 	4	19950802	G	3454	066106700	RECEIVER 		KN53 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7062X					S793				BAD DISPLAY. REPLACED DISPLAY P/N 037-00060-0001, REPAIRED. APPLIED HUMISEAL TO ALL HEADERS FOR HEADER MODIFICAITON. B	ENCH CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995081100274	19950811	00274		1995	8	11	HEEA955503 	4	19950802	G	3457	0110005400	GPS 150 			BELL 	206 	206B 	1181511	SW 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	104PH					3622				UNIT GOES FROM SELF-TEST TO OPERATE TO SELF-TEST, ETC. CONTINUOUSLY. SENT TO GARMIN INTERNATIONAL FOR WARRANTY REPAIR.						1	G	7	1 	3U				H2SW 					 
1995081100275	19950811	00275		1995	8	11	HEEA955504 	4	19950802	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R	1608 				36007				CVR TEST LIGHT INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995081100276	19950811	00276		1995	8	11	HEEA955505 	4	19950802	G	3416	5035P2P13	ENCODER 			BELL 	230 	230 	1182149	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN					23009				ENCODER IS 130 FEET OFF AT 15,000 FEET.						1	G	7	2 	3U			NC	H9SW 					 
1995081100277	19950811	00277	NE 	1995	8	11	HEEA955506 	1	19950802	G	5610	S761014	WINDOW 			SKRSKY	S76 	S76A 	8143006	NE 										RT AIRFRAME	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545X					760050				THE R/H WINDOW WHEN INSTALLED, CRACKED IN THE UPPER R/H CORNER. LOWER CORNER OF THE WINDOW EXTENDS 3 1/2" WHEN LAYED ON	 THE AIRFRAME. THIS DISTANCE CREATES EXCESSIVE STRESS DURING INSTALLATION.					1	G	7	2 	3U				H1NE 					 
1995081100278	19950811	00278	EU 	1995	8	11	HEEA955507 	1	19950802	G	2436	51565000R	REGULATOR 			BOLKMS	105 	BO105S 	5626006	EU 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	54197					S805				GENERATOR WILL NOT COME ON LINE. SCRAPPED VOLTAGE REGULATOR AT PHI.						1	G	7	2 	3U				H3EU 					 
1995081100279	19950811	00279	EU 	1995	8	11	HEEA955508 	1	19950802	G	2436	51565000R	REGULATOR 			BOLKMS	105 	BO105S 	5626006	EU 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	54197					S805				GENERATOR WILL NOT COME ON LINE. REPLACED Q4 TRANSISTOR P/N 03-0044-28. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995081100280	19950811	00280		1995	8	11	HEEA955509 	4	19950802	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2272J					3620				BENCH CHECK NEEDED. INSPECTED UNIT. REPLACED DETERIORATED RESISTOR R477. REPLACED CRACKED FACEPLATE. REPLACED PHOTOCE	LL V301 DUE TO WEAK REPLY LIGHT. REPAIRED. ALIGNED RECEIVER AND PULSE WIDTH TO SPECS. CLEANED CONTACTS ON ALL WAFER S	WITCHES. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995081100281	19950811	00281		1995	8	11	HEEA955510 	4	19950802	G	2312	4000106010	CONTROL UNIT 		C10 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911BR					S719				LOAD BUTTON STICKING. REPLACED S6 SWITCH. REPAIRED. THUMBWHEEL INTERMITTENT. REPLACED S1 THUMBWHEEL. REPAIRED.						1	G	7	2 	3U				H3EU 					 
1995081100282	19950811	00282	EU 	1995	8	11	HEEA955511 	1	19950802	G	2436	51565000R	REGULATOR 			BOLKMS	105 	BO105S 	5626006	EU 										DC SYS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	724MB					S756				PEGS VOLTAGE METER INDICATOR TO TOP END. FOUND Q4 TRANSISTOR BAD AND CIRCUIT BOARD BURNT AROUND R65 RESISTOR. SCRAPPED 	VOLTAGE REGULATOR.					1	G	7	2 	3U				H3EU 					 
1995081100283	19950811	00283		1995	8	11	HEEA955513 	4	19950802	G	3457	0845000000	SKYNAV 5000 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT GPS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7062X					S793				DOES NOT PICK UP SIGNALS. FOUND UNIT TO INTERMITTENTLY PICK UP SIGNALS. ALSO UNIT DROPS OFF LOCK SEVERAL TIMES. BACKLI	GHTING BEHIND "OB" BUTTON IS DIMMER THAN THE REST OF ALL THE OTHER BUTTONS. SENT TO MAGELLAN SYSTEMS FOR WARRANTY EXCHA	NGE.				1	G	7	2 	3U				H3EU 					 
1995081100284	19950811	00284		1995	8	11	HEEA955514 	4	19950802	G	3457	0845000000	SKYNAV 5000 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT GPS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951					2771				INOPERATIVE. LOST MEMORY. SENT TO MAGELLAN SYSTEMS FOR WARRANTY EXCHANGE. RECEIVED REPAIRED ON 6-8-95.						1	G	7	1 	3U				H9EU 					 
1995081100285	19950811	00285	SW 	1995	8	11	HEEA955515 	1	19950802	G	6240	412075010109	INDICATOR 			BELL 	412 	412 	1182202	SW 										TRIPLE TACH	COCKPIT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				ROTOR NEEDLE INDICATES 4% LOW THROUGHOUT SCALE.						1	G	7	2 	4U				H4SW 					 
1995081100286	19950811	00286	SW 	1995	8	11	HEEA955516 	1	19950802	G	7714	412075010109	INDICATOR 			BELL 	412 	412 	1182202	SW 										TRIPLE TACH	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				#2 NEEDLE HAS A STICKY OPERATION; CAUSING A 3% NEEDLE SPLIT ON INCREASING RPM. TIME SINCE REPAIR 59:00.						1	G	7	2 	4U				H4SW 					 
1995081100287	19950811	00287	SW 	1995	8	11	HEEA955517 	1	19950802	G	7712	212070160101	INDICATOR 			BELL 	212 	212 	1181420	SW 										DUAL TORQUE	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3131S					30953				#1 NEEDLE READ 10% LOW.						1	G	7	1 	4U				H4SW 					 
1995081100288	19950811	00288	SW 	1995	8	11	HEEA955518 	1	19950802	G	2436	206075447007	REGULATOR 			BELL 	206 	206L3 	1182108	SW 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31073					51519				GENERATOR COMING ON AND OFF LINE.						1	G	7	1 	3U				H2SW 					 
1995081100289	19950811	00289	GL 	1995	8	11	HEEA955519 	2	19950802	G	7321	252494410	FUEL CONTROL 			BELL 	206 	206L 	1181522	SW 	ALLSN 	250C 	250C28B 	03013	GL 					ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7074W	8748 				52033				FUEL CONTROL BY-PASS COVER RETENTION SCREW HEAD BROKEN (SHEARED)						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995081100290	19950811	00290		1995	8	11	HEEA955521 	4	19950802	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	33008	2397 				36004				CVR DID NOT TEST ON EITHER SIDE.						1	G	7	2 	4U				H4SW 					 
1995081100291	19950811	00291		1995	8	11	HEEA955522 	4	19950802	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S	1697 				36002				CVR INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995081100292	19950811	00292		1995	8	11	HEEA955523 	4	19950802	G	3453	066402600	LORAN 		KLN88 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	54191					S804				LORAN NO SCREEN INDICATION.						1	G	7	2 	3U				H3EU 					 
1995081100293	19950811	00293	SW 	1995	8	11	HEEA955524 	1	19950802	G	2436	206075447007	REGULATOR 			BELL 	206 	206L1 	1182107	SW 										DC SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2251A					45755				GENERATOR DELAYED IN COMING ON LINE.						1	G	7	1 	3U				H2SW 					 
1995081100294	19950811	00294	SW 	1995	8	11	HEEA955525 	1	19950802	G	2820	206063640103	VALVE 			BELL 	206 	206L1 	1182107	SW 										FUEL SYS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2775A					45297				MOTOR WILL NOT STOP RUNNING.						1	G	7	1 	3U				H2SW 					 
1995081100295	19950811	00295	EU 	1995	8	11	HEEA955526 	1	19950802	G	6220	827S115X140X12FP	SHAFT SEAL 		10514104 	BOLKMS	105 	BO105S 	5626006	EU 										M/R HEAD	LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	624MB				S162	S751				SEALING LIP ON SEALS FOUND TO BE DEFECTIVE CAUSING OIL TO LEAK OUT OF MAIN ROTOR HEAD.						1	G	7	2 	3U				H3EU 					 
1995081100296	19950811	00296	EU 	1995	8	11	HEEA955527 	1	19950803	G	6230	350A37000402	TRANSMISSION 			SNIAS 	350 	AS350B2 	8680813	EU 										SWASHPLATE	SEAL LEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	472 				2771				SWASHPLATE BEARING GREASE SEAL LEAKING. REPLACED WITH SERVICEABLE ASSEMBLY AND RETURNED TO SERVICE.						1	G	7	1 	3U				H9EU 					 
1995081100297	19950811	00297	EU 	1995	8	11	HEEA955528 	1	19950803	G	6230	704A33699008	BOOT 			SNIAS 	350 	AS350B2 	8680813	EU 										SWASHPLATE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951					2771				LOWER ATTACH POINT STRETCHED. NO LONGER ATTACHES TO SWASHPLATE. REPLACED WITH SERVICEABLE BOOT. (OLD PART SCRAPPED)						1	G	7	1 	3U				H9EU 					 
1995081100298	19950811	00298	EU 	1995	8	11	HEEA955529 	1	19950803	G	6500	350A33205721	WASHER TAB 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	932 				2771				LOCK TAB BROKEN OFF. REPLACED LOCK WASHER AND RETURNED AIRCRAFT TO SERVICE.						1	G	7	1 	3U				H9EU 					 
1995081100299	19950811	00299	EU 	1995	8	11	HEEA955530 	1	19950803	G	6720	350A27119120	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R CONTROL	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	896 				2771				TAIL ROTOR CONTROL TUBE GUIDE IS WORN. REMOVED AND REPLACED WITH NEW GUIDE.						1	G	7	1 	3U				H9EU 					 
1995081100300	19950811	00300	EU 	1995	8	11	HEEA955531 	1	19950803	G	6420	350A37211905	HUB 			SNIAS 	350 	AS350B 	8680801	EU 										T/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	529 				2777				WORN BEARINGS IN HUB. REPLACED HUB ASSEMBLY.						1	G	7	1 	3U				H9EU 					 
1995081100301	19950811	00301	EU 	1995	8	11	HEEA955532 	1	19950803	G	6220	123668P	ROD END 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951					2771				BEARING WORN. REPLACED WITH SERVICEABLE ROD END.						1	G	7	1 	3U				H9EU 					 
1995081100302	19950811	00302	EU 	1995	8	11	HEEA955533 	1	19950803	G	6220	350A32124420	BOLT 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1676 				2771				GRAPHOIL COATING WORN THROUGH. REPLACED WITH SERVICEABLE BOLTS.						1	G	7	1 	3U				H9EU 					 
1995081100303	19950811	00303	EU 	1995	8	11	HEEA955534 	1	19950803	G	6220	350A32124420	BOLT 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1676 				2771				GRAPHOIL COATING WORN THROUGH. SERIAL NUMBERS REMOVED ARE 14246, 12047, 14365, 13884, 14387. REPLACED WITH SERVICEABLE 	BOLTS.					1	G	7	1 	3U				H9EU 					 
1995081100304	19950811	00304		1995	8	11	HEEA955535 	4	19950804	G	3442	MI585467	ANTENNA PEDESTAL			BELL 	230 	230 	1182149	SW 										RADAR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2059 				23009				ANTENNA FUNCTIONS INTERMITTENTLY.						1	G	7	2 	3U			NC	H9SW 					 
1995081800256	19950818	00256	SW 	1995	8	18	HEEA955536 	1	19950807	G	2730	214001970107	ACTUATOR ASSY 			BELL 	214 	214ST 	1182106	SW 										NR 1 ELEV	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				#1 ELEVATOR SYSTEM TRIPS OFF LINE DURING FLIGHT - COULD NOT ADJUST ENOUGH.						2	G	7	2 	4U				H10SW 					 
1995081800257	19950818	00257	EU 	1995	8	18	HEEA955538 	4	19950807	G	2562	DK100	BEACON 			BOLKMS	105 	BO105S 	5626006	EU 										LOCATOR BEACON	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	81982	669 				S818				LOW BATTERY VOLTAGE. SENT TO DUKANE INDUSTRIES FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H3EU 					 
1995081800258	19950818	00258	EU 	1995	8	18	HEEA955539 	1	19950807	G	7722	TM42740	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										ENG TEMP	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3535T					S113				INDICATOR HAS ERRATIC READING.						1	G	7	2 	3U				H3EU 					 
1995081800259	19950818	00259	SW 	1995	8	18	HEEA955540 	1	19950807	G	3213	412050010107	CROSSTUBE 			BELL 	412 	412 	1182202	SW 										HISKID	DEBONDED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893N	5196 				33010				CROSSTUBE PREBOND PEELED BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995081800260	19950818	00260	SW 	1995	8	18	HEEA955541 	1	19950807	G	2810	412060603102	FUEL CELL 			BELL 	412 	412 	1182202	SW 										CELL SEAMS	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893N					33010				FUEL CELL HAS CRACKED SEAMS.						1	G	7	2 	4U				H4SW 					 
1995081800261	19950818	00261	EU 	1995	8	18	HEEA955543 	1	19950807	G	2842	1176415203	TRANSDUCER 			BOLKMS	117 	BK117B1 	5626012	EU 										FUEL QTY	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911TL					7198				TRANSDUCER CAUSING FUEL GAUGE NEEDLE TO STICK AT ZERO.						1	G	7	2 	3U				H13EU 					 
1995081800262	19950818	00262	EU 	1995	8	18	HEEA955544 	1	19950807	G	7722	1179405105	INDICATOR 			BOLKMS	117 	BK117A4 	5626017	EU 										COCKPIT	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	520WJ					7092				TOT INDICATOR READS 20 DEGREES LOW.						1	G	7	2 	3U				H13EU 					 
1995081800263	19950818	00263	EU 	1995	8	18	HEEA955545 	1	19950807	G	7722	1179405105	INDICATOR 			BOLKMS	117 	BK117A4 	5626017	EU 										COCKPIT	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	520WJ					7092				TOT INDICATOR READS 30 DEGREES LOW.						1	G	7	2 	3U				H13EU 					 
1995081800264	19950818	00264	EU 	1995	8	18	HEEA955546 	1	19950807	G	2841	VT4261	GAUGE 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL QTY	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5031U					S678				SUPPLY INOPERATIVE, ERRATIC READING.						1	G	7	2 	3U				H3EU 					 
1995081800265	19950818	00265	SW 	1995	8	18	HEEA955547 	1	19950807	G	7830	212061201011	EJECTOR 			BELL 	412 	412 	1182202	SW 										LT EXH	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893N					33010				LT EJECTOR RING ASSEMBLY CRACKED AND PARTS OF RING MISSING.						1	G	7	2 	4U				H4SW 					 
1995081800266	19950818	00266	NE 	1995	8	18	HEEA955548 	1	19950807	G	6220	7610608003042	PISTON 			SKRSKY	S76 	S76A 	8143006	NE 										M/R HEAD	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										PISTON ROD ASSY. WAS RECEIVED FROM SUPPLY WITH A NICK.						1	G	7	2 	3U				H1NE 					 
1995081800267	19950818	00267	EU 	1995	8	18	HEEA955550 	4	19950808	G	2562	DK100	BEACON 			BOLKMS	105 	BO105S 	5626006	EU 										LOCATOR BEACON	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										BEACON BATTERY LOW.						1	G	7	2 	3U				H3EU 					 
1995081800268	19950818	00268		1995	8	18	HEEA955551 	4	19950808	G	2210	7611123	AMPLIFIER 			SKRSKY	S76 	S76A 	8143006	NE 										PITCH SLICE	KICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911MJ					760231				#1 PITCH KICK IN FLIGHT.						1	G	7	2 	3U				H1NE 					 
1995081800269	19950818	00269	SW 	1995	8	18	HEEA955552 	1	19950808	G	7722	212075067105	INDICATOR 			BELL 	212 	212 	1181420	SW 										COCKPIT ITT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5736D					31135				INDICATOR DEFECTIVE, DOESN'T INDICATE.						1	G	7	1 	4U				H4SW 					 
1995081800270	19950818	00270	SW 	1995	8	18	HEEA955553 	1	19950808	G	2436	206075447007	REGULATOR 			BELL 	206 	206L1 	1182107	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2246Q					45752				REGULATOR DEFECTIVE CANNOT DECREASE BELOW 40 VOLTS.						1	G	7	1 	3U				H2SW 					 
1995081800271	19950818	00271	SW 	1995	8	18	HEEA955554 	1	19950808	G	2436	206075447007	REGULATOR 			BELL 	206 	206L3 	1182108	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31801					51074				REGULATOR DEFECTIVE. GENERATOR WOULD NOT COME ON LINE.						1	G	7	1 	3U				H2SW 					 
1995081800272	19950818	00272	SW 	1995	8	18	HEEA955555 	1	19950808	G	2436	206075447007	REGULATOR 			BELL 	206 	206L1 	1182107	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2246Q					45752				REGULATOR DEFECTIVE. GENERATOR COMES OFF LINE 8 TIMES DURING 45 MINUTE FLIGHT.						1	G	7	1 	3U				H2SW 					 
1995081800273	19950818	00273	SW 	1995	8	18	HEEA955556 	1	19950808	G	2422	ASH4501	INVERTER 			BELL 	412 	412 	1182202	SW 										AC SYS	NOISY 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	23023					33080				INVERTER HAS NOISY OUTPUT.						1	G	7	2 	4U				H4SW 					 
1995081800274	19950818	00274	EU 	1995	8	18	HEEA955557 	1	19950808	G	7930	6607190A	SWITCH 			BOLKMS	105 	BO105S 	5626006	EU 										OIL PRESS WARN	DEFECTIVE 	E			HEEA	K				NONE 				P			NO WARNING INDICATION 			NR	NOT REPORTED 	1			SW	03	205UC					S668				T-OIL LIGHT WILL NOT ILLUMINATE. REPLACED WITH SERVICEABLE PRESS. SWITCH.						1	G	7	2 	3U				H3EU 					 
1995081800275	19950818	00275	EU 	1995	8	18	HEEA955558 	1	19950808	G	2822	D107318D1	PUMP ASSY 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5421E					S806				PUMP CUTS OUT AND CAUSE FUEL PRESSURE TO FLUCTUATE. REPLACED PUMP ASSEMBLY.						1	G	7	2 	3U				H3EU 					 
1995081800276	19950818	00276	SW 	1995	8	18	HEEA955559 	1	19950808	G	2435	23081018	STARTER 			BELL 	206 	206L3 	1182108	SW 										START/GEN	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6610Y					51419				SPACER BETWEEN SHAFT AND GENERATOR FLANGE DISINTEGRATED CAUSING SHAFT NOT TO ENGAGE IN SPLINES. REMOVED AND REPLACED STA	RTER GENERATOR.					1	G	7	1 	3U				H2SW 					 
1995081800277	19950818	00277	SW 	1995	8	18	HEEA955560 	1	19950808	G	6310	206040270003	FREEWHEEL 			BELL 	206 	206B 	1181511	SW 										ENG/XMSN	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3181J	14861				3771				FREEWHEEL MAKING METAL. REPLACED FREEWHEELING UNIT.						1	G	7	1 	3U				H2SW 					 
1995081800278	19950818	00278	SW 	1995	8	18	HEEA955561 	1	19950808	G	6710	206001019005	SUPPORT ASSY 			BELL 	206 	206L1 	1182107	SW 										M/R CONTROL	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5742N					45477				SUPPORT ASSY CORROSION BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H2SW 					 
1995081800279	19950818	00279	SW 	1995	8	18	HEEA955562 	1	19950808	G	6710	206001343001	ELBOW 			BELL 	206 	206L1 	1182107	SW 										M/R CONTROL	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5742N					45477				CORROSION BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H2SW 					 
1995081800280	19950818	00280		1995	8	18	HEEA955563 	4	19950808	G	3453	25410038	7000 CDU 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1545K					760047				DISPLAY SEGMENTS MISSING.						1	G	7	2 	3U				H1NE 					 
1995081800281	19950818	00281		1995	8	18	HEEA955564 	4	19950808	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4282Z					51499				TRANSPONDER INOPERATIVE. UNIT WOULD DRAW EXCESSIVE CURRENT. FOUND V101 CAVITY OSCILLATOR TO BE PROBLEM. REPLACED V101 	CAVITY AND ALSO REPLACED WEAK V301 PHOTODETECTOR. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995081800282	19950818	00282		1995	8	18	HEEA955565 	4	19950808	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8197X					S808				TRANSPONDER NO SIGNAL. IDENT LIGHT VERY WEAK WHEN TESTED. REPLACED WEAK V101 CAVITY OSCILLATOR AND WEAK V301 PHOTODECTO	R. REPAIRED PROBLEM. BENCH CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995081800283	19950818	00283		1995	8	18	HEEA955566 	4	19950808	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5421E					S806				TRANSPONDER WILL NOT IDENT. RESOLDERED COLD SOLDER JOINT ON DIODE CR416. REPAIRED RECEIVE PROBLEM. FOUND -10 VOLTS ON 	-6 VOLT LINE. TROUBLESHOT AND FOUND C409 CAPACITOR DEFECTIVE. REPLACED CAPACITOR TO REPAIR -6V LINE. COMPLETED FUNCTI	ON CHECK. ALSO INSTALLED Q415 HEATSINK AND REPLACED DETERIORATED RESISTOR R477. BENCH CHECK GOOD.				1	G	7	2 	3U				H3EU 					 
1995081800284	19950818	00284		1995	8	18	HEEA955567 	4	19950808	G	3423	C2300DL4B	COMPASS 	MASCO 																COCKPIT	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03										COMPASS UNIT GIVES ERRATIC READINGS.																			 
1995081800285	19950818	00285	NE 	1995	8	18	HEEA955568 	1	19950808	G	7334	7645001078119	TRANSMITTER 			SKRSKY	S76 	S76A 	8143006	NE 										FUEL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				TRANSMITTER CAUSING ERRONEOUS READINGS.						1	G	7	2 	3U				H1NE 					 
1995081800286	19950818	00286	SW 	1995	8	18	HEEA955569 	1	19950808	G	2435	36B510954G2	CLUTCH 			BELL 	214 	214ST 	1182106	SW 										START/GEN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N					28106				START/GEN CLUTCH HAS EXCESSIVE END PLAY AND BREAK AWAY TORQUE BELOW LIMITS.						2	G	7	2 	4U				H10SW 					 
1995081800287	19950818	00287	EU 	1995	8	18	HEEA955570 	1	19950808	G	7714	1176322301	SPRING 			BOLKMS	117 	BK117B2 	5626013	EU 										N2 CONTROL	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	925 				7234				N2 CONTROL SPRING CRACKED. SCRAPPED IN FIELD.						1	G	7	2 	3U			NC	H13EU 					 
1995081800288	19950818	00288		1995	8	18	HEEA955571 	4	19950808	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6610E					51424				TRANSPONDER INOPERATIVE. OFF FREQUENCY. ADJUSTED FREQUENCY TO SPECS. REPAIRED. ALSO FOUND UNIT TO HAVE WEAK RECEIVE A	ND INTERMITTENT TRANSMIT. REPLACED MIXER DIODE CR202. REPAIRED WEAK RECEIVE. CLEANED CONNECTOR P202 AND WHERE CONNECT	OR P202 FITS ON CAVITY TUBE. REPAIRED INTERMITTENTTRANSMIT. REPLACED DETERIORATED RESISTOR R477. REPLACED PHOTOCELL V	301 DUE TO WEAK REPLY LIGHT. REPAIRED. CLEANED CONTACTS ON WAFER SWITCHES. BENCH CHECK GOOD.			1	G	7	1 	3U				H2SW 					 
1995081800289	19950818	00289	SW 	1995	8	18	HEEA955572 	1	19950808	G	2436	206075447007	REGULATOR 			BELL 	206 	206L3 	1182108	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4180F					51469				GENERATOR WILL NOT COME ON LINE.						1	G	7	1 	3U				H2SW 					 
1995081800290	19950818	00290		1995	8	18	HEEA955573 	4	19950808	G	2312	40001452500	TRANSCEIVER 		RT138F 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	90752					S156				TRANSCEIVER UNIT HAS HESITATING POWER WHEN KEYING UP.						1	G	7	2 	3U				H3EU 					 
1995081800291	19950818	00291		1995	8	18	HEEA955574 	4	19950808	G	3455	066107200	RECEIVER 		KR87 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ADF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	50293					S677				DISPLAY FLICKERS. REPLACED DISPLAY REPAIRED.						1	G	7	2 	3U				H3EU 					 
1995091500235	19950915	00235	GL 	1995	9	15	HEEA955575 	2	19950808	G	7320	6890586	TUBE ASSY 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					NR 2 ENG N1	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	672 				23009	CAE898201			#2 ENGINE N1 NOT ADVANCING WITH THROTTLE INPUT. UPON TROUBLESHOOTING NOTED THE FOLLOWING: CRACKED TUBE ASSY APPROXIMAT	ELY 270 DEGREES AROUND FERRULE MATING SURFACE AT GOVERNOR END. SCRAPPED TUBE ASSEMBLY AND INSTALLED NEW TUBE ASSY.					1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995081800292	19950818	00292	GL 	1995	8	18	HEEA955576 	2	19950808	G	7250	6886407	WHEEL 		6898735 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					1ST STAGE	SULFIDATION 	E			HEEA	K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			SW	03	7136H	1681 			CAT33501	S833	CAE800819F			ENGINE REMOVED DUE TO LOW POWER. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MILD SULFIDATION OUT OF OVERHAU	L MANUAL LIMITS ON ALL 1ST STAGE TURBINE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995081800293	19950818	00293	EU 	1995	8	18	HEEA955577 	1	19950808	G	6220	350A31190703	STARFLEX 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1607 				2771				STARFLEX CRACKED.						1	G	7	1 	3U				H9EU 					 
1995081800294	19950818	00294	SW 	1995	8	18	HEEA955578 	1	19950808	G	5260	212075418103	ACTUATOR 			BELL 	412 	412 	1182202	SW 										STEP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2149S					36002				CIRCUIT BREAKER POPS IN BOTH DIRECTIONS. STEP ACTUATOR INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND ACTUATOR OPERATE	S BUT DRAWS HIGH AMPERAGE.					1	G	7	2 	4U				H4SW 					 
1995081800295	19950818	00295	SW 	1995	8	18	HEEA955579 	1	19950809	G	5302	212030126001	CAP 		212030100069	BELL 	212 	212 	1181420	SW 										TAILBOOM	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03					ADW03193					IMPROPER DISTANCE FROM LOWER EDGE OF CAP TO MILLED AREA FOR CAMLOC RAIL. DISTANCE ON NEW PART IS .650. DISTANCE ON OLD 	PART IS .550.					1	G	7	1 	4U				H4SW 					 
1995081800296	19950818	00296	SW 	1995	8	18	HEEA955580 	1	19950809	G	5302	212030126001	CAP 		212030100069	BELL 	212 	212 	1181420	SW 										TAILBOOM	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03					ADW03193					MILLED AREA OF VERTICAL LEG, WHERE COWLING CAMLOC RAIL ATTACHES, IS NOT WIDE ENOUGH TO MAINTAIN REQUIRED EDGE DISTANCE O	N BOTH CAP ANGLE AND CAMLOC RAIL.					1	G	7	1 	4U				H4SW 					 
1995081800297	19950818	00297	SW 	1995	8	18	HEEA955581 	1	19950809	G	5302	206030407103A	BRACKET 		206031004115	BELL 	206 	206B 	1181511	SW 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	2FOR				BCJN08060	3000				RECEIVED NEW HANGER BEARING BRACKET WITH CRACKED, AFT VERTICAL FLANGE IN CENTER OF BRACKET.						1	G	7	1 	3U				H2SW 					 
1995081800298	19950818	00298	SW 	1995	8	18	HEEA955582 	1	19950809	G	6710	206062721105	ACTUATOR 			BELL 	230 	230 	1182149	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	542 				23009				ACTUATOR WOULD NOT BEEP.						1	G	7	2 	3U			NC	H9SW 					 
1995081800299	19950818	00299	SW 	1995	8	18	HEEA955583 	1	19950809	G	5320	212030009115A	DECK ASSY 			BELL 	412 	412 	1182202	SW 										ENGINE	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N					33010				ENGINE DECK SEPARATED BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995081800300	19950818	00300	SW 	1995	8	18	HEEA955584 	1	19950809	G	2436	206075447007	REGULATOR 			BELL 	206 	206L1 	1182107	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2772A					45311				GENERATOR KICKS OFF LINE.						1	G	7	1 	3U				H2SW 					 
1995081800301	19950818	00301	SW 	1995	8	18	HEEA955585 	1	19950809	G	5610	222031290117	VENT WINDOW 			BELL 	230 	230 	1182149	SW 										COCKPIT	HINGE BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2279 				23009				VENT WINDOW HINGES BROKEN.						1	G	7	2 	3U			NC	H9SW 					 
1995081800302	19950818	00302	EU 	1995	8	18	HEEA955588 	1	19950810	G	2121	420800001	BLOWER 			SNIAS 	350 	AS350B2 	8680813	EU 										AIR DIST	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	350BZ	1151 				2653				BLOWER INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995081800303	19950818	00303	EU 	1995	8	18	HEEA955589 	1	19950810	G	6420	350A33211905	BODY 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	RUBBER SPLIT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6097Z	795 				2820				TAIL ROTOR BODY SPLIT RUBBER.						1	G	7	1 	3U				H9EU 					 
1995081800304	19950818	00304		1995	8	18	HEEA955590 	4	19950810	G	3416	61031016	ALTIMETER 			BELL 	206 	206L3 	1182108	SW 										COCKPIT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4282Z					51499				ALTIMETER NEEDLE INTERMITTENTLY STICKS THROUGHOUT SCALE. TIME SINCE REPAIR 81:50.						1	G	7	1 	3U				H2SW 					 
1995081800305	19950818	00305		1995	8	18	HEEA955591 	4	19950810	G	3416	212070238007	ALTIMETER 			BELL 	230 	230 	1182149	SW 										COCKPIT	ERROR 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN					23009				ALTIMETER NEEDLE IS 140 FEET OFF AT 18,000 FEET. ALSO, INTERMITTENTLY STICKS WHEN DECREASING ALTITUDE. TIME SINCE REPAI	R 164:25.					1	G	7	2 	3U			NC	H9SW 					 
1995081800306	19950818	00306		1995	8	18	HEEA955592 	4	19950810	G	3416	5035P2P44	ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT ENCODER	FRICTION ERROR 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				NEEDLE HAS EXCESSIVE FRICTION ERROR. TIME SINCE REPAIR 89:45.						1	G	7	2 	4U				H4SW 					 
1995090100210	19950901	00210	SW 	1995	9	1	HEEA955593 	1	19950817	G	6520	214040009109	GEAR BOX 			BELL 	214 	214ST 	1182106	SW 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N	832 				28106				COUPLING BACKLASH TOO HIGH. NOTE: PIN DIM IN CR&O CHAPTER 65.20-07 PAGE 33 PARAGRAPH #3B IS INCORRECT. GEARBOX REMOVE	D DUE TO THIS ERROR. REPAIRED GEARBOX.					2	G	7	2 	4U				H10SW 					 
1995090100211	19950901	00211	SW 	1995	9	1	HEEA955595 	1	19950817	G	2436	222375060115	REGULATOR 			BELL 	230 	230 	1182149	SW 										NR 2 GENERATOR	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2270 				23009				#2 GENERATOR LIGHT WILL NOT GO OUT.						1	G	7	2 	3U			NC	H9SW 					 
1995090100212	19950901	00212	SW 	1995	9	1	HEEA955597 	1	19950817	G	6410	206010765001	BEARING 		206016201127	BELL 	206 	206B 	1181511	SW 										T/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	FGHRS	1069 			CS251CS445	3000				BLADE BEARING CRACKED. ALSO DISCARDED 4 EACH SLEEVES P/N 206-010-733-003. BEARINGS SCRAPPED LOCALLY.						1	G	7	1 	3U				H2SW 					 
1995090100213	19950901	00213	SW 	1995	9	1	HEEA955598 	1	19950817	G	6220	206010110105	WASHER 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1072T	1200 			A2327	45385				MATERIAL DETERIORATION CAUSING EXCESSIVE LOAD. LOWERED TORQUE ON ADJUSTMENT SCREWS AND LOWERED PRELOAD ON THRUST PLUGS.						1	G	7	1 	3U				H2SW 					 
1995090100214	19950901	00214	SW 	1995	9	1	HEEA955599 	1	19950817	G	3212	TA14M15HB0222	CUSHION STRAP 			BELL 	230 	230 	1182149	SW 										FLOAT BOTTLE	TORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2258 				23009				FLOAT BOTTLE CLAMP CUSHIONS TORN.						1	G	7	2 	3U			NC	H9SW 					 
1995090100215	19950901	00215	EU 	1995	9	1	HEEA955600 	1	19950817	G	6730	SC50811	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			SW	03	60951	1724 				2771				CYCLIC STIFF WHEN IT IS MOVED LEFT AND RIGHT. FOUND LT-RT CONTROL SERVO DEFECTIVE						1	G	7	1 	3U				H9EU 					 
1995090100216	19950901	00216	EU 	1995	9	1	HEEA955601 	1	19950817	G	6730	SC50821	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6097Z	664 				2820				FRONT CONTROL SERVO CHATTERS AND WILL NOT TEST. UNIT WAS ORIGINALLY SENT LOOSE IN AIRCRAFT N6097Z.						1	G	7	1 	3U				H9EU 					 
1995090100217	19950901	00217		1995	9	1	HEEA955603 	4	19950824	G	2312	064102300	TRANSCIEVER 			BELL 	230 	230 	1182149	SW 										COCKPIT VHF	WEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2296 				23009				TRANSCEIVER WEAK AND LOW MODULATION.						1	G	7	2 	3U			NC	H9SW 					 
1995090100218	19950901	00218		1995	9	1	HEEA955604 	4	19950824	G	2312	064102300	TRANSCIEVER 			BELL 	230 	230 	1182149	SW 										COCKPIT VHF	WEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2302 				23009				TRANSCEIVER WEAK AND LOW MODULATION.						1	G	7	2 	3U			NC	H9SW 					 
1995090100219	19950901	00219	SW 	1995	9	1	HEEA955605 	1	19950824	G	3212	214052200102	FLOAT ASSY 			BELL 	214 	214ST 	1182106	SW 										TOP OFF VALVE	LEAKAGE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03										WHEN PERFORMING ACCEPTANCE CHECK, FLOAT BAG WAS DETERMINED TO HAVE LEAKAGE AROUND TOP-OFF VALVES AND POROSITY LEAKAGE ON	 FLOAT BAG.					2	G	7	2 	4U				H10SW 					 
1995090100220	19950901	00220	SW 	1995	9	1	HEEA955610 	1	19950825	G	5302	206032308103S	FRAME 			BELL 	206 	206L3 	1182108	SW 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X					51495				TAILBOOM FRAME CRACKED. REPLACED WITH SERVICEABLE FRAME.						1	G	7	1 	3U				H2SW 					 
1995090100221	19950901	00221	SW 	1995	9	1	HEEA955611 	1	19950825	G	5313	206031314037	LONGERON 			BELL 	206 	206L3 	1182108	SW 										LT AFT LONGERON	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8591X					51495				L/H AFT LONGERON CRACKED. REPLACED WITH SERVICEABLE L/H AFT LONGERON.						1	G	7	1 	3U				H2SW 					 
1995090100222	19950901	00222	SW 	1995	9	1	HEEA955612 	1	19950825	G	6310	206040015103	DRIVE SHAFT 			BELL 	206 	206B 	1181511	SW 										ENG/XMSN	OVERTEMP 	E			HEEA	K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			SW	03	2276B	10552				3628				BOTH FORWARD YELLOW TEMP. INDICATORS TURNED BLACK. REPLACED WITH SERVICEABLE DRIVE SHAFT.						1	G	7	1 	3U				H2SW 					 
1995090100223	19950901	00223	SW 	1995	9	1	HEEA955613 	1	19950825	G	5260	FYLM735023	MOTOR ASSY 		SYLC502281 	BELL 	412 	412 	1182202	SW 										STEP	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22608				3686	33075				INSPECTED BY ACCESSORY SHOP AND FOUND MOTOR INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995090100224	19950901	00224		1995	9	1	HEEA955614 	4	19950825	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	2258F	3019 				33073				CVR WILL NOT TEST.						1	G	7	2 	4U				H4SW 					 
1995090100225	19950901	00225		1995	9	1	HEEA955615 	4	19950825	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	2261D	2543 				33076				CVR DOES NOT TEST.						1	G	7	2 	4U				H4SW 					 
1995090100226	19950901	00226	SW 	1995	9	1	HEEA955616 	1	19950825	G	2432	3055401C	BATTERY 	MARATHON 		BELL 	206 	206L1 	1182107	SW 										DC SYS	WEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5742H					45476				BATTERY WEAK. INSPECTED BY ACCESSORY SHOP. THIS BATTERY HAS BEEN LEAD TESTED AND FOUND TO BE WEAK AS RECEIVED. FURTHE	R INSPECTION FOUND ELECTROLYTE DISCOLORED AND BATTERY FAILED TO COME UP TO REQUIRED 1.55 VOLTS AT END OF CHARGE.					1	G	7	1 	3U				H2SW 					 
1995090100227	19950901	00227	SW 	1995	9	1	HEEA955617 	1	19950825	G	2432	3055401C	BATTERY 	MARATHON 		BELL 	206 	206L1 	1182107	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3892R					45594				BATTERY INSPECTED BY ACCESSORY SHOP. FOUND CELL #17 TO HAVE THERMAL RUNNER WAY AND NUMEROUS CELLS WOULD NOT COME UP TO 	THE REQUIRED 1.55 VOLTS AT END OF CHARGE.					1	G	7	1 	3U				H2SW 					 
1995090100228	19950901	00228	EU 	1995	9	1	HEEA955618 	1	19950825	G	2432	24SP100	CELL 		30248001 	BOLKMS	105 	BO105S 	5626006	EU 										DC SYS	WEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	352TT				9300464	S59				BATTERY WEAK. INSPECTED BY ACCESSORY SHOP AND FOUND CELLS #5 AND #16 VOLTAGE READING ZERO VOLTS. CELLS REPLACED WITH ON	ES GIVEN ON CONSIGNMENT.					1	G	7	2 	3U				H3EU 					 
1995090100229	19950901	00229	NE 	1995	9	1	HEEA955619 	1	19950825	G	2432	40SP100	CELL 	MARATHON 	30126001S 	SKRSKY	S76 	S76A 	8143006	NE 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4253S				9204560	760035				TIME. INSPECTED BY ACCESSORY SHOP AND FOUND CELL #9 WOULD NOT ACCEPT A CHARGE. CELL REPLACED WITH ONE GIVEN ON CONSIGNM	ENT.					1	G	7	2 	3U				H1NE 					 
1995090100230	19950901	00230	SW 	1995	9	1	HEEA955620 	1	19950825	G	2432	40SP100	CELL 		30126002 	BELL 	412 	412 	1182202	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3911L				9400203	33023				BATTERY WEAK. INSPECTED BY ACCESSORY SHOP AND FOUND #4 VOLTAGE READING ZERO AS RECEIVED. CELL REPLACED WITH ONE GIVEN O	N CONSIGNMENT.					1	G	7	2 	4U				H4SW 					 
1995090100231	19950901	00231	SW 	1995	9	1	HEEA955621 	1	19950825	G	2432	17SP100	CELL 	MARATHON 	32007001 	BELL 	206 	206L3 	1182108	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	206FS				9303190	51506				TIME. INSPECTED BY ACCESSORY SHOP AND FOUND CELL #14 VOLTAGE READING ZERO AS RECEIVED. CELL REPLACED WITH ONE GIVEN ON 	CONSIGNMENT.					1	G	7	1 	3U				H2SW 					 
1995090100232	19950901	00232	SW 	1995	9	1	HEEA955622 	1	19950825	G	2432	17SP100	CELL 	MARATHON 	32007001 	BELL 	206 	206L 	1181522	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7074W				9304065	52033				TIME. INSPECTED BY ACCESSORY SHOP AND FOUND CELL #8 WOULD NOT ACCEPT A CHARGE AT THE END OF THE CHARGE. CELL REPLACED 	WITH ONE GIVEN ON CONSIGNMENT.					1	G	7	1 	3U				H2SW 					 
1995090100233	19950901	00233	SW 	1995	9	1	HEEA955623 	1	19950825	G	2432	17SP100	CELL 	MARATHON 	3055401C 	BELL 	206 	206L1 	1182107	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2772A				9306831	45311				LOW VOLTAGE. INSPECTED BY ACCESSORY SHOP AND FOUND BATTERY CELL #17 WILL NOT TAKE A CHARGE. CELL REPLACED WITH ONE GIVE	N ON CONSIGNMENT.					1	G	7	1 	3U				H2SW 					 
1995090100234	19950901	00234	EU 	1995	9	1	HEEA955624 	1	19950825	G	2432	17SP100	CELL 	MARATHON 	30402001 	AEROSP	AS355 	AS355F1 	8680810	EU 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5785Y				9307200	5105				TIME. INSPECTED BY ACCESSORY SHOP AND FOUND CELL #2 WOULD NOT ACCEPT A CHARGE. CELL REPLACED WITH ONE GIVEN ON CONSIGNM	ENT.					1	G	7	2 	3U				H11EU 					 
1995090100235	19950901	00235	SW 	1995	9	1	HEEA955626 	1	19950825	G	2432	17SP100	CELL 		32007001 	BELL 	206 	206L3 	1182108	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8592X				9402767	51508				TIME. INSPECTED BY ACCESSORY SHOP AND FOUND CELL #8 VOLTAGE READING ZERO AS RECEIVED. CELL REPLACED WITH ONE GIVEN ON C	ONSIGNMENT.					1	G	7	1 	3U				H2SW 					 
1995090100236	19950901	00236		1995	9	1	HEEA955627 	4	19950825	G	2210	7683431	POTENTIOMETER 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		98 								POTIENTIOMETER CAUSES ERRATIC READINGS ON STRIP CHART WHEN TESTING AFCS ACTUATOR.						1	G	7	2 	3U				H1NE 					 
1995090100237	19950901	00237	NE 	1995	9	1	HEEA955628 	1	19950825	G	7930	7630807900101	SWITCH 			SKRSKY	S76 	S76A 	8143006	NE 										OIL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5435V	187 				760158				SWITCH DOES NOT ILLUMINATE CAUTION LIGHT; INTERMITTENTLY.						1	G	7	2 	3U				H1NE 					 
1995090100238	19950901	00238	EU 	1995	9	1	HEEA955629 	1	19950825	G	7930	DK040	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										OIL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	724MB	45 				S756				#1 ENGINE OIL PRESSURE NEEDLE INDICATES FULL SCALE. REPLACED WITH SERVICEABLE TRANSMITTER.						1	G	7	2 	3U				H3EU 					 
1995090100239	19950901	00239	EU 	1995	9	1	HEEA955630 	1	19950825	G	3340	4580	LAMP 			SNIAS 	350 	AS350B2 	8680813	EU 										LANDING LIGHT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951					2771				FOUND LANDING LIGHT BULB BLOWN. REPLACED WITH SERVICEABLE BULB.						1	G	7	1 	3U				H9EU 					 
1995090100240	19950901	00240	EU 	1995	9	1	HEEA955631 	1	19950825	G	3340	4580	LAMP 			SNIAS 	350 	AS350B2 	8680813	EU 										LANDING LIGHT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951					2771				LANDING LIGHT BURNT OUT. REPLACED WITH SERVICEABLE BULB.						1	G	7	1 	3U				H9EU 					 
1995090100241	19950901	00241		1995	9	1	HEEA955632 	4	19950825	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	707AE	2059 				760276				CVR WILL NOT TEST. TIME SINCE REPAIR 260:45.						1	G	7	2 	3U				H1NE 					 
1995090100242	19950901	00242	EU 	1995	9	1	HEEA955633 	1	19950825	G	2822	2C273	CARTRIDGE 			BOLKMS	105 	BO105S 	5626006	EU 										BOOST PUMP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	86CH					S557				UNIT STOPPED RUNNING. INSPECTED BY ACCESSORY SHOP AND RAN ON TEST BENCH. UNIT RAN SLOW AND NOISY. IT DID NOT RUN FAST	 ENOUGH TO INDICATE FLOW ON THE FLOW METER AND PRODUCED APPROXIMATELY 1 1/2 LBS. OF PRESSURE. UNIT RAN THIS WAY FOR A C	OUPLE OF MINUTES THEN STOPPED WORKING AND WOULD NOT START AGAIN. WHEN CARTRIDGE WAS REMOVED FROM BENCH IT WAS FOUND TO 	HAVE FUEL ON INTERIOR.			1	G	7	2 	3U				H3EU 					 
1995090100243	19950901	00243	EU 	1995	9	1	HEEA955634 	1	19950825	G	7110	350A5810262703	DOUBLER ASSY 			SNIAS 	350 	AS350B2 	8680813	EU 										LT ENG COWL	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6095S	875 				2777				L/H AFT ENGINE COWL LATCH WORN AND ATTACHING DOUBLER CRACKED.						1	G	7	1 	3U				H9EU 					 
1995090100244	19950901	00244	EU 	1995	9	1	HEEA955635 	1	19950825	G	2822	1109000A5	FUEL PUMP 			BOLKMS	117 	BK117B2 	5626013	EU 										FUEL BOOST	LEAKS 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	911LK	3361 				7068				EXCESSIVE FUEL LEAKS OUT SEAL DRAIN WHEN BOOST PUMP IS TURNED ON.						1	G	7	2 	3U			NC	H13EU 					 
1995090100245	19950901	00245	SW 	1995	9	1	HEEA955636 	1	19950825	G	5260	BYLM5090185	ACTUATOR 		SYLC502283 	BELL 	412 	412 	1182202	SW 										STEP	ARMATURE BURNT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2258F	33 			2103	33073				UNIT INOPERATIVE. INSPECTED AND BENCH CHECKED BY ACCESSORY OVERHAUL SHOP. UNIT SLOW TO RESPOND AND DREW EXCESSIVELY HI	GH AMPS. FOUND ARMATURE BURNT.					1	G	7	2 	4U				H4SW 					 
1995092200031	19950922	00031	SW 	1995	9	22	HEEA955637 	1	19950830	G	6330	214040013113	GEARBOX 			BELL 	214 	214ST 	1182106	SW 										COMBINING GR BOX	STUD BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N	3029 				28106				BROKEN STUD ON R/H BIPOD MOUNT LOCATION.						2	G	7	2 	4U				H10SW 					 
1995092200032	19950922	00032	SW 	1995	9	22	HEEA955638 	1	19950830	G	6330	214040013113	GEARBOX 			BELL 	214 	214ST 	1182106	SW 										COMBINING GR BOX	STUD BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M	3831 				28102				BROKEN STUD ON THE R/H FORWARD ENGINE MOUNT BIPOD LOCATION.						2	G	7	2 	4U				H10SW 					 
1995092200033	19950922	00033	SW 	1995	9	22	HEEA955642 	1	19950830	G	6220	412010111103	FITTING 			BELL 	412 	412 	1182202	SW 										M/R	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										BOLT HOLE BOSSES WILL NOT ACCEPT BOLT AND NUTS. BOSS HAS NOT BEEN MACHINED TO SPEC.						1	G	7	2 	4U				H4SW 					 
1995092200034	19950922	00034	SW 	1995	9	22	HEEA955643 	1	19950830	G	6210	412015048105	TIP COVER ASSY 			BELL 	412 	412 	1182202	SW 										M/R BLADE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										COVER HAS PREBOND MATERIAL MISSING ALONG THE LEADING EDGE SURFACES.						1	G	7	2 	4U				H4SW 					 
1995092200035	19950922	00035	EU 	1995	9	22	HEEA955644 	1	19950830	G	6220	10513142	ROD END ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										M/R	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										DOES NOT HAVE MACHINED GROOVE TO INSTALL LOCK WASHER.						1	G	7	2 	3U				H13EU 					 
1995092200036	19950922	00036		1995	9	22	HEEA955645 	4	19950831	G	3453	4530093	RECEIVER 		ARNAV20 	BELL 	206 	206L 	1181522	SW 										COCKPIT LORAN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21497					51518				UNIT WILL NOT ACCEPT COMMANDS.						1	G	7	1 	3U				H2SW 					 
1995092200037	19950922	00037		1995	9	22	HEEA955646 	4	19950831	G	2312	064105430	TRANSCEIVER 			AEROSP	AS355 	AS355F2 	8680812	EU 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6040U					5474				VERY LOUD STATIC NOISE ON ALL FREQUENCIES.						1	G	7	2 	3U				H11EU 					 
1995092200038	19950922	00038		1995	9	22	HEEA955647 	4	19950831	G	3425	1113025	INDICATOR 			BELL 	212 	212 	1181420	SW 										COCKPIT HSI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5736J					31140				OFF FLAG WILL NOT PULL. WILL NOT SLAVE.						1	G	7	1 	4U				H4SW 					 
1995092200039	19950922	00039		1995	9	22	HEEA955648 	4	19950831	G	2312	6222078001	TRANSCEIVER 		VHF251 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT VHF	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	352TT					S59				INOPERATIVE. GEARS BROKEN AND WAFER SWITCH BROKEN ON STORE, SELECT, RECALL CONTROL.						1	G	7	2 	3U				H3EU 					 
1995092200040	19950922	00040		1995	9	22	HEEA955649 	4	19950831	G	3416	D120P2T	ANEROID 			BELL 	206 	206L1 	1182107	SW 										ALTIMETER	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22425					45743				UNIT HAS EXCESSIVE DRIFT RATE. TRANSMITS LOW OUT OF TOLERANCE ABOVE 10,000 FEET.						1	G	7	1 	3U				H2SW 					 
1995092200041	19950922	00041		1995	9	22	HEEA955650 	4	19950831	G	3457	0845000000	SKYNAV 5000 																	COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03										UNIT DOES NOT FIT ALL THE WAY INTO RACK.																			 
1995092200042	19950922	00042		1995	9	22	HEEA955651 	4	19950831	G	3457	0845000000	SKYNAV 5000 																	COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03										INOPERATIVE GREEN LIGHT IN 20 MODE.																			 
1995092200043	19950922	00043	SW 	1995	9	22	HEEA955652 	1	19950831	G	5230	205032809035	PANEL ASSY 			BELL 	412 	412 	1182202	SW 										BAG DOOR	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	3893N					33010				DIMENSION OF CORE TOO LONG TO FIT IN BAGGAGE DOOR SILL OPENING. DIMENSION OF OPENING IS 28 INCHES FROM FWD. TO AFT SILL	. DIMENSION OF HONEYCOMB ON DOOR FROM TRANSITION AREA FWD TO AFT IS 28 5/8". DIMENSION OF HONEYCOMB CORE FROM TOP TOBO	TTOM OF DOOR IS OK.				1	G	7	2 	4U				H4SW 					 
1995092200044	19950922	00044	EU 	1995	9	22	HEEA955653 	1	19950831	G	6210	10515141	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7171A	6629 				S838				NOSE AND NECK SHELL CRACKED IN THE ROOT AREA. ALSO HAS A SMALL AREA OF SEPARATION NEAR THE TIP ON THE LEADING EDGE STRI	P.					1	G	7	2 	3U				H3EU 					 
1995092200045	19950922	00045	EU 	1995	9	22	HEEA955654 	1	19950831	G	7714	DL40438	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										TRIPLE TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	86CH					S557				#1 NEEDLE LAGS BY APPROXIMATELY 3%.						1	G	7	2 	3U				H3EU 					 
1995092200046	19950922	00046		1995	9	22	HEEA955655 	4	19950831	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6559Z					36019				COMMAND COURSE NEEDLE INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995092200047	19950922	00047	SW 	1995	9	22	HEEA955656 	1	19950831	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5014Y	2758 				45219				BOLT BUSHING PITTED BEYOND THE MAX. LIMIT OF 1.524".						1	G	7	1 	3U				H2SW 					 
1995092200048	19950922	00048		1995	9	22	HEEA955657 	4	19950831	G	3416	A30	ENCODER 	ACK 																COCKPIT	ERRATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03										UNIT HAS A ERRATIC OUTPUT.																			 
1995092200049	19950922	00049	SW 	1995	9	22	HEEA955658 	1	19950831	G	6240	2360016901	INDICATOR 			BELL 	206 	206L3 	1182108	SW 										ROTOR	WIRE CHAFED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										ROTOR WIRES CHAFFED AT ROTOR.						1	G	7	1 	3U				H2SW 					 
1995092200050	19950922	00050	EU 	1995	9	22	HEEA955659 	1	19950831	G	2435	23032020	STARTER 			BOLKMS	105 	BO105S 	5626006	EU 										START/GEN NR 2	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	724MB					S756				PILOT TRIED TO START ENGINE (MAX RPM 13% N1) AND TOT CLIMBED MUCH HIGHER THAN NORMAL. ABORTED START AND TRIED TO START 	ENGINE AGAIN, ENGINE WOULD NOT SPIN. SHUT #1 ENGINE DOWN. ENGAGED #2 STARTER AGAIN AND ONLY LOUD ARCING NOISE HEARD. RE	PLACED STARTER GENERATOR AND RETURNED AIRCRAFT TO SERVICE.				1	G	7	2 	3U				H3EU 					 
1995092200051	19950922	00051	SW 	1995	9	22	HEEA955660 	1	19950831	G	2430	51509002R	CONTROL UNIT 			BELL 	212 	212 	1181420	SW 										NR 1 GENERATOR	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5010F					30936				#1 GENERATOR FAILS TO COME ON LINE. RELAY 212-075-199-1 BLOWS IT OUT. REPLACED Q4 TRANSISTOR P/N 05-990044. BENCH CHECK	 OK.					1	G	7	1 	4U				H4SW 					 
1995092200052	19950922	00052	EU 	1995	9	22	HEEA955661 	1	19950831	G	6321	419210	BRAKE HOUSING 			BOLKMS	105 	BO105S 	5626006	EU 										ROTOR CALIPER	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	624MB					S751				ROTOR BRAKE PUCKS REMAIN IN THE EXTENDED POSITION DRAGGING ON ROTOR BRAKE DISC. PUCKS WILL NOT FULLY RETRACT. INSTALLED	 SERVICEABLE ROTOR BRAKE CALIPER ASSEMBLY.					1	G	7	2 	3U				H3EU 					 
1995092200053	19950922	00053		1995	9	22	HEEA955662 	4	19950831	G	3457	0845000000	SKYNAV 5000 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951					2771				LIGHTS GO TOO DIM TO READ DURING DAY LIGHT. COULD NOT VERIFY PROBLEM. UNIT DIMS ACCORDING TO OPERATOR'S MANUAL. UNIT F	UNCTION CHECKS GOOD.					1	G	7	1 	3U				H9EU 					 
1995092200054	19950922	00054		1995	9	22	HEEA955663 	4	19950831	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6559Z					36019				COURSE DIGITIZER STUCK AT 210 AND GLIDE SLOPE NEEDLE INTERMITTENTLY STICKS.						1	G	7	2 	4U				H4SW 					 
1995092200055	19950922	00055		1995	9	22	HEEA955664 	4	19950831	G	2312	40001452502	TRANSCEIVER 		RT138F 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7062X					S793				DOES NOT TRANSMIT WHEN GENERATORS ARE ON; ON GUARD OR MAIN. REPLACED U2 REGULATOR AND L9 COIL. REPAIRED.						1	G	7	2 	3U				H3EU 					 
1995092200056	19950922	00056		1995	9	22	HEEA955665 	4	19950831	G	3455	066107701	RECEIVER 		KDF806 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	89H					760406				BACKGROUND NOISE IN ALL MODES OF OPERATION. FOUND WEAK RECEIVE ON 900KHZ - 1799KHZ BAND. CLEANED MINIMAL CORROSION FROM	 MAIN BOARD. NO HELP. REPLACED Q101 TRANSISTOR ON RECEIVER BOARD. REPAIRED.					1	G	7	2 	3U				H1NE 					 
1995092200057	19950922	00057		1995	9	22	HEEA955666 	4	19950831	G	3452	066106200	TRANSPONDER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3116P					51530				TRANSPONDER INOPERATIVE. TRIED ADJUSTING POWER UP TO SPECS. REPLACED CAVITY OSCILLATOR (V101). REPAIRED. ADJUSTED FRE	QUENCY. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995092200058	19950922	00058	SW 	1995	9	22	HEEA955667 	1	19950831	G	6220	412010179105	CONE 			BELL 	412 	412 	1182202	SW 										LOWER	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2148K	862 				36001				BONDED FABRIC MATERIAL GALLED OR DAMAGED.						1	G	7	2 	4U				H4SW 					 
1995092200059	19950922	00059		1995	9	22	HEEA955669 	4	19950831	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	22608	2550 				33075				CVR UNIT WILL NOT TEST IN PILOT OR COPILOT POSITION.						1	G	7	2 	4U				H4SW 					 
1995092200060	19950922	00060	EU 	1995	9	22	HEEA955670 	1	19950831	G	7332	10593910	SWITCH 			BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					NR 2 ENG PRESS	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	91070					S145				#2 ENGINE DIFFERENTIAL PRESSURE SWITCH WOULD NOT FUNCTION CHECK AS PER BO-105 M & O CHAPTER 62 PAGE 43 PARA. 62-39 ITEM 	#2. REPLACED DIFFERENTIAL PRESSURE SWITCH.					1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995092200061	19950922	00061		1995	9	22	HEEA955671 	4	19950831	G	3421	5040017901	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT ATTITUDE	PLUG LOOSE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2245Y					45751				CANNON PLUG CONNECTOR LOOSE IN CASE. REPLACED WITH SERVICEABLE ATTITUDE INDICATOR.						1	G	7	1 	3U				H2SW 					 
1995092200062	19950922	00062	SW 	1995	9	22	HEEA955672 	1	19950831	G	5320	206033201249	PANEL 			BELL 	206 	206L1 	1182107	SW 										ROOF	REQ REPAIR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5742N					45477				EXTERNAL DOUBLER IS OF INADEQUATE WIDTH TO SUPPORT PADS OF TRANSMISSION STOPS. REMOVE DOUBLER FROM ROOF PANEL. FABRICAT	E NEW DOUBLER FROM 7075-T6 .050" 5.625" X 18". BONDED TO ROOF PANEL USING EA9309.3 NA AND EXISTING TYPE RIVETS. REPAIR	ED AS PER 8110-3 FROM NORDAM REPAIR DIVISION DATED 18 AUGUST 1995 ANDMRR# 08930.				1	G	7	1 	3U				H2SW 					 
1995092200063	19950922	00063	EU 	1995	9	22	HEEA955673 	1	19950831	G	5347	350A77125805	SEAT 			SNIAS 	350 	AS350B2 	8680813	EU 										LOWER RAIL	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	897 				2777				LOWER SEAT SHELL CRACKED WHERE IT ATTACHES TO SLIDE RAILS.						1	G	7	1 	3U				H9EU 					 
1995092200064	19950922	00064	SW 	1995	9	22	HEEA955674 	1	19950831	G	5320	206033100261	SHELL ASSY 			BELL 	206 	206L1 	1182107	SW 										AIRFRAME	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5742N					45477				INBOARD HALF OF TOP CAP ON L/H AND R/H SIDES OF SHELL ASSY CRACKED IN RADIUS. AFT INSERTS FOR R/H FWD AIRFRAME STEP NOT	 INSTALLED THROUGH INTERNAL DOUBLER.					1	G	7	1 	3U				H2SW 					 
1995092200065	19950922	00065	SW 	1995	9	22	HEEA955675 	1	19950831	G	2810	205030173066	CELL 			BELL 	412 	412 	1182202	SW 										RT SADDLE	CHAFES 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N					33010				FWD. TRANSITION AREA HITS AGAINST MOUNTING ANGLE.						1	G	7	2 	4U				H4SW 					 
1995092200066	19950922	00066		1995	9	22	HEEA955676 	4	19950831	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	7128R					36007				CVR WON'T TEST PROPERLY.						1	G	7	2 	4U				H4SW 					 
1995092200067	19950922	00067	SW 	1995	9	22	HEEA955677 	1	19950831	G	5320	206033100261	SHELL ASSY 			BELL 	206 	206L1 	1182107	SW 										LT STEP	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5742N					45477				INSERTS FOR L/H FORWARD FUSELAGE STEP INSTALLED TOO FAR FORWARD. "Z" ANGLE AT BASE OF AFT BROOM CLOSET ANGLES CRACKED O	N UPPER R/H END IN RADIUS. SEVERAL INSERTS NOT INSTALLED FOR CREW SEAT BACK BULKHEAD BASE ANGLES L/H AND R/H SIDESAND F	UEL LINE COVER. INSERTS WERE NOT SENT WITH PANEL (20 EACH 80-005-2-12 AND 8 EACH 80-004-2-12)				1	G	7	1 	3U				H2SW 					 
1995092200068	19950922	00068	GL 	1995	9	22	HEEA955678 	2	19950831	G	7300	230060714101	BELLCRANK 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					ENGINE	WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	2347 				23009				WORN BEARING AND STIFF (BEARING HAD FROZE UP)						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995092200069	19950922	00069	SW 	1995	9	22	HEEA955679 	1	19950831	G	2435	214175150105	GENERATOR 			BELL 	214 	214ST 	1182106	SW 										DC SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				TRIPS OFF LINE - WON'T STAY ON LINE WITH LOAD. (RECEIVED FROM BELL IN OVERHAULED CONDITION)						2	G	7	2 	4U				H10SW 					 
1995092900401	19950929	00401	SW 	1995	9	29	HEEA955714 	1	19950912	G	6220	412010160103	CAP ASSY 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911AR	4976 			A62	33111				M/R HUB LOCKS CRACKED.						1	G	7	2 	4U				H4SW 					 
1995092900402	19950929	00402	NE 	1995	9	29	HEEA955717 	2	19950912	G	7200	0292005220	ENGINE 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1D 		NE 					POWER SECT	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	908 				2777				ENGINE MAKING METAL.						1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995092900403	19950929	00403	CE 	1995	9	29	HEEA955718 	1	19950912	G	7931	903800097	TRANSMITTER 			BEECH 	200 	200CBEECH 	1152926	CE 										OIL PRESS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	500PH					BL29				TRANSMITTER FAILED.						1	L	7	2 	4T				A24CE 					 
1995092900404	19950929	00404		1995	9	29	HEEA955719 	4	19950912	G	3457	0110005400	GPS RECEIVER 	GARMIN 	GPS150 	SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6100R					2862				STATION DOES NOT COME UP, NO SIGNAL STRENGTH.						1	G	7	1 	3U				H9EU 					 
1995092900405	19950929	00405	EU 	1995	9	29	HEEA955720 	1	19950912	G	6410	355A12004008	BLADE 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	350BZ	1227 				2653				HALF MOON BEARINGS WORN. CAP ASSEMBLY WORN.						1	G	7	1 	3U				H9EU 					 
1995092900406	19950929	00406	NE 	1995	9	29	HEEA955721 	2	19950912	G	7210	3024780	GEARBOX 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					COMBINING GR BOX	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K	11909				36001				COMBINING GEARBOX HAS METAL IN OIL.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995092900407	19950929	00407	NE 	1995	9	29	HEEA955722 	2	19950912	G	7200	3017600	ENGINE 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					POWER SECT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	102PH	10531				30899				ENGINE FAILURE.						1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1995092900408	19950929	00408	NE 	1995	9	29	HEEA955723 	2	19950912	G	7210	3024780	GEARBOX 			BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					COMBINING GR BOX	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3131S	8451 				30953				COMBINING GR BOX MAKING METAL.						1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1995092900409	19950929	00409	EU 	1995	9	29	HEEA955724 	1	19950912	G	6730	7004109901	ACTUATOR ASSY 			BOLKMS	117 	BK117B2 	5626013	EU 										PITCH & ROLL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	132AE					7238				TORN BOOT AND TROUBLESHOOTING, RATCHETY MOVEMENT.						1	G	7	2 	3U			NC	H13EU 					 
1995092900410	19950929	00410	EU 	1995	9	29	HEEA955725 	1	19950912	G	5220	350A25109521	ROD 			SNIAS 	350 	AS350B2 	8680813	EU 										JETTISON DOOR	BINDING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	855 				2777				R/H DOOR JETTISON ROD BINDING AND BENDING WHEN CLOSING DOOR.						1	G	7	1 	3U				H9EU 					 
1995092900411	19950929	00411	NE 	1995	9	29	HEEA955726 	1	19950912	G	7333	PC820101	SIGNAL CONDITION			SKRSKY	S76 	S76A 	8143006	NE 										NR 1 ENG FUEL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4253S					760035				#1 ENGINE FUEL FLOW UNRELIABLE. FLUCTUATES FROM 0-500.						1	G	7	2 	3U				H1NE 					 
1995092900412	19950929	00412	SW 	1995	9	29	HEEA955727 	1	19950912	G	5320	206033100261	SHELL ASSY 			BELL 	206 	206L1 	1182107	SW 										RT CONSOLE	CRACKED ANGLE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										SHELL ASSEMBLY HAS CRACKED ANGLE FOR R/H CENTER CONSOLE SKIN AT AFT END, SHELL ASSY IS ALSO 3/8" TOO SHORT ON FORWARD E	ND WHICH WILL NOT PROVIDE FOR PROPER EDGE DISTANCE ON TAIL ROTOR BELL CRANK CASTING RIVETS AND BOLTS.					1	G	7	1 	3U				H2SW 					 
1995092900413	19950929	00413	NE 	1995	9	29	HEEA955728 	2	19950912	G	7320	6038T62P24	HMU 			BELL 	214 	214ST 	1182106	SW 	GE 	CT7TS 	CT72A 	30030	NE 					ENGINE	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				NO FUEL DURING START.						2	G	7	2 	4U	4	U		H10SW 	E8NE				 
1995092900414	19950929	00414	EU 	1995	9	29	HEEA955729 	1	19950912	G	2822	2C273	CARTRIDGE 			BOLKMS	105 	BO105CBS 	5626008	EU 										BOOST PUMP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										BOOST PUMP UNIT POPPED THE CIRCUIT ON THE TEST STAND.						1	G	7	2 	3U			NC	H3EU 					 
1995092900415	19950929	00415	SW 	1995	9	29	HEEA955730 	1	19950912	G	2820	L88010491	VALVE 			BELL 	412 	412 	1182202	SW 										FUEL SYS	TRIPS BREAKER 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2258F	689 				33073				FUEL VALVE CIRCUIT BREAKER TRIPPED.						1	G	7	2 	4U				H4SW 					 
1995092900416	19950929	00416		1995	9	29	HEEA955731 	4	19950912	G	2210	7690001802106	ACTUATOR 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	CHATTERING 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	792CH	3313 				760193				AFCS ACTUATOR CHATTERING.						1	G	7	2 	3U				H1NE 					 
1995092900417	19950929	00417		1995	9	29	HEEA955732 	4	19950912	G	3416	5035P2P44	ENCODER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546K					760082				ENCODER READS 500 FEET LOW OUT OF TOLERANCE.						1	G	7	2 	3U				H1NE 					 
1995092900418	19950929	00418	NE 	1995	9	29	HEEA955733 	1	19950912	G	7722	7645001076106	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										POWER TURB TEMP	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546K					760082				INDICATOR READS 500 DEGREES LOW.						1	G	7	2 	3U				H1NE 					 
1995092900419	19950929	00419	EU 	1995	9	29	HEEA955734 	1	19950912	G	2435	230321823	STATORS 			AEROSP	AS355 	AS355F1 	8680810	EU 										START/GEN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										WHEN INSTALLING ON STARTER GENERATOR TERMINAL THE FIELD LEAD BROKE OFF. REMOVED FROM STARTER GEN. P/N 150SG117Q, S/N 12	60.					1	G	7	2 	3U				H11EU 					 
1995092900420	19950929	00420	SW 	1995	9	29	HEEA955735 	1	19950912	G	2435	230321827	FIELD ASSY 			BELL 	206 	206L3 	1182108	SW 										START/GEN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										FIELD SHOES ARE RUBBING ON ARMATURE. REMOVED FROM STARTER GEN. P/N 23081-018, S/N 4902.						1	G	7	1 	3U				H2SW 					 
1995092900421	19950929	00421	SW 	1995	9	29	HEEA955736 	1	19950912	G	5330	206031100681	SHELL ASSY 			BELL 	206 	206L1 	1182107	SW 										LT & RT SIDES	SEPARATION 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										OUTER SKIN WAVY IN L/H AND R/H SIDES. SKIN WAS STEP BENT INSTEAD OF ROLLED. SEVERAL SMALL AREAS OF SEPARATION ON OUTER	 AND INNER SKIN AND ON TOP CAPS. ANGLES FOR PILOT AND CO-PILOT FWD. KICK PANELS HAVE IMPROPER CONTOUR AND DO NOT FIT TU	B CONTOUR WHEN POSITIONED WHERE NEEDED.				1	G	7	1 	3U				H2SW 					 
1995092900422	19950929	00422	SW 	1995	9	29	HEEA955737 	1	19950912	G	5330	205032814051	PANEL ASSY 			BELL 	212 	212 	1181420	SW 										BOOM STA 101	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										CORE ON PANEL IS TOO NARROW LEAVING APPROXIMATELY 1/2" TO 5/8" SPACE BETWEEN CORE TRANSITION AREA AND LOWER LONGERON FLA	NGES ON BOTH L/H AND R/H SIDES. PANEL OUTER DIMENSION IS TOO SHORT, NOT LEAVING ENOUGH MATERIAL TO GET PROPER EDGEDISTA	NCE ON RIVETS FOR TOP FLANGES OF L/H AND R/H LONGERONS. CORE AREAS ON INSIDE OF PANEL ARE MISPOSITIONED CAUSING PANEL T	O NOT FIT BETWEEN ATTACHMENT FLANGES AT BOOM STATION 101.38.			1	G	7	1 	4U				H4SW 					 
1995092900423	19950929	00423	SW 	1995	9	29	HEEA955738 	1	19950912	G	7810	212061201011	EJECTOR 			BELL 	412 	412 	1182202	SW 										EXHAUST	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6559Z					36019				EJECTOR CRACKED ON RINGS. CRACK BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995092900424	19950929	00424	NE 	1995	9	29	HEEA955739 	1	19950913	G	2435	200SGL1064	ARMATURE 			SKRSKY	S76 	S76A 	8143006	NE 										GENERATOR	SHORTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1546K	110 				760082				GRINDING NOISE AND NO VOLTAGE OUTPUT. INSPECTED BY ACCESSORY SHOP AND FOUND GENERATOR S/N 1260 HAD NO VOLTAGE OUTPUT AS	 RECEIVED. DISASSEMBLED AND INSPECTED, FOUND ARMATURE WAS SHORTED OUT.					1	G	7	2 	3U				H1NE 					 
1995092900425	19950929	00425	SW 	1995	9	29	HEEA955740 	1	19950913	G	7712	412075205101	TRANSMITTER 			BELL 	412 	412 	1182202	SW 										ENG TORQUE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				ENGINE NOT MAKING POWER, TRANSMITTER READS LOW.						1	G	7	2 	4U				H4SW 					 
1995092900426	19950929	00426	SW 	1995	9	29	HEEA955741 	1	19950913	G	5320	206033322003A	PANEL ASSY 			BELL 	206 	206L1 	1182107	SW 										OIL COOLER DECK	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										TRANS OIL LINES THROUGH OIL COOLER DECK MISSING FLANGES FOR GROMETS. TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW 					 
1995092900427	19950929	00427	SW 	1995	9	29	HEEA955742 	1	19950913	G	6730	212076005101	SERVO 			BELL 	212 	212 	1181420	SW 										CYCLIC	LEAKS 	E			HEEA	K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	03	27805	12244				31106				CYCLIC SERVO LEAKS FROM PILOT VALVE SEALS.						1	G	7	1 	4U				H4SW 					 
1995092900428	19950929	00428	NE 	1995	9	29	HEEA955743 	2	19950913	G	7240	414302017	HOUSING 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					GP SHROUD	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										GP SHROUD PILOT WAS MACHINED BELOW SPECS.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995092900429	19950929	00429	EU 	1995	9	29	HEEA955744 	1	19950913	G	6340	KDW02	WARNING BOX 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT PANEL	DEFECTIVE 	E			HEEA	K				NONE 				N			FALSE WARNING 			CR	CRUISE 	1			SW	03	7170D					S840				RPM WARNING LIGHT COMING ON INTERMITTENTLY IN CRUISE FLIGHT.						1	G	7	2 	3U				H3EU 					 
1995092900430	19950929	00430	SW 	1995	9	29	HEEA955745 	1	19950913	G	5320	205030280127	DECK ASSY 			BELL 	412 	412 	1182202	SW 										TRANSITION AREA	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2298Z					33077				PANEL SEPARATED FWD. INBOARD SIDE APPROXIMATELY 3 X 8 AT TRANSITION AREA.						1	G	7	2 	4U				H4SW 					 
1995092900431	19950929	00431	SW 	1995	9	29	HEEA955746 	1	19950913	G	5320	205030280127	DECK ASSY 			BELL 	412 	412 	1182202	SW 										ENGINE AREA	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3893N					33010				ENGINE WORK DECK SEPARATED BEYOND LIMITS.						1	G	7	2 	4U				H4SW 					 
1995092900432	19950929	00432		1995	9	29	HEEA955747 	4	19950913	G	3414	8000A	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT AIR SPD	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2775A					45297				NEEDLE INDICATES 6 MPH LOW AT 60 MPH.						1	G	7	1 	3U				H2SW 					 
1995092900433	19950929	00433	SW 	1995	9	29	HEEA955748 	1	19950913	G	7810	212061202009	DUCT ASSY 			BELL 	412 	412 	1182202	SW 										LT EXH	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7128R					36007				DUCT ASSY CRACKED AT BOTH INBOARD CORNERS.						1	G	7	2 	4U				H4SW 					 
1995092900434	19950929	00434	EU 	1995	9	29	HEEA955749 	1	19950913	G	6510	1053180301	SHAFT 			BOLKMS	105 	BO105S 	5626006	EU 										T/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3535T					S113				CORROSION AT BEARING SEAT.						1	G	7	2 	3U				H3EU 					 
1995092900435	19950929	00435	SW 	1995	9	29	HEEA955750 	1	19950913	G	5530	206020113117	FIN ASSY 			BELL 	206 	206L1 	1182107	SW 										V STAB	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										MOUNTING INSERTS MIS-LOCATED. NUT PLATES NOT INSTALLED ON PAIRING RING. TOP TIP OF FIN NOT MODIFIED FOR ANT. NEEDS MOU	NT BRKT INSTALLED.					1	G	7	1 	3U				H2SW 					 
1995092900436	19950929	00436	SW 	1995	9	29	HEEA955752 	1	19950914	G	7722	206075680103	INDICATOR 			BELL 	206 	206B 	1181511	SW 										COCKPIT TOT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	FGHRS					3000				WHEN POWER IS REMOVED AT 800 DEGREES, NEEDLE DOES NOT RETURN TO ZERO.						1	G	7	1 	3U				H2SW 					 
1995092900437	19950929	00437	NE 	1995	9	29	HEEA955753 	1	19950914	G	7810	7630507003044	EJECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										EXH	PARTS MISSING 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3122H					760233				EJECTOR MISSING PIECES.						1	G	7	2 	3U				H1NE 					 
1995092900438	19950929	00438		1995	9	29	HEEA955754 	4	19950914	G	3416	120120461210	ALTIMETER 			BELL 	206 	206L1 	1182107	SW 										COCKPIT	READS HIGH 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748Q					45499				NEEDLE INDICATES 40 FEET HIGH AT ZERO.						1	G	7	1 	3U				H2SW 					 
1995092900439	19950929	00439	SW 	1995	9	29	HEEA955755 	1	19950914	G	7714	412075010109	INDICATOR 			BELL 	412 	412 	1182202	SW 										TRIPLE TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22608					33075				NEEDLES SPLIT, #1 AND #2 NEEDLES.						1	G	7	2 	4U				H4SW 					 
1995092900440	19950929	00440		1995	9	29	HEEA955756 	4	19950914	G	2562	ELT910	ELT 	NARCO 		BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893S					33022				WHEN ARM SWITCH IS "ON" UNIT IS ACTIVATED AND WILL NOT TURN OFF.						1	G	7	2 	4U				H4SW 					 
1995092900441	19950929	00441	SW 	1995	9	29	HEEA955757 	1	19950914	G	6220	412010179105	CONE LWR 		412010100193	BELL 	412 	412 	1182202	SW 										M/R HUB	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22608	2937 			AAD00027	33075				BONDED FABRIC MATERIAL GALLED AND WORN.						1	G	7	2 	4U				H4SW 					 
1995092900442	19950929	00442	SW 	1995	9	29	HEEA955758 	1	19950914	G	7722	206375006101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5012V	312 				45200				NEEDLE OSCILLATES AT 610 DEGREES.						1	G	7	1 	3U				H2SW 					 
1995092900443	19950929	00443	SW 	1995	9	29	HEEA955759 	1	19950914	G	5620	M2043001	SLIDING WINDOW 			BELL 	412 	412 	1182202	SW 										DOOR	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893N					33010				THE WINDOW IS TOO WIDE; IT DOESN'T FIT BETWEEN DOOR TRACKS.						1	G	7	2 	4U				H4SW 					 
1995092900444	19950929	00444	EU 	1995	9	29	HEEA955760 	1	19950914	G	6310	4638202007	CLUTCH 		4638001004 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	CAGE WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	205BB	1317 			1078	1234				INNER CAGE WORN BEYOND LIMITS ON 2 EACH CLUTCHES. REPLACED WITH SERVICEABLE CLUTCHES. SEE MMIR# 5761 FOR OTHER CLUTCH 	INFORMATION.					1	G	7	2 	3U				H3EU 					 
1995092900445	19950929	00445	EU 	1995	9	29	HEEA955761 	1	19950914	G	6310	4638202007	CLUTCH 		4638001004 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	205BB	1238 			1078	1234				INNER CAGE WORN BEYOND LIMITS ON 2 EACH CLUTCHES. REPLACED WITH SERVICEABLE CLUTCHES. SEE MMIR# 5760 FOR OTHER CLUTCH 	INFORMATION.					1	G	7	2 	3U				H3EU 					 
1995092900446	19950929	00446	SW 	1995	9	29	HEEA955762 	1	19950914	G	2430	A7002C7	RELAY 			BELL 	206 	206B 	1181511	SW 										REVERSE CURRENT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268X					3607				GENERATOR MOTORS AFTER ENGINE SHUT DOWN. REPLACED WITH SERVICEABLE RELAY.						1	G	7	1 	3U				H2SW 					 
1995092900447	19950929	00447	SW 	1995	9	29	HEEA955763 	1	19950914	G	5320	206033110239	STIFFENER 			BELL 	206 	206L1 	1182107	SW 										FUSELAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748Q					45499				CRACKED COMPLETELY IN TWO 4 3/8" FROM TOP OF STIFFENER. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H2SW 					 
1995092900448	19950929	00448	SW 	1995	9	29	HEEA955765 	1	19950914	G	5302	206031329103S	ATTACH FITTING 			BELL 	206 	206L1 	1182107	SW 										TAIL BOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3178K					45765				L/H UPPER T/B ATTACH FITTING CRACKED AT INBOARD FLANGE (IN TWO) 1 1/4" FROM AFT EDGE OF FITTING. REPLACED USING T/B ALIG	NMENT FIXTURE.					1	G	7	1 	3U				H2SW 					 
1995092900449	19950929	00449	SW 	1995	9	29	HEEA955766 	1	19950914	G	5311	206032308103S	FRAME 			BELL 	206 	206L3 	1182108	SW 										FUSELAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81671					51301				FRAME IS CRACKED AT BOTH TOP ATTACHMENT FITTINGS. REPLACED WITH SERVICEABLE FRAME.						1	G	7	1 	3U				H2SW 					 
1995092900450	19950929	00450	EU 	1995	9	29	HEEA955767 	1	19950914	G	6720	116488P	BEARING 		10513141 	BOLKMS	105 	BO105S 	5626006	EU 										T/R PC LINK	WORN 	E			HEEA	O				OTHER 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5418A					S800				BEARING HAS EXCESSIVE AXIAL WEAR (.4MM MAX) REPLACED WITH SERVICEABLE T/R P/C LINK.						1	G	7	2 	3U				H3EU 					 
1995092900451	19950929	00451	SW 	1995	9	29	HEEA955768 	1	19950914	G	5320	214031253109	CABIN WALL 			BELL 	214 	214ST 	1182106	SW 										PYLON	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N	5323 				28106				THE .020 S/STEEL OVERLAY FROM PREVIOUS REPAIR DATED NOV. 88 CRACKED AND PYLON WALL CRACKED 1/8" PAST PREVIOUS STOP DRILL	 HOLE. STOP DRILL NEW CRACK AND OVERLAID WITH .032 S/STEEL AS PER NEW REPAIR IN 8110-23551 DATED 25 MAY 1995.					2	G	7	2 	4U				H10SW 					 
1995092900452	19950929	00452	EU 	1995	9	29	HEEA955769 	1	19950914	G	7714	65201008	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										TRIPLE TACH	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5029H	360 				S670				#2 NEEDLE WILL NOT INDICATE. SENT TO FIVE STAR TECHNOLOGY, INC. FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H3EU 					 
1995092900453	19950929	00453	SW 	1995	9	29	HEEA955770 	1	19950915	G	5210	1008402	LATCH ASSY 			BELL 	230 	230 	1182149	SW 										DOOR LT	MIS INSTALLED 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	230UN					23009				THE LATCH SLIDER INSTALLED UPSIDE DOWN. THE TWO PIN HOLE SIDE OF SLIDER SHOULD BE ON THE BOTTOM OF THE LATCH.						1	G	7	2 	3U			NC	H9SW 					 
1995092900454	19950929	00454	SW 	1995	9	29	HEEA955771 	1	19950915	G	6220	206011149105	YOKE 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R HUB	BEARINGS FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2133X	1190 			A2361	45634				BEARING JOURNALS ON YOKE BREAKING DOWN, ALONG WITH FOUR BEARINGS P/N 206-011-118-001. T.T. ON ALL PARTS 1189:55. REPLA	CEMENT PART INFORMATION FOR BEARINGS (4 EACH) P/N 206-011-118-001					1	G	7	1 	3U				H2SW 					 
1995092900474	19950929	00474	SW 	1995	9	29	HEEA955772 	1	19950918	G	6321	40004244	BRAKE ASSY 			BELL 	230 	230 	1182149	SW 										ROTOR	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2347 				23009				ROTOR BRAKE PUCK BROKE AND PUCK PISTON RUBBED DISC.						1	G	7	2 	3U			NC	H9SW 					 
1995092900475	19950929	00475	SW 	1995	9	29	HEEA955773 	1	19950918	G	6220	222031613103	LIFT LINK ASSY 			BELL 	230 	230 	1182149	SW 										M/R	BEARING FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2364 				23009				LIFT LINK ASSY LOWER BEARING SEPARATED FROM RUBBER.						1	G	7	2 	3U			NC	H9SW 					 
1995092900476	19950929	00476	SW 	1995	9	29	HEEA955775 	1	19950918	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2124Z	1723 				45646				BLADE HAS SEVERAL AREAS OF INNER GRANULAR CORROSION ON THE LEADING EDGE SPAR NEAR THE INBOARD SECTION OF THE BLADE.						1	G	7	1 	3U				H2SW 					 
1995092900477	19950929	00477	SW 	1995	9	29	HEEA955776 	1	19950918	G	2435	214060056001	STARTER 			BELL 	214 	214ST 	1182106	SW 										START/GEN	BURNT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M	1244 				28102				STARTER BURNT UP.						2	G	7	2 	4U				H10SW 					 
1995092900478	19950929	00478	SW 	1995	9	29	HEEA955777 	1	19950918	G	2436	222375060115	REGULATOR 			BELL 	230 	230 	1182149	SW 										DC VOLTS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	115 				23009				GENERATOR LIGHT REMAINS ON. VOLTAGE REG DEFECTIVE.						1	G	7	2 	3U			NC	H9SW 					 
1995092900479	19950929	00479	SW 	1995	9	29	HEEA955781 	1	19950920	G	6230	206040535105	MAST 			BELL 	206 	206L1 	1182107	SW 										M/R	DAMAGED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										MAST INCOMPLETE AND DAMAGE TO LOWER RACE.						1	G	7	1 	3U				H2SW 					 
1995092900480	19950929	00480	SW 	1995	9	29	HEEA955783 	1	19950920	G	5260	BYLM5090185	ARMATURE 		SYLC502283 	BELL 	412 	412 	1182202	SW 										STEP	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2261D	162 			1578	33076				STEP ACTUATOR POPS CIRCUIT BREAKER. INSPECTED AND BENCH CHECKED AS RECEIVED BY THE ACCESSORY SHOP. UNIT WOULD NOT RESP	OND TO TEST. ARMATURE BURNT.					1	G	7	2 	4U				H4SW 					 
1995092900481	19950929	00481	SW 	1995	9	29	HEEA955784 	1	19950920	G	6230	412010366105	MAST ASSY 			BELL 	412 	412 	1182202	SW 										M/R	SEAL LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	911AR	4976 				33111				INSPECT AND REPAIR DUE TO SEAL LEAKING. REPLACEMENT PART INFORMATION: P/N 29810-8056, SLEEVE, P/N 412-340-001-101, S	EAL,					1	G	7	2 	4U				H4SW 					 
1995092900482	19950929	00482	SW 	1995	9	29	HEEA955785 	1	19950920	G	6230	412010405109	LINK 			BELL 	412 	412 	1182202	SW 										M/R MAST	WORN BEARINGS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911AR	1105 				33111				REPAIR TO REPLACE WORN BEARINGS. REPLACEMENT PART INFORMATION LISTED BELOW: P/N 412-010-418-101, QTY 2 P/N 412-010-41	8-105, QTY 2, P/N412-010-423-103, QTY 2, P/N 412-010-424-103, QTY 4, P/N 412-010-427-101, QTY 2,					1	G	7	2 	4U				H4SW 					 
1995092900483	19950929	00483	EU 	1995	9	29	HEEA955786 	1	19950921	G	3340	356H2802	POWER SUPPLY 			SNIAS 	350 	AS350B2 	8680813	EU 										STROBE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	684 				2771				LIGHT COMES ON DIM, BUT WOULD NOT FLASH.						1	G	7	1 	3U				H9EU 					 
1995092900484	19950929	00484	EU 	1995	9	29	HEEA955787 	1	19950921	G	6510	1053180301	SHAFT 			BOLKMS	105 	BO105S 	5626006	EU 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5418A					S800				OUTPUT SHAFT WORN IN AREA OF OUTBOARD BOOT.						1	G	7	2 	3U				H3EU 					 
1995092900485	19950929	00485	EU 	1995	9	29	HEEA955788 	1	19950921	G	6410	10531980	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										T/R	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81992	1914 				S827				SEPARATION OF RUBBER NEAR END CAP. REPLACED WITH 2 EACH NEW BLADES. S/N 009 & 011						1	G	7	2 	3U				H3EU 					 
1995092900486	19950929	00486	SW 	1995	9	29	HEEA955789 	1	19950921	G	2435	214060056103	STARTER 			BELL 	214 	214ST 	1182106	SW 										START/GEN	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8045T					28101				STARTER DROPS OUT AT 10%.						2	G	7	2 	4U				H10SW 					 
1995092900487	19950929	00487	SW 	1995	9	29	HEEA955790 	1	19950921	G	2432	32007001	BATTERY 			BELL 	206 	206L3 	1182108	SW 										DC SYS	WEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8590X					51494				BATTERY WEAK. INSPECTED BY ACCESSORY SHOP AND FOUND BATTERY WILL NOT PASS CAPACITY TEST.						1	G	7	1 	3U				H2SW 					 
1995092900488	19950929	00488	SW 	1995	9	29	HEEA955791 	1	19950921	G	2432	3055401C	BATTERY 			BELL 	206 	206L1 	1182107	SW 										DC SYS	WEAK 	E			HEEA	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	2758N					45267				BATTERY HOT LIGHT. INSPECTED BY ACCESSORY SHOP: VOLTAGE READING TAKEN AS RECEIVED. FOUND BATTERY WEAK.						1	G	7	1 	3U				H2SW 					 
1995092900489	19950929	00489	EU 	1995	9	29	HEEA955792 	1	19950921	G	6210	10515150	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911BR	5924 				S719				NOSE AND NECK SHELL CRACKS.						1	G	7	2 	3U				H3EU 					 
1995092900490	19950929	00490	EU 	1995	9	29	HEEA955794 	1	19950921	G	2820	209072433105	VALVE 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL SYS	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911HM					S683				VALVE SHORTED ELECTRICALLY. INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND SOLENOID IS SHORTED OUT.						1	G	7	2 	3U				H3EU 					 
1995092900491	19950929	00491		1995	9	29	HEEA955796 	4	19950921	G	3453	25410036	LORAN 		7000RCU 	BELL 	412 	412 	1182202	SW 										COCKPIT	ERROR CODE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				DISPLAYS ERROR CODE.						1	G	7	2 	4U				H4SW 					 
1995092900492	19950929	00492		1995	9	29	HEEA955797 	4	19950921	G	3453	25410038	LORAN 		7000CDU 	BELL 	412 	412 	1182202	SW 										COCKPIT	LIGHTS INOP 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22608					33075				4 LED LIGHTS INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995092900493	19950929	00493		1995	9	29	HEEA955798 	4	19950921	G	3451	066106902	INDICATOR 		KDI573 	BELL 	412 	412 	1182202	SW 										COCKPIT DME	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S					36002				INDICATOR WILL NOT COME ON. DIGITS WERE A LITTLE DIM. REPLACED WEAK DISPLAY DS901, FADED DISPLAY LENS AND WEAK V901 PHO	TOCELL. UNIT BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995092900494	19950929	00494	SW 	1995	9	29	HEEA955799 	1	19950921	G	2436	206075447007	REGULATOR 			BELL 	206 	206L1 	1182107	SW 										DC VOLTS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5012V					45200				TROUBLESHOOTING GENERATOR TURNING AS A MOTOR AT 15-20% N1 AFTER SHUTDOWN.						1	G	7	1 	3U				H2SW 					 
1995092900495	19950929	00495	SW 	1995	9	29	HEEA955800 	1	19950921	G	6330	206033506101	RESTRAINT 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6610Y					51419				ROLL STAKE BEARING WORN. REPLACED RESTRAINT ASSY.						1	G	7	1 	3U				H2SW 					 
1995092900496	19950929	00496	GL 	1995	9	29	HEEA955801 	2	19950921	G	7321	252473830	FUEL CONTROL 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					ENGINE	LEAKS 	E			HEEA	K				NONE 				K			FLUID LOSS 			NR	NOT REPORTED 	1			SW	03	2249Z	9574 				45753				FUEL LEAKS FROM BY-PASS VALVE RETENTION PLATE. REPLACED WITH SERVICEABLE FUEL CONTROL.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995092900497	19950929	00497	GL 	1995	9	29	HEEA955802 	2	19950921	G	7323	252467710	GOVERNOR 			BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	10778	10801				45391				GOVERNOR LEVER STIFF. REPLACED WITH SERVICEABLE GOVERNOR.						1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995092900498	19950929	00498		1995	9	29	HEEA955803 	4	19950921	G	3414	117940471	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT AIR SPD	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	191BK					7146				NEEDLE WENT TO ZERO.						1	G	7	2 	3U				H13EU 					 
1995092900499	19950929	00499		1995	9	29	HEEA955805 	4	19950921	G	3457	0845000000	SKYNAV 5000 			AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5786D	116 				5113				NO FACE LIGHTS AND COULD NOT TURN OFF.						1	G	7	2 	3U				H11EU 					 
1995092900500	19950929	00500		1995	9	29	HEEA955808 	4	19950921	G	3457	0110010602	GPS 	GARMIN 	GPS165 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545K					760047				WILL NOT STAY IN AUTO SEQUENCE MODE. WHEN AIRCRAFT IS MOVED, GOES TO HOLD MODE AND STAYS.						1	G	7	2 	3U				H1NE 					 
1995092900501	19950929	00501	SW 	1995	9	29	HEEA955812 	1	19950922	G	6320	357950111452	SHAFT SPLINE 		206040004115	BELL 	206 	206L 	1181522	SW 										TRANSMISSION	WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7077B	1593 			A236	52037				AT TRANSMISSION 1500 HOUR INSPECTION FOUND SHAFT SPLINES WORN BEYOND LIMITS. REPLACED WITH NEW SHAFT.						1	G	7	1 	3U				H2SW 					 
1995100600172	19951006	00172	NE 	1995	10	6	HEEA955813 	1	19950926	G	6210	7615009043051	TIP CAP 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5426U					760167				CRACKED ABRASION STRIP WITH MULTIPLE BRANCH. IT ALSO HAS EXCESSIVE EROSION OF FIBERGLASS NEAR THE TIP.						1	G	7	2 	3U				H1NE 					 
1995100600173	19951006	00173	SW 	1995	10	6	HEEA955814 	1	19950926	G	5320	206031100681	SHELL ASSY 			BELL 	206 	206B 	1181511	SW 										LT RT PANELS	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										DOUBLER ANGLES ON AFT SIDE OF L/H AND R/H AFT KICK PANELS ARE MISLOCATED AS MARKED ON SUPPORT ANGLES. SUPPORT ANGLES FO	R FWD KICK PANELS DO NOT FIT CONTOUR OF TUB PROPERLY. PANEL IS TOO WIDE AT CENTER AND AFT ENDS TO FIT AIRFRAME.					1	G	7	1 	3U				H2SW 					 
1995100600174	19951006	00174		1995	10	6	HEEA955815 	4	19950926	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	2014K	1310 				33020				CVR WILL NOT TEST.						1	G	7	2 	4U				H4SW 					 
1995100600175	19951006	00175		1995	10	6	HEEA955816 	4	19950926	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	1546G	2236 				760076				CVR DOES NOT TEST.						1	G	7	2 	3U				H1NE 					 
1995100600176	19951006	00176	SW 	1995	10	6	HEEA955817 	1	19950926	G	5320	206031302227	SUPPORT 			BELL 	206 	206B 	1181511	SW 										FUSELAGE	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	28ED					2498				PILOT HOLES DO NOT LINE UP WITH EXISTING ORIGINAL HOLES ON AIRFRAME CROSSTUBE TUNNEL AND FORWARD BAGGAGE COMPARTMENT PAN	EL.					1	G	7	1 	3U				H2SW 					 
1995100600177	19951006	00177	EU 	1995	10	6	HEEA955818 	1	19950929	G	6310	4638202007	CLUTCH 		4638001004 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	LOCKED UP 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7170D	957 			1291	S840				CLUTCH LOCKED UP AND CAUSED DAMAGE TO PINION AND BEVEL GEAR. (RIGHT SIDE) REPLACED DAMAGED CLUTCH WITH SERVICEABLE CLUT	CH.					1	G	7	2 	3U				H3EU 					 
1995100600178	19951006	00178	EU 	1995	10	6	HEEA955819 	1	19950929	G	6310	4638202007	CLUTCH 		4638001001 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	LOCKED UP 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	9190Y	1182 			306	S669				CLUTCH LOCKED UP AND CAUSED DAMAGE TO PINION AND F/W SHAFT. REPLACED CLUTCH WITH SERVICEABLE CLUTCH.						1	G	7	2 	3U				H3EU 					 
1995100600179	19951006	00179	SW 	1995	10	6	HEEA955820 	1	19950929	G	6330	222330620103	BEARING 			BELL 	230 	230 	1182149	SW 										M/R MOUNT	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	509 				23009				ROLL STAKE BEARING WORN.						1	G	7	2 	3U			NC	H9SW 					 
1995100600180	19951006	00180	SW 	1995	10	6	HEEA955821 	1	19950929	G	6230	222010497109	LEVER 			BELL 	222 	222 	1182122	SW 										COLLECTIVE	MIS INSTALLED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										RECEIVED ASSY NEW AND OBSERVED COLLECTIVE PIN P/N 222-010-456-007 INSTALLED BACKWARDS. ADVISED TO INSTALL CORRECTLY. O	N REMOVAL FOUND A LARGE GOUGE. MEASURED AT 1.0025 OUT OF MFG SPECS.					1	G	7	2 	3U				H9SW 					 
1995101300136	19951013	00136	GL 	1995	10	13	HEEA955824 	2	19951004	G	7250	23030974	SPLINE ADAPTER 		23035128 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					TURBINE	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5426U				CAT90185	760167	CAE890469S			RECEIVING INSPECTION OF NEW, NEVER INSTALLED SPLINE ADAPTER INDICATED I.D. MANUFACTURED .0005" OVER MAX B.P. SPECS OF .6	565" ADAPTER MEASURES .657. INSTALLED NEW SPLINE ADAPTER.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995101300137	19951013	00137	GL 	1995	10	13	HEEA955827 	2	19951004	G	7230	23008090	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	31219	663 			CAC90152	760230	CAE890432S			ENGINE REMOVED DUE TO CRACKED SCROLL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS	 ON SPUR ADAPTER GEARSHAFT FORWARD & AFT SPLINES. NEW PART INSTALLED.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995101300138	19951013	00138	GL 	1995	10	13	HEEA955828 	2	19951004	G	7230	23056634	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911MJ	810 			CAC90484	760231	CAE890499S			ENGINE REMOVED DUE TO CRACKED SCROLL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS	 ON SPUR ADAPTER GEARSHAFT FWD & AFT SPLINES. NEW PART INSTALLED.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995101300139	19951013	00139	GL 	1995	10	13	HEEA955829 	2	19951004	G	7230	23008090	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1545K	840 			CAC90527	760047	CAE890639S			ENGINE REMOVED DUE TO 1750 HOUR INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND 	LIMITS ON SPUR ADAPTER GEARSHAFT AFT SPLINES. NEW PART INSTALLED.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995101300140	19951013	00140		1995	10	13	HEEA955830 	4	19951005	G	3453	066402600	RECEIVER 		KLN88 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT LORAN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	9190Y					S669				WILL NOT ADJUST WITH LEFT HAND KNOB.						1	G	7	2 	3U				H3EU 					 
1995101300141	19951013	00141	NE 	1995	10	13	HEEA955831 	1	19951005	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	31219					760230				BLADE CRACK WITH MULTIPLE BRANCHES ON THE LEADING EDGE ABRASION STRIP.						1	G	7	2 	3U				H1NE 					 
1995101300142	19951013	00142	EU 	1995	10	13	HEEA955832 	1	19951005	G	6220	350A31190703	STARFLEX 			AEROSP	AS355 	AS355F 	8680806	EU 										M/R	BUSHING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5780D	548 				5071				STARFLEX ARM BUSHINGS WORN BEYOND LIMITS.						1	G	7	2 	3U				H11EU 					 
1995101300143	19951013	00143	EU 	1995	10	13	HEEA955833 	1	19951005	G	6220	350A31190703	STARFLEX 			AEROSP	AS355 	AS355F1 	8680810	EU 										M/R	BUSHING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5793Y	965 				5141				STARFLEX THREE ARM BUSHINGS WORN BEYOND LIMITS.						1	G	7	2 	3U				H11EU 					 
1995101300144	19951013	00144	EU 	1995	10	13	HEEA955834 	1	19951005	G	6210	10587214	BLADE 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	54197	7683 				S805				BLADE NOSE AND NECK SHELL CRACK IN THE ROOT AREA. FIBERGLASS IN THE ROOT AREA ALSO DISCOLORED AND SEPARATED FROM THE RO	VINGS.					1	G	7	2 	3U				H3EU 					 
1995101300145	19951013	00145		1995	10	13	HEEA955835 	4	19951005	G	3442	MI5852013	INDICATOR 		P4001 	BELL 	212 	212 	1181420	SW 										RADAR	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3131S					30953				INDICATOR HAS NO DISPLAY.						1	G	7	1 	4U				H4SW 					 
1995101300146	19951013	00146	SW 	1995	10	13	HEEA955836 	1	19951005	G	6220	206011132113A	GRIP 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R HUB	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5745S	2620 			HB400	45491				GRIPS WORN IN BOTTOM OF RETAINER BORE.						1	G	7	1 	3U				H2SW 					 
1995101300147	19951013	00147		1995	10	13	HEEA955837 	4	19951005	G	3434	066107800	RECEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT MARKER	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				MARKER BEACON DAMAGED KA35A ASSEMBLY. MARKER BEACON INOPERATIVE AND HAS CONSTANT TONE WITH NO SIGNAL APPLIED.						1	G	7	2 	4U				H4SW 					 
1995101300148	19951013	00148		1995	10	13	HEEA955838 	4	19951005	G	3453	066402600	RECEIVER 		KLN88 	BELL 	206 	206L3 	1182108	SW 										COCKPIT LORAN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6610E					51424				INSPECTED UNIT AND FOUND THAT R/H INNER KNOB PULLS OUT AND R/H OUTER KNOB LOCKS UP.						1	G	7	1 	3U				H2SW 					 
1995101300149	19951013	00149	SW 	1995	10	13	HEEA955839 	1	19951005	G	6320	L15231487	O-RING 		206040004111	BELL 	206 	206L1 	1182107	SW 										M/R XMSN	FAULTY 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2772A				BMC00131	45311				THESE "NEW DESIGN" ORINGS FOLD OVER UPON INSTALLATION OF INPUT FLANGE CAUSING EXCESSIVE LEAKING. REPLACED "NEW DESIGN" (	THINNER) ORINGS WITH "OLD DESIGN" (THICKER) ORINGS AND RETURNED TO SERVICE.					1	G	7	1 	3U				H2SW 					 
1995101300150	19951013	00150		1995	10	13	HEEA955840 	4	19951005	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2761X					45283				TRANSCEIVER ON-OFF KNOB BROKEN. REPLACED FACEPLATE ASSEMBLY THAT HAD BROKEN KNOB. ALSO REPLACED DEFECTIVE MIXER DIODE C	R202. UNIT BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995101300151	19951013	00151	SW 	1995	10	13	HEEA955841 	1	19951005	G	6310	206040270003	FREEWHEEL 			BELL 	206 	206B 	1181511	SW 										FWD SEAL	SEAL LEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2276B	8140 				3628				FREEWHEEL FORWARD SEAL LEAKING. REPLACED WITH SERVICEABLE FREEWHEELING UNIT.						1	G	7	1 	3U				H2SW 					 
1995101300152	19951013	00152	SW 	1995	10	13	HEEA955842 	1	19951005	G	6220	206011149105	YOKE 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R HUB	BEARING FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2246Q	7785 			A324	45752				YOKE O.B. BEARING JOURNAL ON ONE SIDE BREAKING DOWN. REPLACED WITH SERVICEABLE PART AND RETURNED TO SERVICE.						1	G	7	1 	3U				H2SW 					 
1995101300153	19951013	00153	SW 	1995	10	13	HEEA955843 	1	19951005	G	5320	206031100681	SHELL ASSY 			BELL 	206 	206B 	1181511	SW 										LAP SEAM	SEPARATION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2275Y					3626				FOUND LOWER SHELL ASSY (TUB) SEPARATED BOTH INSIDE AND OUT. THE OUTSIDE OF TUB WAS SEPARATED ALONG LAP SEAM FROM AFT END	 TO 44 1/2" FWD OF AFT EDGE. THE SEPARATION WAS 3" WIDE ALONG ENTIRE LENGHT; ONE SECTION 12" LONG THE WIDTH INCREASED T	O 6". THE INSIDE OF THE TUB WAS SEPARATED MOST OF THE R/H AFT PASSENGER FLOOR AREA. THE SEPARATION IS AT LEAST 10" WID	E ALONG INNER LAP AREA. THE SEPARATION IS AT LEAST 10" WIDE ALONG INNER LAP SEAM. CUT OUT SEPARATION AREA ON OUTSIDE.			1	G	7	1 	3U				H2SW 					 
1995101300154	19951013	00154	SW 	1995	10	13	HEEA955844 	1	19951005	G	7920	174000103	FILTER ASSEMBLY 			BELL 	206 	206L1 	1182107	SW 										OIL SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5006F					45181				LOUD CHATTERING NOISE COMING FROM FILTER HEAD WHEN MOTORING ENGINE - NOTE: CHATTERING OCCURS ON SPOOL DOWN AFTER MOTORI	NG TO 10% N1. REPLACED FILTER HOUSING ASSEMBLY.					1	G	7	1 	3U				H2SW 					 
1995101300155	19951013	00155		1995	10	13	HEEA955845 	4	19951005	G	3451	066106600	TRANSCEIVER 			BELL 	212 	212 	1181420	SW 										COCKPIT DME	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1079U					31122				INSPECT FOR CORROSION. DISASSEMBLED TRANSCEIVER UNIT AND CHECKED FOR OIL AND CORROSION. CLEANED AS NEEDED. ALIGNED RE	CEIVER AND IF SECTION FOR PROPER RECEIVE SENSITIVITY. INSPECTED AND UNT BENCH CHECK GOOD.					1	G	7	1 	4U				H4SW 					 
1995101300156	19951013	00156		1995	10	13	HEEA955846 	4	19951005	G	2312	4000106010	CONTROL UNIT 		C10 	BELL 	212 	212 	1181420	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1079U					31122				INSPECT FOR CORROSION. INSPECTED CONTROL UNIT, BUT FOUND NO CORROSION. HOWEVER, FOUND THUMBWHEEL TO BE INTERMITTENTLY D	IALING UP WRONG FREQUENCIES. REPLACED 1 EACH S1 THUMBWHEEL. REPAIRED.					1	G	7	1 	4U				H4SW 					 
1995101300157	19951013	00157		1995	10	13	HEEA955847 	4	19951005	G	3452	066107100	TRANSPONDER 			BELL 	412 	412 	1182202	SW 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	107X					33113				TRANSPONDER INOPERATIVE. FOUND PLASTIC INSULATOR BUSHING ON Q501 TRANSISTOR BURNT AND ARCING TO GROUND. REPLACED BUSHIN	G TO REPAIR PROBLEM. ALIGNED RECEIVER AND IF SECTION TO SPECS. UNIT BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995101300158	19951013	00158		1995	10	13	HEEA955848 	4	19951005	G	2312	064102300	TRANSCIEVER 			BELL 	412 	412 	1182202	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				TRANSCEIVER TRANSMISSIONS SCRATCHY. FOUND MODULATION AND TRANSMIT COMPRESSOR OUT OF SPECS. ADJUSTED TRANSMIT COMPRESSOR	 AND MODULATION TO SPECS. REPAIRED. ALSO ADJUSTED C/SQUELCH, FREQUENCY, AND SIDETONE TO SPECS. REPLACED HEADER J304 A	ND APPLIED HUMISEAL TO HEADER FOR CORROSIONCONTROL. BENCH CHECK GOOD.				1	G	7	2 	4U				H4SW 					 
1995101300159	19951013	00159		1995	10	13	HEEA955849 	4	19951005	G	3452	066107100	TRANSPONDER 			BELL 	412 	412 	1182202	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S					36002				TROUBLESHOOTING C/H GOING OUT. UNIT WOULD NOT RECEIVE. FOUND HEAVY CORROSION AND FOUND INSULATOR BUSHINGS ON Q501 TRANS	ISTOR AND ON Q104 TRANSISTOR WERE BURNT. REPLACED BUSHINGS, CLEANED CORROSION AND APPLIED ALODINE. ALIGNED RECEIVER AN	D IF SECTIONS. ALSO TRANSMITTER WAS ALIGNED. UNIT BENCH CHECK GOOD.				1	G	7	2 	4U				H4SW 					 
1995101300160	19951013	00160		1995	10	13	HEEA955850 	4	19951005	G	3451	066106602	TRANSCEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT DME	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	23023					33080				TRANSCEIVER 24 MONTH INSPECTION. CLEANED CORROSION. UNIT WOULD NOT RECEIVE. REPLACED INTEGRATED CIRCUIT I1 ON POWER SUP	PLY BOARD TO MAKE UNIT RECEIVE. UNABLE TO ALIGN RECEIVER TO MANUFACTURER SPECS. SENT TO ALLIED SIGNAL AVIONICS FOR INS	PECTION AND REPAIR.				1	G	7	2 	4U				H4SW 					 
1995101300161	19951013	00161		1995	10	13	HEEA955851 	4	19951005	G	3444	066305401	INDICATOR 		KI250 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	FACE BROKEN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4391S					S787				GLASS BROKEN ON FACE OF INDICATOR. REPLACED BROKEN LENS, REPAIRED. PERFORMED COMPLETE ALIGNMENT AND CALIBRATION. BENCH	 CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995101300162	19951013	00162	EU 	1995	10	13	HEEA955852 	1	19951005	G	6330	355A38004004	FRONT BAR 			AEROSP	AS355 	AS355F 	8680806	EU 										M/R XMSN	BEARING FAULTY 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5796S					5164				FRONT BAR UPPER BEARING IS UNBONDED. REPLACED WITH SERVICEABLE STRUT.						1	G	7	2 	3U				H11EU 					 
1995101300163	19951013	00163		1995	10	13	HEEA955853 	4	19951005	G	2312	4000106010	CONTROL UNIT 		C10 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2743E					760155				CONTROL UNIT VOLUME CONTROL WORKS EITHER FULL VOLUME OR OFF. NO CONTROLLING VOLUME. REPLACED R1/S5 VOLUME SWITCH. REP	AIRED. FOUND THUMBWHEEL TO INTERMITTENTLY DIAL WRONG FREQUENCIES. REPLACED S1 THUMBWHEEL. REPAIRED.					1	G	7	2 	3U				H1NE 					 
1995101300164	19951013	00164		1995	10	13	HEEA955854 	4	19951005	G	2312	064102300	TRANSCIEVER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VHF	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	15459					760222				TRANSCEIVER WILL NOT TRANSMIT OR RECEIVE. NO TRANSMIT OR RECEIVE. FOUND OPEN FACE. TROUBLESHOT ENTIRE POWER SUPPLY FOR	 SHORTS ON 27.5V LINE. REPLACED FUSE F101. REPAIRED. COOKED UNIT AND VIBRATED ON BENCH. ALIGNED RECEIVER TO SPECS. A	DJUSTED C/N SQUELCH, C/S SQUELCH, MODULATION. ANDSIDETONE. BENCH CHECK GOOD.				1	G	7	2 	3U				H1NE 					 
1995101300165	19951013	00165	NE 	1995	10	13	HEEA955855 	1	19951005	G	6321	7665009803105	MODULE 			SKRSKY	S76 	S76A 	8143006	NE 										ROTOR BRAKE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2743E					760155				DURING OPS CHECK, NOTED ROTOR BRAKE MOTOR SOUNDED WEAK BUT SEEMED TO OPERATE NORMALLY. TWO DAYS LATER AIRCRAFT WAS FLOW	N FOR FIRST TIME AND PILOT'S REPORTED ROTOR BRAKE DOES NOT WORK. REPLACED WITH SERVICEABLE ROTOR BRAKE MODULE.					1	G	7	2 	3U				H1NE 					 
1995101300166	19951013	00166	EU 	1995	10	13	HEEA955856 	1	19951006	G	6230	350A37118101	GUIDE 			SNIAS 	350 	AS350B 	8680801	EU 										SWASHPLATE	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	962 				2777				GUIDE WORN .082" DEEP, ABOUT 1/2 THE WAY AROUND TUBE. REMOVED FROM UPPER TRANSMISSION S/N M855.						1	G	7	1 	3U				H9EU 					 
1995101300167	19951013	00167	EU 	1995	10	13	HEEA955858 	1	19951006	G	6220	350A31201621	FAIRING 		350A31003304	SNIAS 	350 	AS350B 	8680801	EU 										VIB ABSORBER	CORROSION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951				PHI48	2771				CORROSION IN FAIRING BOLT HOLES. SEE MMIR#5859 FOR LOWER FLANGE ALSO REPLACED.						1	G	7	1 	3U				H9EU 					 
1995101300168	19951013	00168	EU 	1995	10	13	HEEA955859 	1	19951006	G	6220	350A31200200	FLANGE ASSY 		350A31003304	SNIAS 	350 	AS350B 	8680801	EU 										VIB ABSORBER	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951				PHI48	2771				VIB ABSORBER LOWER FLANGE ASSY EXCESSIVE CORROSION. SEE MMIR#5858 FOR FAIRING ALSO REPLACED.						1	G	7	1 	3U				H9EU 					 
1995101300169	19951013	00169	EU 	1995	10	13	HEEA955860 	1	19951006	G	6320	350A37107421	BALL JOINT 			SNIAS 	350 	AS350B 	8680801	EU 										TRANSMISSION	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	962 				2777				BALL JOINT WORN .008" OUT WHERE IT RIDES AGAINST SUPPORT. REMOVED FROM TRANSMISSION S/N M855. PART SCRAPPED.						1	G	7	1 	3U				H9EU 					 
1995110200017	19951102	00017		1995	11	2	HEEA955861 	4	19951006	G	3421	4021541671	GYRO 			BOLKMS	117 	BK117A4 	5626017	EU 										COCKPIT HORIZ	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	520WJ					7092				HORIZ GYRO INTERMITTENTLY TAKES 9 MINUTES TO ERECT.						1	G	7	2 	3U				H13EU 					 
1995101300170	19951013	00170		1995	10	13	HEEA955862 	4	19951006	G	3421	102005901	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT ATTITUDE	PRECESSES 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5742N					45477				ATTITUDE POINTER BAR PRECESSES 3 DEGREES DURING SETTLING TEST.						1	G	7	1 	3U				H2SW 					 
1995101300171	19951013	00171		1995	10	13	HEEA955863 	4	19951006	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	7128R	3056 				36007				CVR WILL NOT TEST.						1	G	7	2 	4U				H4SW 					 
1995102000113	19951020	00113	SW 	1995	10	20	HEEA955864 	1	19951012	G	6210	206010200133	BLADE 			BELL 	206 	206B 	1181511	SW 										M/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22743	2497 				3624				EXCESSIVE AMOUNT OF EXFOLIATION ON UPPER LEADING EDGE NEAR THE TIP WITH PIECES MISSING.						1	G	7	1 	3U				H2SW 					 
1995102000114	19951020	00114		1995	10	20	HEEA955867 	4	19951012	G	3421	102005403	GYRO 			BELL 	206 	206L3 	1182108	SW 										COCKPIT HORIZ	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6603X					51412				GYRO HAS 2 DEGREES LEFT TILT IN LEVEL FLIGHT. ROLL ERECTION RATES SLOW AND 10 DEGREES POINTER BAR DROP. TIME SINCE REP	AIR 339:10.					1	G	7	1 	3U				H2SW 					 
1995102000115	19951020	00115	NE 	1995	10	20	HEEA955868 	1	19951012	G	6210	7615009100049A	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22342	9236 				760096				SEVERAL CRACKS IN THE TITANIUM LEADING EDGE STRIP, BUT THE CRACK AT STATION 173" HAS IN EXCESS OF 2.5 INCHES OF SEPARATI	ON. THE INBOARD END OF THE NICKEL STRIP HAS APPROX. 13" OF SEPARATION.					1	G	7	2 	3U				H1NE 					 
1995102000116	19951020	00116	SW 	1995	10	20	HEEA955869 	1	19951012	G	6210	206015001107	BLADE 			BELL 	206 	206L3 	1182108	SW 										M/R	PITTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8594X	1700 				51531				BLADE HAS A BUSHING PITTED BEYOND LIMITS.						1	G	7	1 	3U				H2SW 					 
1995102000117	19951020	00117		1995	10	20	HEEA955870 	4	19951012	G	2312	069102525	TRANSCEIVER 		KX165 	BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT VHF	SHORTED 	E			HEEA	K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			SW	03	134AE					7237				UNIT SHORTED. SMOKE CAME FROM UNIT WHEN TURNED ON.						1	G	7	2 	3U			NC	H13EU 					 
1995102000118	19951020	00118		1995	10	20	HEEA955871 	4	19951012	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	WEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1077A					45382				TRANSCEIVER REPORTED WEAK BY A.T.C.						1	G	7	1 	3U				H2SW 					 
1995102000119	19951020	00119	EU 	1995	10	20	HEEA955872 	1	19951012	G	2435	150SG1156	STATOR 			AEROSP	AS355 	AS355F1 	8680810	EU 										START/GEN	LEADS DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										BRUSH LEADS ARE TOO SHORT; DOES NOT REACH SCREW HOLE OF BRUSH BOXES.						1	G	7	2 	3U				H11EU 					 
1995102000120	19951020	00120		1995	10	20	HEEA955873 	4	19951012	G	3453	4530093	RECEIVER 		ARNAV20 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911HM					S683				CDI NOT FOLLOWING LORAN.						1	G	7	2 	3U				H3EU 					 
1995102000121	19951020	00121		1995	10	20	HEEA955874 	4	19951013	G	3416	214175278101	INDICATOR 	MASCO 																COCKPIT ALT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03										INSTRUMENT LIGHTS INOPERATIVE. TIME SINCE REPAIR 0:00.																			 
1995102000122	19951020	00122		1995	10	20	HEEA955875 	4	19951013	G	3442	MI5852013	INDICATOR 		P4001 	BEECH 	200 	200CBEECH 	1152926	CE 										COCKPIT RADAR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	39PH					BL3				BLUE SCREEN ON INDICATOR, ANTENNA LIGHT AND INTERMITTENT ON TAKE OFF.						1	L	7	2 	4T				A24CE 					 
1995102000123	19951020	00123	EU 	1995	10	20	HEEA955876 	1	19951013	G	2844	642792002	TRANSMITTER 			SNIAS 	350 	AS350B2 	8680813	EU 										FUEL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951	2031 				2771				FUEL PRESSURE GAUGE GOES TO MAX WITH BATT POWER OFF.						1	G	7	1 	3U				H9EU 					 
1995102000124	19951020	00124	EU 	1995	10	20	HEEA955877 	1	19951013	G	6420	350A33211904	HUB 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R YOKE	BEARING FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951	1086 				2771				T/R YOKE FORK BEARINGS SEPARATED IN TWO.						1	G	7	1 	3U				H9EU 					 
1995102000125	19951020	00125		1995	10	20	HEEA955878 	4	19951013	G	2312	064102300	TRANSCIEVER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22342					760096				BENCH CHECK NEEDED. INSPECTED AND TESTED. REPLACED HEADER J304 AND APPLIED HUMISEAL TO HEADER FOR CORROSION CONTROL. A	DJUSTED MODULATION AND TRANSMIT COMPRESSOR TO SPECS. COOKED UNIT. BENCH CHECK GOOD.					1	G	7	2 	3U				H1NE 					 
1995102000126	19951020	00126	SW 	1995	10	20	HEEA955879 	1	19951013	G	6220	206011149105	YOKE 		206011100149	BELL 	206 	206B 	1181511	SW 										M/R	BEARING FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2268A	10471			A101018	3602				M/R YOKE OB BEARING JOURNAL ON BOTH SIDES BREAKING DOWN. REPLACED WITH SERVICEABLE M/R YOKE.						1	G	7	1 	3U				H2SW 					 
1995102000127	19951020	00127	SW 	1995	10	20	HEEA955880 	1	19951013	G	6220	206010110105	WASHER 		206011100159	BELL 	206 	206L3 	1182108	SW 										M/R THRUST	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6610C	378 			HB94	51425				MATERIAL DETERIORATION CAUSING EXCESSIVE LOAD. LOWERED TORQUE ON ADJUSTMENT SCREWS AND LOWERED PRELOAD ON THRUST PLUGS.						1	G	7	1 	3U				H2SW 					 
1995102000128	19951020	00128	EU 	1995	10	20	HEEA955881 	1	19951013	G	7930	DK040	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										OIL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7161J					S834				OIL PRESSURE FLUCTUATING AND PEGS TO HIGH SIDE. REPLACED WITH SERVICEABLE OIL PRESSURE TRANSMITTER.						1	G	7	2 	3U				H3EU 					 
1995102000129	19951020	00129	EU 	1995	10	20	HEEA955882 	1	19951013	G	7930	DK040	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										OIL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7161J					S834				ERRATIC READING. REPLACED WITH SERVICEABLE TRANSMITTER.						1	G	7	2 	3U				H3EU 					 
1995102000130	19951020	00130	SW 	1995	10	20	HEEA955883 	1	19951013	G	6410	206310105101	BEARING 		206011810135	BELL 	206 	206L1 	1182107	SW 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y	1158 			AFS5841	45751				INBOARD BEARING ON BLADE S/N CS6823 WORN THROUGH ANODIZED SURFACE. INBOARD BEARING ON BLADE S/N CS6821 CRACKED. REPLACE	D BEARINGS AND SLEEVES. ROLLED STAKED AS REQUIRED.					1	G	7	1 	3U				H2SW 					 
1995102000131	19951020	00131	NE 	1995	10	20	HEEA955884 	2	19951013	G	7250	3017600	ENGINE 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					POWER SECT	FAULTY 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347	3871 				36005				HIGH N1, 1% TO 2% HIGH ON POWER CHECK.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995102000132	19951020	00132	SW 	1995	10	20	HEEA955885 	1	19951013	G	2824	L88010491	VALVE 			BELL 	412 	412 	1182202	SW 										FUEL SYS	SHORTED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	23023					33080				VALVE SHORTED INTERNALLY.						1	G	7	2 	4U				H4SW 					 
1995102000133	19951020	00133	SW 	1995	10	20	HEEA955886 	1	19951013	G	2841	412375001101	INDICATOR 			BELL 	412 	412 	1182202	SW 										FUEL QTY	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				REPORTED DIGITAL QUANTITY AND NEEDLE DO NOT COINCIDE.						1	G	7	2 	4U				H4SW 					 
1995102000134	19951020	00134	SW 	1995	10	20	HEEA955889 	1	19951013	G	6720	7001484	YAW CONTROL 			BELL 	412 	412 	1182202	SW 										T/R CONTROL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22608					33075				YAW ACTUATOR DEFLECTS LEFT, WILL NOT ENTER.						1	G	7	2 	4U				H4SW 					 
1995102000135	19951020	00135	NE 	1995	10	20	HEEA955890 	2	19951013	G	7250	3017600	ENGINE 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					POWER SECT	FAULTY 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2261D	13799				33076				HIGH ITT AT POWER CHECK.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995102000136	19951020	00136		1995	10	20	HEEA955891 	4	19951013	G	3414	8502CS20LW	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT AIR SPD	CASE LEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5444X					760174				AIR SPEED INDICATOR UNIT HAS EXCESSIVE CASE LEAK.						1	G	7	2 	3U				H1NE 					 
1995102000137	19951020	00137		1995	10	20	HEEA955892 	4	19951013	G	3425	7000469902	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT HSI	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	792CH					760193				VERTICAL FLAG WOULD NOT PULL, INTERMITTENT.						1	G	7	2 	3U				H1NE 					 
1995102000138	19951020	00138	NE 	1995	10	20	HEEA955894 	1	19951013	G	7810	7630507003043	EJECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										EXHAUST	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3122G					760232				EJECTOR UNIT CRACKED.						1	G	7	2 	3U				H1NE 					 
1995102700443	19951027	00443	SW 	1995	10	27	HEEA955895 	1	19951017	G	6720	222312702101	PITCH LINKS 			BELL 	230 	230 	1182149	SW 										T/R PC LINK	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	362 				23009				T/R P/C LINKS BEARINGS WORN BEYOND LIMITS.						1	G	7	2 	3U			NC	H9SW 					 
1995102700444	19951027	00444	EU 	1995	10	27	HEEA955897 	1	19951017	G	6220	350A31190703	STARFLEX 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	1318 				2653				STARFLEX CRACKED BEYOND LIMITS.						1	G	7	1 	3U				H9EU 					 
1995102700445	19951027	00445	EU 	1995	10	27	HEEA955898 	1	19951017	G	2435	150SG122Q	GENERATOR 			SNIAS 	350 	AS350B2 	8680813	EU 										START/GEN	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ					2653				GENERATOR WILL NOT RESET, STARTER WILL NOT TURN OVER.						1	G	7	1 	3U				H9EU 					 
1995102700446	19951027	00446	NE 	1995	10	27	HEEA955899 	1	19951017	G	5347	107820003	BUCKET ASSY 			SKRSKY	S76 	S76A 	8143006	NE 										SEAT	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5444X					760174				SEAT FRAME CRACKED DUE TO CORROSION AT LEFT CORNER OF SEAT BOTTOM.						1	G	7	2 	3U				H1NE 					 
1995102700447	19951027	00447	EU 	1995	10	27	HEEA955900 	1	19951017	G	6730	SC50821	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R CONTROL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	60951	2035 				2771				SERVO LEAKING.						1	G	7	1 	3U				H9EU 					 
1995102700448	19951027	00448	EU 	1995	10	27	HEEA955901 	1	19951017	G	2150	6AS35039	EVAPORATOR 			SNIAS 	350 	AS350B2 	8680813	EU 										FORWARD	LEAKING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	1329 				2653				LEAKING. HOLE IN EVAPORATOR, MOTOR INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995102700449	19951027	00449	SW 	1995	10	27	HEEA955902 	1	19951019	G	6220	206011149105	YOKE 		206011100149	BELL 	206 	206B 	1181511	SW 										M/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2277A	7425 			A127	3630				FOUND GREASE WATERY & BLACK COLORED. O/B BEARING JOURNAL BREAKING DOWN, EXCESSIVE CORROSION IN RETAINER BORES, AND SURF	ACE CORROSION ON YOKE BETWEEN JOURNALS. SCRAPPED YOKE LOCALLY.					1	G	7	1 	3U				H2SW 					 
1995102700450	19951027	00450	SW 	1995	10	27	HEEA955904 	1	19951019	G	5210	1008402	LATCH ASSY 			BELL 	230 	230 	1182149	SW 										PILOT DOOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	58 				23009				PILOTS DOOR WOULD NOT OPEN OR CLOSE PROPERLY.						1	G	7	2 	3U			NC	H9SW 					 
1995102700451	19951027	00451	EU 	1995	10	27	HEEA955908 	1	19951020	G	5610	04011341990	WINDOW 			SNIAS 	350 	AS350B2 	8680813	EU 										LT SLIDER	TRACK MISSING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6100R	182 				2862				TRACK ON WINDOW IS MISSING.						1	G	7	1 	3U				H9EU 					 
1995102700452	19951027	00452	EU 	1995	10	27	HEEA955909 	1	19951020	G	6220	350A31190703	STARFLEX 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	1008 				2777				STARFLEX CRACK ON YELLOW ARM.						1	G	7	1 	3U				H9EU 					 
1995102700453	19951027	00453	EU 	1995	10	27	HEEA955910 	1	19951020	G	6240	117945641	INDICATOR 			BOLKMS	117 	BK117A4 	5626017	EU 										MAST MOMENT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230H					7136				MAST MOMENT INDICATOR NEEDLE DROPS TO ZERO.						1	G	7	2 	3U				H13EU 					 
1995102700454	19951027	00454	EU 	1995	10	27	HEEA955911 	1	19951020	G	6240	10594575	TRANSMITTER 			BOLKMS	117 	BK117A4 	5626017	EU 										M/R TORQUE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230H					7136				TORQUE NEEDLE DROPS TO ZERO.						1	G	7	2 	3U				H13EU 					 
1995102700455	19951027	00455	NE 	1995	10	27	HEEA955912 	2	19951020	G	7261	17425000080	FILTER HOUSING 			BOLKMS	117 	BK117A4 	5626017	EU 	LYC 	LTS101	LTS101650B1 	41560	NE 					ENG OIL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230H					7136				BY PASS BUTTON WON'T STAY RESET. RECEIVED INSTALLED ON AIRCRAFT.						1	G	7	2 	3U	3	U		H13EU 	E5NE				 
1995102700456	19951027	00456	EU 	1995	10	27	HEEA955913 	1	19951020	G	7722	1179405105	INDICATOR 			BOLKMS	117 	BK117A4 	5626017	EU 										COCKPIT TOT	READS HIGH 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230H					7136				GAUGE READS HIGH 8 DEGREES TO 800. UNIT RECEIVED INSTALLED ON AIRCRAFT.						1	G	7	2 	3U				H13EU 					 
1995102700457	19951027	00457	SW 	1995	10	27	HEEA955917 	1	19951020	G	2810	10648BH1201	SWITCH 			BELL 	230 	230 	1182149	SW 										NR 1 FUEL VLV	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2364 				23009				#1 FUEL VALVE SWITCH WILL NOT LATCH.						1	G	7	2 	3U			NC	H9SW 					 
1995110600045	19951106	00045	SW 	1995	11	6	HEEA955919 	1	19951024	G	2436	222375060115	REGULATOR 			BELL 	230 	230 	1182149	SW 										NR 2 GENERATOR	DEFECTIVE 	E			HEEA	K				NONE 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			SW	03	230UN	19 				23009				#2 GENERATOR LIGHT WILL NOT GO OUT. VOLTAGE REG DEFECTIVE.						1	G	7	2 	3U			NC	H9SW 					 
1995110600046	19951106	00046	SW 	1995	11	6	HEEA955920 	1	19951024	G	6330	222331617101	MOUNT 			BELL 	230 	230 	1182149	SW 										M/R XMSN	SEPARATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	598 				23009				ISOLATION MOUNT ELASTOMER SEPARATED.						1	G	7	2 	3U			NC	H9SW 					 
1995110600047	19951106	00047	EU 	1995	11	6	HEEA955921 	1	19951024	G	6220	117775P	BALLJOINT 			SNIAS 	350 	AS350B2 	8680813	EU 										STARFLEX	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1204 				2771				TEFLON WORN. SERIAL NUMBERS REMOVED ARE SF128, SF143, AND SF145.						1	G	7	1 	3U				H9EU 					 
1995110600048	19951106	00048	EU 	1995	11	6	HEEA955922 	1	19951024	G	6230	350A37116200	YOKE ASSY STOP 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1000 				2771				YOKE ASSY STOP WORN. CHARGED AS A SET DUE TO ONE BREAKING IN FITTING.						1	G	7	1 	3U				H9EU 					 
1995110600049	19951106	00049	EU 	1995	11	6	HEEA955923 	1	19951024	G	6410	704A33633116	BEARING 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	350BZ	1450 				2653				BEARING DEFECTIVE. REMOVED AS ORIGINAL EQUIPMENT ON AIRCRAFT.						1	G	7	1 	3U				H9EU 					 
1995110600050	19951106	00050	EU 	1995	11	6	HEEA955924 	1	19951024	G	6320	1171261201	BEARING 		1171200501 	BOLKMS	117 	BK117B2 	5626013	EU 										M/R XMSN	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	132AE	1171 			KA0377	7238				BEARING INNER RACE AND ROLLERS BREAKING DOWN AND CAUSING METAL IN OIL. SCRAPPED PART.						1	G	7	2 	3U			NC	H13EU 					 
1995110600051	19951106	00051	GL 	1995	11	6	HEEA955925 	2	19951027	G	7230	23005262	BEARING 		23033193 	BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					ENG NR 1	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8588X	1426 			CAC91088	51486	CAE895185			ENGINE REMOVED DUE TO TURBINE OVERHAUL AND COMPRESSOR 1750 HOUR INSPECTION. UPON DISASSEMBLY OF #1 BEARING AREA DUE TO 	OIL LEAK NOTED THE FOLLOWING: #1 BEARING FAILURE. FOUND 75% OF SEPERATOR CRACKED AFT OF CENTERING TAB; WITH BREAK OUT 	OF 40%FWD RING. SCRAPPED #1 BEARING. SEE MMIR#5926 FOR #1 BEARING HOUSING.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995110600052	19951106	00052	GL 	1995	11	6	HEEA955926 	2	19951027	G	7230	23009591	BEARING HOUSING 		23033193 	BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					ENG NR 1	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8588X	1426 			CAC91088	51486	CAE895185			ENGINE REMOVED DUE TO TURBINE OVERHAUL AND COMPRESSOR 1750 HOUR INSPECTION. UPON DISASSEMBLY OF #1 BEARING AREA DUE TO 	OIL LEAK NOTED THE FOLLOWING: #1 BEARING FAILURE. FOUND 75% OF SEPERATOR CRACKED AFT OF CENTERING TAB; WITH BREAK OUT 	OF 40%FWD RING. SCRAPPED #1 BEARING. SEE MMIR#5925 FOR #1 BEARING.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995110600053	19951106	00053	GL 	1995	11	6	HEEA955927 	2	19951027	G	7230	6898607	BEARING 		6890550 	BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20B 	03013	GL 					NR 1	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3181Y	2817 			CAC33622	3772	CAE836332			ENGINE REMOVED DUE TO #1 BEARING FAILURE. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: #1 BEARING SEPARATO	R BROKEN INTO MANY PIECES, INNER AND OUTER RACE SPALLED, BEARING BALLS SCORED AND FLATTENED. SECONDARY DAMAGE - MUTE R	UB ON 1STSTAGE WHEELS, CARBON SEAL MATING SURFACE GROOVED ON 1ST STAGE WHEEL STUB SHAFT, CASE HALF VANES EXHIBIT EXCESSI	VE CONTACT WITH WHEEL MUTES AND PLASTIC GROOVED, CRACKED AND MISSING, IMPELLER CONTACT WITH FRONT DIFFUSER, REAR DIFFUSE	R MAJOR AND MINORSEALS GROOVED. SCRAPPED #1 BEARING.		1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995110600054	19951106	00054	EU 	1995	11	6	HEEA955928 	1	19951027	G	5270	SP381200	SWITCH 			SNIAS 	350 	AS350B2 	8680813	EU 										LT DOOR	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951	1547 				2771				SWITRCH INOPERATIVE. SCRAPPED LOCALLY.						1	G	7	1 	3U				H9EU 					 
1995110600055	19951106	00055	EU 	1995	11	6	HEEA955932 	1	19951027	G	6210	350A09101101	STRIP 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R BLADE	WORN EXCESSIVELY	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6097Z	980 				2820				PROTECTION STRIP WORN OFF.						1	G	7	1 	3U				H9EU 					 
1995111700171	19951117	00171	GL 	1995	11	17	HEEA955933 	2	19951031	G	7230	23051099	DIFFUSER COVER 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					COMPRESSOR	AIR LEAK 	E			HEEA	K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			SW	03	31217	2444 			CAC91772	760229	CAE890786S			ENGNE REMOVED DUE TO LOW POWER AND TURBINE OVERHAUL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: AIR LEAK	 AT SPLIT LINE OF DIFFUSER COVER PLATE DUE TO EXCESSIVE DOUBLER WELDS. NOTE: REPLACED PART AND CURED PROBLEM. INSTALL	ED NEW DIFFUSER COVER PLATE.				1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995111700172	19951117	00172		1995	11	17	HEEA955935 	4	19951031	G	2211	4033089901	COMPUTER 		FZ702 	BELL 	214 	214ST 	1182106	SW 										AFCS	FAIL TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	5748M					28102				UNIT FAILED 20 DEGREES ROLL LEFT LIMIT TEST 11.2 ON SST. TIME SINCE REPAIR 3:25.						2	G	7	2 	4U				H10SW 					 
1995111700173	19951117	00173	SW 	1995	11	17	HEEA955936 	1	19951031	G	2824	L88010501	VALVE 			BELL 	212 	212 	1181420	SW 										FUEL SYS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5736J					31140				VALVE INOPERATIVE.						1	G	7	1 	4U				H4SW 					 
1995111700174	19951117	00174	NE 	1995	11	17	HEEA955937 	1	19951031	G	7810	7630507003044	EJECTOR 			SKRSKY	S76 	S76A 	8143006	NE 										EXHAUST	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1547D					760077				EJECTOR IS CRACKED.						1	G	7	2 	3U				H1NE 					 
1995111700175	19951117	00175	SW 	1995	11	17	HEEA955938 	1	19951031	G	7921	209062501001	COOLER 			BELL 	412 	412 	1182202	SW 										ENG OIL	METAL CONTAM 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	33008					36004				OIL COOLER UNIT HAS METAL CONTAMINATION.						1	G	7	2 	4U				H4SW 					 
1995111700176	19951117	00176	SW 	1995	11	17	HEEA955939 	1	19951031	G	6330	206033506101	RESTRAINT 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	WORN EXCESSIVELY	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6610Y					51419				XMSN RESTRAINT ROLL STAKE BEARING WORN.						1	G	7	1 	3U				H2SW 					 
1995111700177	19951117	00177	SW 	1995	11	17	HEEA955940 	1	19951031	G	3213	AB205050403031	CROSSTUBE 			BELL 	412 	412 	1182202	SW 										SADDLES	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										CROSSTUBE MOUNTING HOLES WILL NOT LINE UP WITH SADDLES.						1	G	7	2 	4U				H4SW 					 
1995111700178	19951117	00178		1995	11	17	HEEA955941 	4	19951031	G	2312	064105430	TRANSCEIVER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT VHF	STATIC 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5029H					S670				TRANSCEIVER HAS CONSTANT STATIC IN FLIGHT. COULD NOT DUPLICATE ON GROUND. COULD NOT VERIFY COMPLAINT. REPLACED BAD DIS	PLAY DS901. ADJUSTED MODULATION AND SIDETONE. BENCH CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995111700179	19951117	00179		1995	11	17	HEEA955942 	4	19951031	G	3452	066106200	TRANSPONDER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6610Y					51419				BENCH CHECK REQUIRED. INSPECTED AND TESTED TRANSPONDER. FOUND MTL TO BE BELOW SPECS. ALIGNED RECEIVER TO SPECS. REPAI	RED PROBLEM. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. REPAIRED. COOKED UNIT. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995111700180	19951117	00180	SW 	1995	11	17	HEEA955943 	1	19951031	G	7712	5035T27G04	SENSOR 			BELL 	214 	214ST 	1182106	SW 										ENG TORQUE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T					28101				NO TORQUE INDICATION.						2	G	7	2 	4U				H10SW 					 
1995111700181	19951117	00181		1995	11	17	HEEA955944 	4	19951031	G	2562	ELT910	ELT 	NARCO 		BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	ACTIVATED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5029H					S670				ELT ACTIVATED FOR MORE THAN ONE HOUR.						1	G	7	2 	3U				H3EU 					 
1995111700182	19951117	00182	SW 	1995	11	17	HEEA955945 	1	19951031	G	6730	206076062003	CYLINDER 			BELL 	206 	206L1 	1182107	SW 										M/R SERVO	DEFECTIVE 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03		3704 								BEARINGS COMING UNSTAKED; LEAKING END CAP AND PILOT INPUT HIGH.						1	G	7	1 	3U				H2SW 					 
1995111700183	19951117	00183	EU 	1995	11	17	HEEA955946 	1	19951101	G	7712	G555672	TRANSDUCER 			BOLKMS	117 	BK117A4 	5626017	EU 										ENG TORQUE	FAIL TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	520WJ	1531 				7092				TRANSDUCER FAILED BY 0.3 VOLTS DURING YAW CSAS ELECTRICAL FUNCTION TEST.						1	G	7	2 	3U				H13EU 					 
1995111700184	19951117	00184	NE 	1995	11	17	HEEA955947 	1	19951101	G	7722	7645001076106	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										TURB TEMP	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4253S					760035				INDICATOR READS 500 DEGREES LOW.						1	G	7	2 	3U				H1NE 					 
1995111700185	19951117	00185	SW 	1995	11	17	HEEA955948 	1	19951101	G	3213	412050010107	CROSSTUBE 			BELL 	412 	412 	1182202	SW 										HISKID	SEPARATING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	23023					33080				PREBOND SEPARATING FROM CROSSTUBE.						1	G	7	2 	4U				H4SW 					 
1995111700186	19951117	00186		1995	11	17	HEEA955949 	4	19951101	G	3421	1113034	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT ADI	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K					36001				ADI VIBRATES AND CHANGES ALTITUDE IN FLIGHT.						1	G	7	2 	4U				H4SW 					 
1995111700187	19951117	00187		1995	11	17	HEEA955950 	4	19951101	G	3421	1113034	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT ATTITUDE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21498					36003				INDICATOR #2 NEEDLE HAS NO INDICATION.						1	G	7	2 	4U				H4SW 					 
1995111700188	19951117	00188		1995	11	17	HEEA955951 	4	19951101	G	3425	1113025	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT HSI	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2258F					33073				INDICATOR STICKS IN ROLL AXIS.						1	G	7	2 	4U				H4SW 					 
1995111700189	19951117	00189	SW 	1995	11	17	HEEA955952 	1	19951101	G	6730	206076062003	CYLINDER 			BELL 	206 	206L1 	1182107	SW 										SERVO	LOOSE BEARING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	3178K	13774				45765				LOOSE BEARING AND LEAKING AT WEEP HOLE AND CAP.						1	G	7	1 	3U				H2SW 					 
1995111700190	19951117	00190		1995	11	17	HEEA955953 	4	19951101	G	3454	066302440	COMPASS FLAG 		KPI552 	BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	134AE	1368 				7237				COMPASS FLAG WILL NOT PULL.						1	G	7	2 	3U			NC	H13EU 					 
1995111700191	19951117	00191	SW 	1995	11	17	HEEA955954 	1	19951101	G	2841	412375001105	INDICATOR 			BELL 	412 	412 	1182202	SW 										FUEL SYS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				FUEL QUANTITY READS DIFFERENTLY ON EACH SIDE.						1	G	7	2 	4U				H4SW 					 
1995111700319	19951117	00319	SW 	1995	11	17	HEEA955970 	1	19951107	G	3213	206050288103	CROSSTUBE 			BELL 	206 	206B 	1181511	SW 										AFT SKID	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2269A	1089 				3608				CROSSTUBE IS CORRODED. (CORROSION AT MOUNT PAD .011 BEYOND LIMITS.)						1	G	7	1 	3U				H2SW 					 
1995111700320	19951117	00320	SW 	1995	11	17	HEEA955971 	1	19951107	G	5320	206031100701	TUB 			BELL 	206 	206B 	1181511	SW 										FUSELAGE	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	2275Y					3626				SUPPORT ANGLES FOR L/H AND R/H CREW SEAT BACK LOWER PANELS WERE INSTALLED 3/16" TOO FAR FORWARD. SUPPORT ANGLES FOR AFT	 CENTER DOOR POST WERE INSTALLED 3/16" TOO FAR FORWARD. SUPPORT ANGLE FOR LOWER AFT CENTER BROOM CLOSET VERTICAL ANGLES	 WERE ALSO INSTALLED 3/16" TOO FAR FORWARD. TUB ALSO DOES NOT HAVE HOLES CUT FOR LOCATION OF POSITION LIGHTS. REPLACED 	SUPPORT ANGLES AS REQUIRED PER NORDAM MRR#08957. LOCATED AND CUT 1.5" HOLES FOR POSITION LIGHTS AND HARD POINTED AS REQ	UIRED PER BHT SERVICE INSTRUCTION # 206-47 FIGURE 1-6.		1	G	7	1 	3U				H2SW 					 
1995111700321	19951117	00321	SW 	1995	11	17	HEEA955972 	1	19951107	G	3213	AB205050403031	CROSSTUBE 			BELL 	412 	412 	1182202	SW 										LT SKID	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										INNER BOLT HOLES ON L/H SKID TUBE DOES NOT LINE UP WITH CROSSTUBE NUTPLATES.						1	G	7	2 	4U				H4SW 					 
1995111700322	19951117	00322	EU 	1995	11	17	HEEA955973 	1	19951107	G	6730	AC67246	SERVO 			SNIAS 	350 	AS350B2 	8680813	EU 										FRONT CONTROL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	705 				2771				PILOT FELT FEEDBACK IN FORE/AFT CYCLIC CONTROLS.						1	G	7	1 	3U				H9EU 					 
1995111700323	19951117	00323	EU 	1995	11	17	HEEA955974 	1	19951107	G	2822	D10731818	BEARING 			BOLKMS	105 	BO105S 	5626006	EU 										PUMP	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	105WK	406 				S812				BEARING CAME APART. BEARING RECEIVED WITH OVERHAUL KIT P/N D107318-21.						1	G	7	2 	3U				H3EU 					 
1995111700324	19951117	00324	EU 	1995	11	17	HEEA955975 	1	19951107	G	2822	D10731818	BEARING 			BOLKMS	105 	BO105S 	5626006	EU 										PUMP	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7136J	682 				S830				BEARING IS ROUGH AND COMING APART. BEARING RECEIVED WITH OVERHAUL KIT P/N D107318-21.						1	G	7	2 	3U				H3EU 					 
1995111700325	19951117	00325		1995	11	17	HEEA955976 	4	19951108	G	3442	MI5851345	INDICATOR 	HONEYWELL 	P40 	BELL 	212 	212 	1181420	SW 										COCKPIT RADAR	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	1079U					31122				WILL NOT TEST. INOPERATIVE.						1	G	7	1 	4U				H4SW 					 
1995111700326	19951117	00326		1995	11	17	HEEA955977 	4	19951108	G	3442	MI5851352	TRANSCEIVER 	HONEYWELL 	P40 	BELL 	412 	412 	1182202	SW 										COCKPIT	WEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				RADAR RECEIVER SENSITIVITY WEAK.						1	G	7	2 	4U				H4SW 					 
1995111700327	19951117	00327		1995	11	17	HEEA955978 	4	19951108	G	3442	MI5851352	TRANSCEIVER 	HONEYWELL 	P40 	SKRSKY	S76 	S76A 	8143006	NE 										RADAR	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546G					760076				INOPERATIVE.						1	G	7	2 	3U				H1NE 					 
1995111700328	19951117	00328		1995	11	17	HEEA955979 	4	19951108	G	3442	MI5851352	TRANSCEIVER 	HONEYWELL 	P40 															RADAR	WEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										WEAK RECEIVER AND STC OFF AT 85 LB.																			 
1995112400078	19951124	00078		1995	11	24	HEEA955980 	4	19951108	G	3442	MI5852013	INDICATOR 	HONEYWELL 	P4001 	BOLKMS	117 	BK117A4 	5626017	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	520WJ					7092				UNIT PAINTS FALSE TARGETS AT BOTTOM OF SCREEN ON 5NM RANGE TO 200 NM RANGE WITH FULL GAIN. ALSO UNIT HAS NO FACEPLATE 	LIGHTING.					1	G	7	2 	3U				H13EU 					 
1995111700329	19951117	00329		1995	11	17	HEEA955981 	4	19951108	G	2312	064100900	TRANSCEIVER 		KTR905 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1545X					760050				UNIT STARTS TRANSMITTING AS SOON AS POWER IS APPLIED. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H1NE 					 
1995112400079	19951124	00079		1995	11	24	HEEA955982 	4	19951108	G	2312	064101900	TRANSCEIVER 			BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC					7152				TRANSCEIVER GARBLED, WEAK TRANSMIT AND RECEIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U				H13EU 					 
1995111700330	19951117	00330		1995	11	17	HEEA955983 	4	19951108	G	2312	064105430	TRANSCEIVER 			BELL 	206 	206B3 	1181506	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2268V					3605				TOP SEGMENTS REMAIN ILLUMINATED AT ALL TIMES, ON STANDBY SIDE.						1	G	7	1 	3U				H2SW 					 
1995111700331	19951117	00331		1995	11	17	HEEA955984 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2125M					45649				TRANSMIT WEAK AND INTERMITTENT. TRIED ADJUSTING POWER BUT COULD NOT BRING IT UP TO SPECS. REPLACED CAVITY TUBE V101. R	EPAIRED. ADJUSTED FREQUENCY. FOUND UNIT TO HAVE WEAK RECEIVE. ALIGNED RECEIVER. REPLACED CAPACITOR C409. REPAIRED. 	 BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995111700332	19951117	00332		1995	11	17	HEEA955985 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	206FS					51506				SECOND KNOB WILL NOT TURN INTERNAL NUMBER. REPLACED ONE KNOB SHAFT FROM SPARE. ALSO REPLACED V101 CAVITY OSCILLATOR THA	T WAS WEAK. REPAIRED PROBLEM. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995111700333	19951117	00333		1995	11	17	HEEA955986 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L 	1181522	SW 										COCKPIT ATC	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7077B					52037				ATC REPORTS NO SIGNAL FROM UNIT. UNIT HAS VERY WEAK POWER OUT. REPLACED CAVITY TUBE V101. REPAIRED. ADJUSTED FREQUENC	Y AND PULSE WIDTH. CLEANED CONTACTS ON ALL WAFERS. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995111700334	19951117	00334		1995	11	17	HEEA955987 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L3 	1182108	SW 										COCKPIT ATC	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3207Q					50540				INTERMITTENT INOPERATIVE. REPLACED CAVITY OSCILLATOR V101 DUE TO LOW POWER OUT. REPAIRED. REPLACED PHOTOCELL V301 DUE 	TO WEAK REPLY LIGHT. REPAIRED. ALIGNED RECEIVER. ADJUSTED FREQUENCY AND PULSE WIDTH. CLEANED CONTACTS ON ALL WAFER S	WITCHES. BENCH CHECK GOOD.				1	G	7	1 	3U				H2SW 					 
1995111700335	19951117	00335		1995	11	17	HEEA955988 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5007Y					45192				NOT RECEIVED BY TOWER. FOUND POWER SLIGHTLY LOW AT ABOUT 150W. ADJUSTED POWER UP, FREQUENCY AND PULSE SHAPE. REPLACED 	DETERIORATED RESISTOR R477 AND DEFECTIVE PHOTODETECTOR V301. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995111700336	19951117	00336		1995	11	17	HEEA955989 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4294R					S860				BENCH CHECK REQUIRED. INSPECTED AND TESTED. REPLACED CAVITY TUBE V101 DUE TO LOW POWER OUT. REPAIRED. ADJUSTED FREQUE	NCY AND ALIGNED RECEIVER TO SPECS. CLEANED CONTACTS ON ALL WAFER SWITCHES. BENCH CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995111700337	19951117	00337		1995	11	17	HEEA955990 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y					45751				BENCH CHECK REQUIRED. INSPECTED AND TESTED. REPLACED CAVITY TUBE V101 DUE TO LOW POWER OUT. REPAIRED. REPLACED PHOTOC	ELL V301 DUE TO WEAK REPLY LIGHT. REPAIRED. ALIGNED RECEIVER TO SPECS. ADJUSTED FREQUENCY. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995111700338	19951117	00338		1995	11	17	HEEA955991 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2275Y					3626				FREQUENCY IS OUT OF TOLERANCE. ADJUSTED FREQUENCY, REPLACED MISSING WASHER AND PIN ON UNITS RETAINING SCREW. INSPECTED 	UNIT. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995111700339	19951117	00339		1995	11	17	HEEA955992 	4	19951108	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	81992					S827				BENCH CHECK REQUIRED. INSPECTED AND TESTED. REPLACED CAVITY TUBE V101 DUE TO LOW POWER OUT. REPAIRED. ADJUSTED FREQUE	NCY AND ALIGNED RECEIVER. CLEANED CONTACTS ON ALL WAFERS. BENCH CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995111700340	19951117	00340		1995	11	17	HEEA955993 	4	19951108	G	3444	066104800	ALTIMETER 		KRA405 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT RAD ALT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31217					760229				RADAR ALT. INOPERATIVE. REPLACED OPEN FUSE (F101) AND SHORTED C115 CAPACITOR BOTH ON POWER SUPPLY BOARD. REPAIRED OPEN 	FOIL FROM PIN L OF FRONT CONNECTOR TO PIN 3 OF J101. UNIT IS REPAIRED AND BENCH CHECKS GOOD.					1	G	7	2 	3U				H1NE 					 
1995112400080	19951124	00080		1995	11	24	HEEA955994 	4	19951108	G	3452	066107100	TRANSPONDER 			BELL 	412 	412 	1182202	SW 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S					36002				INOPERATIVE. REPLACED SHORTED TRANSISTOR Q104 AND REPAIRED BURNT FOIL ON PC BOARD FOR 28V SUPPLY. REPAIRED PROBLEM AND 	BENCH CHECKED GOOD.					1	G	7	2 	4U				H4SW 					 
1995111700341	19951117	00341		1995	11	17	HEEA955995 	4	19951108	G	3455	066107200	RECEIVER 		KR87 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ADF	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5014Y					45219				INOPERATIVE. FOUND UNIT POWERS UP; BUT DISPLAY IS TOTALLY INOPERATIVE. REPLACED INTEGRATED CIRCUITS I401, I402 AND TRAN	SISTOR Q401. SOME SEGMENTS ARE NOW LIT, BUT MOST ARE INOPERATIVE. REPLACED INTEGRATED CIRCUITS I507 AND I508. NO HELP	. REPLACED DIODECR404. REPAIRED PROBLEM. REPLACED DISPLAY DUE TO SOME SEGMENTS BEING WEAK. REPAIRED. APPLIED DOW COR	NING #4 COMPOUND TO DISPLAY. BENCH CHECK GOOD.			1	G	7	1 	3U				H2SW 					 
1995111700342	19951117	00342		1995	11	17	HEEA955996 	4	19951108	G	3455	066107200	RECEIVER 		KR87 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT ADF	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7062X					S793				DOES NOT RECEIVE.						1	G	7	2 	3U				H3EU 					 
1995111700343	19951117	00343		1995	11	17	HEEA955997 	4	19951108	G	3455	066107700	RECEIVER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT ADF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22342					760096				LOUD AND SCRATCHY RECEPTION. PERFORMED HEADER MODIFICATION BY REPLACING HEADERS J301, J302, J306, AND J307. APPLIED HUM	ISEAL TO HEADERS. ALSO FOUND 200 KHZ TO POINT DIFFERENTLY.					1	G	7	2 	3U				H1NE 					 
1995111700344	19951117	00344		1995	11	17	HEEA955998 	4	19951108	G	3454	066107800	RECEIVER 			BELL 	412 	412 	1182202	SW 										VHF NAV	SHORTED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				J6341 FRONT CONNECTOR NEEDS TO BE REPLACED DUE TO SHORT CAUSING BLUE MARKER LIGHT TO STAY LIT AND GLIDESCOPE INTERMITTEN	TLY INOPERATIVE.					1	G	7	2 	4U				H4SW 					 
1995111700345	19951117	00345		1995	11	17	HEEA955999 	4	19951108	G	3454	066107800	RECEIVER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT NAV	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				INOPERATIVE. POWER SUPPLY VOLTAGES ARE LOADED DOWN.						2	G	7	2 	4U				H10SW 					 
1995111700346	19951117	00346		1995	11	17	HEEA956000 	4	19951108	G	3444	066305401	INDICATOR 		KI250 	BELL 	206 	206L3 	1182108	SW 										COCKPIT	LENS CRACKED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	206LS					51070				INDICATOR LENS CRACKED.						1	G	7	1 	3U				H2SW 					 
1995111700347	19951117	00347		1995	11	17	HEEA956001 	4	19951108	G	3454	066400700	RECEIVER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5444X					760174				VOR NEEDLE INOPERATIVE. FOUND EXCESSIVE CORROSION ON MOTHER BOARD. CLEANED CORROSION FROM MOTHER BOARD- NO HELP - SWAPP	ED RMI CARD, MANUAL VOR CARD AND NAV CARD- NO HELP.					1	G	7	2 	3U				H1NE 					 
1995111700348	19951117	00348		1995	11	17	HEEA956002 	4	19951108	G	3444	066304401	INDICATOR 																	COCKPIT	FLAG STICKS 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										RADAR ALTIMETER FLAG STICKS BEHIND MASK.																			 
1995111700349	19951117	00349		1995	11	17	HEEA956003 	4	19951108	G	3457	0845000000	SKYNAV 5000 			SNIAS 	350 	AS350B 	8680801	EU 										COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	60951					2771				DISPLAY LIGHTS ARE TOO DIM TO READ. LIGHTS DIM ACCORDING TO SPECS. FUNCTION CHECKS GOOD.						1	G	7	1 	3U				H9EU 					 
1995111700350	19951117	00350	SW 	1995	11	17	HEEA956004 	1	19951108	G	6210	206010200133	BLADE 			BELL 	206 	206B 	1181511	SW 										M/R	BUSHING SHIFT 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2275Q	3248 				3625				THE BUSHING SHIFTED UPWARD.						1	G	7	1 	3U				H2SW 					 
1995111700351	19951117	00351	SW 	1995	11	17	HEEA956005 	1	19951108	G	6220	206011149105	YOKE 		206011100159	BELL 	206 	206L1 	1182107	SW 										M/R	BEARING FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1077A	2292 			A2048	45382				BEARING JOURNAL BREAKING DOWN. REPLACED WITH NEW YOKE ASSEMBLY.						1	G	7	1 	3U				H2SW 					 
1995111700352	19951117	00352	SW 	1995	11	17	HEEA956006 	1	19951108	G	5320	206031314037	CHANNEL 			BELL 	206 	206L3 	1182108	SW 										FUSELAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	205FC					51130				PART IS CRACKED. (CRACKED IN FITTING AREA STARTING AT RIVET HOLES) REPLACED CHANNEL WITH NEW CHANNEL.						1	G	7	1 	3U				H2SW 					 
1995111700353	19951117	00353	SW 	1995	11	17	HEEA956007 	1	19951108	G	5311	206032308103S	FRAME 			BELL 	206 	206L 	1181522	SW 										FUSELAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7077B					52037				PART IS CRACKED. (FRAME CRACKED AT R/H UPPER ATTACHMENT FITTING.) REPLACED WITH SERVICEABLE FRAME.						1	G	7	1 	3U				H2SW 					 
1995111700354	19951117	00354	SW 	1995	11	17	HEEA956008 	1	19951108	G	5320	206033110229	STIFFENER 			BELL 	206 	206L3 	1182108	SW 										FUSELAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6160Y	4073 				51609				STIFFENER IS CRACKED. (CRACKED IN LOWER RIGHT HAND RADIUS OF CUTOUT) REPLACED WITH SERVICEABLE STIFFENER.						1	G	7	1 	3U				H2SW 					 
1995111700355	19951117	00355	SW 	1995	11	17	HEEA956009 	1	19951108	G	5320	206033110249	STIFFNER 			BELL 	206 	206L 	1181522	SW 										FUSELAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7077B					52037				STIFFENER IS CRACKED. (STIFFNER CRACKED UPPER SECTION) REPLACED WITH SERVICEABLE STIFFNER.						1	G	7	1 	3U				H2SW 					 
1995111700356	19951117	00356	SW 	1995	11	17	HEEA956010 	1	19951108	G	6330	206033506101	RESTRAINT 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	BEARING UNSTAKED	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3116P					51530				ROLL STAKE BEARING UNSTAKED.						1	G	7	1 	3U				H2SW 					 
1995111700357	19951117	00357	SW 	1995	11	17	HEEA956011 	1	19951108	G	7722	206075678103	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										ENGINE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5742N					45477				TEMP NEEDLE PEGS OUT INTERMITTENTLY.						1	G	7	1 	3U				H2SW 					 
1995112400274	19951124	00274	SW 	1995	11	24	HEEA956040 	1	19951115	G	6310	289052017	SEAL 		206040270009	BELL 	206 	206L3 	1182108	SW 										FREEWHEEL	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	6610E	186 			BLA082	51424				SEAL LEAKING.						1	G	7	1 	3U				H2SW 					 
1995112400275	19951124	00275	NE 	1995	11	24	HEEA956041 	1	19951115	G	6320	SB3316101	BEARING 		763510950004	SKRSKY	S76 	S76A 	8143006	NE 										M/R GR BOX	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22342	5473 			A08100347	760096				BEARING CAGE BROKEN (OUTER RACE, SB3316-201 IS BEING SENT WITH BEARING) SENT FOR EVALUATION.						1	G	7	2 	3U				H1NE 					 
1995112400276	19951124	00276	SW 	1995	11	24	HEEA956042 	1	19951115	G	5320	206031202015S	FITTING 			BELL 	206 	206B 	1181511	SW 										BOX BEAM	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2269A					3608				PILOT HOLES ON VERTICAL FLANGE OF FITTING DO NOT ALIGN WITH EXISTING FASTENER HOLES ON BOX BEAM.						1	G	7	1 	3U				H2SW 					 
1995112400277	19951124	00277	SW 	1995	11	24	HEEA956043 	1	19951115	G	6420	214011801109	HUB 		214011801109	BELL 	214 	214ST 	1182106	SW 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5748M	2763 			A53	28102				TRUNNION RACHETS WHEN ROTATED: SUPPORT BRINELLING ON RACES.						2	G	7	2 	4U				H10SW 					 
1995112400278	19951124	00278	SW 	1995	11	24	HEEA956044 	1	19951115	G	2436	222375060115	REGULATOR 			BELL 	230 	230 	1182149	SW 										NR 2 GEN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	230UN	17 				23009				#2 GENERATOR WILL NOT COME ON LINE.						1	G	7	2 	3U			NC	H9SW 					 
1995112400279	19951124	00279	SW 	1995	11	24	HEEA956045 	1	19951115	G	5510	222035256111	SLAT 			BELL 	230 	230 	1182149	SW 										HORIZ STAB	DETERIORATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2582 				23009				LT SLAT DETERIORATING.						1	G	7	2 	3U			NC	H9SW 					 
1995112400280	19951124	00280	SW 	1995	11	24	HEEA956047 	1	19951115	G	7810	206064300005	EXHAUST ASSY 			BELL 	206 	206L1 	1182107	SW 										ENG	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2245Y	510 				45751				EXHAUST ASSY IS CRACKED.						1	G	7	1 	3U				H2SW 					 
1995112400281	19951124	00281	SW 	1995	11	24	HEEA956048 	1	19951115	G	7810	206064300005	EXHAUST ASSY 			BELL 	206 	206L3 	1182108	SW 										ENGINE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6610E	675 				51424				EXHAUST ASSY IS CRACKED.						1	G	7	1 	3U				H2SW 					 
1995112400282	19951124	00282	NE 	1995	11	24	HEEA956049 	2	19951115	G	7200	0292005220	ENGINE 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1D 		NE 					FUEL CONTROL	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	1215 				2777				DURING ENGINE START, WHEN THE START BUTTON IS PRESSED AND FFC LEVER WAS ADVANCED, NORMAL IGNITION AND ACCELERATION WOULD	 OCCUR UNTIL REACHING 25 TO 30% NG. AT THAT TIME ACCELERATION WOULD ALMOST STOP. THE ENGINE WOULD NOT ACCELERATE UNLES	S THE T4 WAS KEPT AT THE TOP OF THE GREEN ARC. EVEN THEN ACCELERATION TO 40% WAS VERY SLOW. WHEN ENGINE WAS COLD, ACCE	LERATION TO 40% WOULD TAKE 45 TO 65 SEC. WHEN ENGINE WAS WARM ACCELERATION TO 40% TOOK 35 TO 40 SEC.			1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995112400283	19951124	00283	NE 	1995	11	24	HEEA956050 	2	19951115	G	7200	0292005220	ENGINE 			SNIAS 	350 	AS350B2 	8680813	EU 	TMECA 	ARRIEL	ARRIEL1D 		NE 					CHIP PLUG	MAKING METAL 	E			HEEA	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	6097Z	1089 				2820				ENGINE CHIP LIGHT. FOUND TINY AMOUNT FERROUS SHINY FUZZ ON LOWER CHIP PLUG. FILTER HAD SMALLER AMOUNT OF SAME TYPE OF 	FUZZ. CLEANED AND COMPLIED WITH 30 MINUTE PENALTY RUN. ON REAR BEARING ELEC. PLUG FOUND TINY FERROUS SPECKS (ABOUT 15 	EA)REINSTALLED ALL CHIP PLUGS. COMPLIED WITH ANOTHER 30 MINUE PENALTY RUN. REAR BEARING CHIP PLUG HAD 10 FERROUS SPECK	S AND THE OTHER 4 DETECTORS HAD 2-5 EACH SPECKS.			1	G	7	1 	3U	3	U		H9EU 	E19EU				 
1995112400284	19951124	00284	SW 	1995	11	24	HEEA956052 	1	19951116	G	6500	212040502001	SLEEVE ASSY 			BELL 	412 	412 	1182202	SW 										T/R	PLATE MISSING 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										RECEIVED NEW FROM BELL WITHOUT SHIM PLATE INSTALLED.						1	G	7	2 	4U				H4SW 					 
1995112400285	19951124	00285	EU 	1995	11	24	HEEA956054 	1	19951116	G	5610	04011340990	WINDOW 			SNIAS 	350 	AS350B2 	8680813	EU 										RT SLIDER	RAIL CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	60951	1174 				2771				SLIDING WINDOW BOTTOM RAIL CRACKED.						1	G	7	1 	3U				H9EU 					 
1995112400286	19951124	00286	EU 	1995	11	24	HEEA956055 	1	19951116	G	5610	04011341990	WINDOW 			SNIAS 	350 	AS350B2 	8680813	EU 										SLIDER TRACK	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6100U	57 				2863				SLIDER TRACK CRACKED OFF.						1	G	7	1 	3U				H9EU 					 
1995112400287	19951124	00287	EU 	1995	11	24	HEEA956057 	1	19951116	G	2822	D107318D1	PUMP ASSY 			BOLKMS	105 	BO105S 	5626006	EU 										FUEL SYS	TRIPS BREAKER 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7062X					S793				FUEL PUMP ASSY POPS CIRCUIT BREAKER.						1	G	7	2 	3U				H3EU 					 
1995112400288	19951124	00288	EU 	1995	11	24	HEEA956058 	1	19951116	G	6330	704A3363310951	STOP ASSY 			SNIAS 	350 	AS350B2 	8680813	EU 										M/R XMSN	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6095S	1008 				2777				SPHERICAL STOP ASSY UNITS WORN OUT. SERIAL NUMBERS REMOVED ARE 7245, 7246 AND 7203.						1	G	7	1 	3U				H9EU 					 
1995120800250	19951208	00250	SW 	1995	12	8	HEEA956075 	1	19951120	G	5520	206023119007	ELEVATOR 			BELL 	206 	206BELL 	1181502	SW 										INNER SPAR	DEFECTIVE 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										DIAMETER OF INNER SPAR TOO BIG, WILL NOT FIT SNUG ON HORN ASSY. SERIAL NUMBERS RECEIVED ARE BP302PC00 AND DODS00208. HA	ND CARRIED.					1	G	7	1 	3U				H2SW 					 
1995120800251	19951208	00251	SW 	1995	12	8	HEEA956076 	1	19951120	G	5520	206023119005	ELEVATOR 			BELL 	206 	206BELL 	1181502	SW 										INNER SPAR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										DIAMETER OF INNER SPAR TOO BIG, WILL NOT FIT SNUG ON HORN ASSY. SERIAL NUMBERS RECEIVED ARE BP0000316 AND DODS00207. HA	ND CARRIED.					1	G	7	1 	3U				H2SW 					 
1995120800252	19951208	00252	EU 	1995	12	8	HEEA956077 	1	19951121	G	5610	04011340990	WINDOW 			SNIAS 	350 	AS350B2 	8680813	EU 										RT SLIDER	RAIL CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6100R	140 				2862				SLIDING WINDOW BOTTOM RAIL CRACKED.						1	G	7	1 	3U				H9EU 					 
1995120800253	19951208	00253	EU 	1995	12	8	HEEA956078 	1	19951121	G	2435	150SG122Q	STARTER 			SNIAS 	350 	AS350B2 	8680813	EU 										START/GEN	WONT ENGAGE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6100R	315 				2862				STARTER WOULD NOT ENGAGE. GENERATOR WOULD COME ON LINE.						1	G	7	1 	3U				H9EU 					 
1995120800254	19951208	00254	EU 	1995	12	8	HEEA956079 	1	19951121	G	5610	350A2500505401	WINDOW 			SNIAS 	350 	AS350B2 	8680813	EU 										PANEL ASSY	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										WINDOW ASSEMBLY HAS NO SLIDE WINDOW AND WIND DEFLECTOR.						1	G	7	1 	3U				H9EU 					 
1995120800255	19951208	00255	GL 	1995	12	8	HEEA956080 	2	19951121	G	7230	6890502	BLADE 		6890550 	BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					3RD STAGE	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7062X	1358 			CAC41432	S793	CAE836134			ENGINE REMOVED DUE TO #1 BEARING OIL LEAK AND 3RD STAGE COMPRESSOR BLADE FAILURE. UPON INSPECTION OF COMPRESSOR PARTS N	OTED THE FOLLOWING: ONE EACH BLADE BROKEN OFF ON 3RD STAGE WHEEL. SECONDARY DAMAGE -- 4TH STAGE WHEEL P/N 6876654, S/N	 ER58760SCRAPPED DUE TO F.O.D. -- 5TH STAGE WHEEL P/N 6876655, S/N KR42186 SCRAPPED DUE TO F.O.D.-- CASE HALF ASSY P/N 	6877410, S/N 16779 SENT FOR REPAIR DUE TO F.O.D. NOTE: FRONT SUPPORT P/N 6890530 S/N 39066 SCRAPPED DUE TO LEA	KING DURINGPRESSURE CHECK. PARTS SCRAPPED.		1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995120800256	19951208	00256		1995	12	8	HEEA956081 	4	19951121	G	2312	069102525	DISPLAY 		KX165 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	90752					S156				DIGIT OUT ON DISPLAY. REPLACED I402 (INTEGRATED CIRCUIT). REPAIRED. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995120800257	19951208	00257		1995	12	8	HEEA956082 	4	19951121	G	2312	069102525	TRANSCEIVER 		KX165 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22425					45743				#1 VHF WILL NOT COME ON. TROUBLESHOT AND REPLACE F401 (FUSE), C586 (CAPACITOR), REPAIRED POWER SUPPLY. FREQUENCY DRIFT	S, RESOLDERED COLD SOLDER JOINTS ON C434 (ADJUSTABLE CAPACITOR) AND Y401 (CRYSTAL), REPAIRED. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995120800258	19951208	00258		1995	12	8	HEEA956083 	4	19951121	G	2312	071104302	TRANSCEIVER 		KSF570B 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893N					33010				REQUIRES REFURBISHING AND BENCH CHECK REQUIRED. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	4U				H4SW 					 
1995120800259	19951208	00259		1995	12	8	HEEA956084 	4	19951121	G	2312	071104302	TRANSCEIVER 		KFS570B 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893P					33012				THIRD DIGIT INOPERATIVE. TWO CENTER WHEEL COUNTERS CRACKED.						1	G	7	2 	4U				H4SW 					 
1995120800260	19951208	00260		1995	12	8	HEEA956085 	4	19951121	G	3425	071107600	AMPLIFIER 		KDA697 	BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				VOR NEEDLE UNRELIABLE. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						2	G	7	2 	4U				H10SW 					 
1995120800261	19951208	00261		1995	12	8	HEEA956086 	4	19951121	G	2312	071121540	CONTROL 			BELL 	412 	412 	1182202	SW 										COCKPIT COMM	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				UPPER LIGHT DIGIT SEGMENTS OUT. VERIFIED. REPLACED DEFECTIVE DS101 DISPLAY. REPAIRED PROBLEM.						1	G	7	2 	4U				H4SW 					 
1995120800262	19951208	00262		1995	12	8	HEEA956087 	4	19951121	G	3457	0845000000	SKYNAV 5000 	MAGELLAN 																COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										FPL LIGHT BLINKS INTERMITTENTLY.																			 
1995120800263	19951208	00263		1995	12	8	HEEA956088 	4	19951121	G	3457	0845000000	SKYNAV 5000 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT RECEIVER	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	350BZ					2653				RECEIVER INOPERATIVE.						1	G	7	1 	3U				H9EU 					 
1995120800264	19951208	00264		1995	12	8	HEEA956089 	4	19951121	G	3425	6501141932	HSI 																	COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										HSI INOPERATIVE. SENT FOR EXCHANGE FOR S/N 841.																			 
1995120800265	19951208	00265	NE 	1995	12	8	HEEA956090 	2	19951121	G	7320	7046M95G04	ECU 			BELL 	214 	214ST 	1182106	SW 	GE 	CT7TS 	CT72A 	30030	NE 					ENG	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				TORQUE SPLITS ABOVE 80% COMBINED TORQUE.						2	G	7	2 	4U	4	U		H10SW 	E8NE				 
1995120800266	19951208	00266	EU 	1995	12	8	HEEA956092 	1	19951121	G	6310	4638202007	CLUTCH 		4638001004 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	91070	3361 			1034	S145				INNER CAGE WORN BEYOND LIMITS. REPLACED WITH SERVICEABLE CLUTCH.						1	G	7	2 	3U				H3EU 					 
1995120800267	19951208	00267		1995	12	8	HEEA956093 	4	19951121	G	3442	MI5852013	INDICATOR 		P4001 	BELL 	412 	412 	1182202	SW 										COCKPIT	FAILED 	E			HEEA	K				NONE 				B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			SW	03	3911L					33023				PILOT SMELLED SMOKE, THEN UNIT WENT DEAD.						1	G	7	2 	4U				H4SW 					 
1995120800268	19951208	00268		1995	12	8	HEEA956094 	4	19951121	G	3453	4530093	RECEIVER 	ARNAV 	ARNAV20 	BELL 	206 	206B 	1181511	SW 										COCKPIT	WEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2275Q					3625				DISPLAY WEAK.						1	G	7	1 	3U				H2SW 					 
1995120800269	19951208	00269		1995	12	8	HEEA956095 	4	19951121	G	3442	MI5851345	INDICATOR 		P40 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1545X					760050				TEST PATTERN SPOKES INTERMITTENTLY.						1	G	7	2 	3U				H1NE 					 
1995120800270	19951208	00270		1995	12	8	HEEA956096 	4	19951121	G	3416	8140BS20LW	ALTIMETER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	707AE					760276				100 FOOT NEEDLE FELL OFF HANDSTAFF. TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H1NE 					 
1995120800271	19951208	00271		1995	12	8	HEEA956097 	4	19951121	G	3442	MI5851345	INDICATOR 		P40 	BELL 	412 	412 	1182202	SW 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				BLANK SCREEN. REPLACED LOW V0LTAGE POWER SUPPLY AND VIDEO BOARD. UNIT HOW HAS INTERMITTENT DISPLAY. REPLACED CONNECTOR	 P1001. NOTE: REPLACE HEADER J1301.					1	G	7	2 	4U				H4SW 					 
1995120800272	19951208	00272	NE 	1995	12	8	HEEA956098 	1	19951121	G	6210	7615009100042A	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1546G	7846 				760076				PART IS CRACKED. (NUMEROUS AMOUNT OF CRACKS ON THE NICKEL STRIP WITH SEPARATION THAT IS BEYOND THE MAX LIMITS.						1	G	7	2 	3U				H1NE 					 
1995120800273	19951208	00273		1995	12	8	HEEA956099 	4	19951121	G	3442	MI5851352	TRANSCEIVER 		P40 	BELL 	412 	412 	1182202	SW 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S					36002				NO R/F OUTPUT.						1	G	7	2 	4U				H4SW 					 
1995120800274	19951208	00274		1995	12	8	HEEA956100 	4	19951121	G	3451	6221233001	TRANSPONDER 		DME40 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT DME	INOP 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				NO TRANSMIT (INOPERATIVE)						1	G	7	2 	3U				H1NE 					 
1995120800275	19951208	00275		1995	12	8	HEEA956101 	4	19951121	G	2370	9806019001	CVR 			BELL 	212 	212 	1181420	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	5736D	3253 				31135				DOESN'T TEST.						1	G	7	1 	4U				H4SW 					 
1995120800276	19951208	00276		1995	12	8	HEEA956102 	4	19951121	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	1545K	3435 				760047				ONLY GIVES SOLID MONOTONE SOUND DURING TEST.						1	G	7	2 	3U				H1NE 					 
1995120800277	19951208	00277		1995	12	8	HEEA956103 	4	19951121	G	3451	066106902	INDICATOR 		KDI573 	BELL 	412 	412 	1182202	SW 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6559Z					36019				UNABLE TO READ DISPLAY.						1	G	7	2 	4U				H4SW 					 
1995120800278	19951208	00278		1995	12	8	HEEA956104 	4	19951121	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5426U	2605 				760167				CVR NOT RECORDING.						1	G	7	2 	3U				H1NE 					 
1995120800279	19951208	00279		1995	12	8	HEEA956105 	4	19951121	G	3454	066107810	RECEIVER 		KNR634A 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	89H	392 				760406				RADIO POWERS UP AND RECEIVES IDENT, BUT DOESN'T POINT TO STATION AND NO CDI.						1	G	7	2 	3U				H1NE 					 
1995120800280	19951208	00280		1995	12	8	HEEA956106 	4	19951121	G	3451	066106902	DISPLAY 		KDI573 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				READOUT LIGHTS DIFFICULT TO READ. REPLACED DS901 DISPLAY THAT WAS WEAK. APPLIED HUMISEAL TO PREVIOUSLY DONE HEADER MODI	FICATION AND APPLIED DOW CORNING COMPOUND TO DISPLAY CONTACTS. BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995120800281	19951208	00281		1995	12	8	HEEA956107 	4	19951121	G	3450	071121004	CONTROL BOX 																	COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										DISPLAY INOPERATIVE.																			 
1995120800282	19951208	00282		1995	12	8	HEEA956108 	4	19951121	G	3453	066402600	LORAN 		KLN88 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	91070					S145				TAKES LONG TIME TO COME ON AND GOES OUT DURING FLIGHT.						1	G	7	2 	3U				H3EU 					 
1995120800283	19951208	00283		1995	12	8	HEEA956109 	4	19951121	G	3455	6222362001	RECEIVER 		ADF60A 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT ADF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				RECEPTION GARBLED.						1	G	7	2 	3U				H1NE 					 
1995120800284	19951208	00284	EU 	1995	12	8	HEEA956110 	1	19951121	G	7931	BSE206150G3	TRANSDUCER 			BOLKMS	105 	BO105S 	5626006	EU 										OIL PRESS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911BR					S719				OIL PRESSURE FLUCTUATION.						1	G	7	2 	3U				H3EU 					 
1995120800285	19951208	00285		1995	12	8	HEEA956111 	4	19951121	G	3455	066107700	RECEIVER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT ADF	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				NO AUDIO-NO NEEDLE POINT.						2	G	7	2 	4U				H10SW 					 
1995120800286	19951208	00286		1995	12	8	HEEA956112 	4	19951121	G	3457	0845000000	SKYNAV 5000 			BELL 	206 	206B 	1181511	SW 										COCKPIT GPS	INOP 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2275Y	122 				3626				LORAN INOPERATIVE.						1	G	7	1 	3U				H2SW 					 
1995120800287	19951208	00287		1995	12	8	HEEA956113 	4	19951121	G	3457	0845000000	SKYNAV 5000 	MAGELLAN 																COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										MSG BUTTON IS BAD.																			 
1995120800288	19951208	00288		1995	12	8	HEEA956114 	4	19951121	G	3457	0845000000	SKYNAV 5000 	MAGELLAN 		AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5786D					5113				POWER BUTTON IS SUNK INSIDE UNIT.						1	G	7	2 	3U				H11EU 					 
1995120800289	19951208	00289		1995	12	8	HEEA956115 	4	19951121	G	3444	066305401	INDICATOR 		KI250 	BELL 	206 	206L1 	1182107	SW 										COCKPIT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2772A					45311				NEEDLE STICKS, BROKEN GLASS.						1	G	7	1 	3U				H2SW 					 
1995120800290	19951208	00290		1995	12	8	HEEA956116 	4	19951121	G	3454	069102505	TRANSCEIVER 			BOLKMS	117 	BK117B2 	5626013	EU 										COCKPIT VOR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	136AE					7234				VOR WILL NOT TRACK RADIAL OR DISPLAY.						1	G	7	2 	3U			NC	H13EU 					 
1995120800291	19951208	00291	SW 	1995	12	8	HEEA956117 	1	19951121	G	5302	206032308003	FRAME 			BELL 	206 	206L3 	1182108	SW 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	205FC					51130				PART IS CRACKED. (FRAME CRACKED AT BOTH UPPER CASTING AREAS) REPLACED WITH SERVICEABLE FRAME ASSEMBLY.						1	G	7	1 	3U				H2SW 					 
1995120800292	19951208	00292	GL 	1995	12	8	HEEA956118 	2	19951121	G	7510	DYLM735011	MOTOR ASSY 			BELL 	206 	206B 	1181511	SW 	ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	INOP 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3181J					3771				LINEAR ACTUATOR INOPERATIVE. REPLACED WITH SERVICEABLE ACTUATOR.						1	G	7	1 	3U	3	U		H2SW 	E4CE				 
1995120800293	19951208	00293	SW 	1995	12	8	HEEA956119 	1	19951121	G	5511	206020120011	SPAR ASSY 			BELL 	206 	206B 	1181511	SW 										HORIZ STAB	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2269A					3608				SPAR ASSY IS CORRODED. (CORROSION AND WORN BEYOND LIMITS) REPLACED WITH SERVICEABLE SPAR ASSY.						1	G	7	1 	3U				H2SW 					 
1995120800294	19951208	00294		1995	12	8	HEEA956120 	4	19951121	G	3442	MI585200	RT UNIT 																	RADAR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										R/T CAUSES DISPLAY ON INDICATOR TO SHRINK AND FLICKER (ONLY DRAWS 4 AMPS OF CURRENT)																			 
1995120800295	19951208	00295		1995	12	8	HEEA956121 	4	19951121	G	3442	MI585200	RT UNIT 			BELL 	212 	212 	1181420	SW 										RADAR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3131S					30953				WILL NOT PAINT TARGETS.						1	G	7	1 	4U				H4SW 					 
1995120800296	19951208	00296		1995	12	8	HEEA956122 	4	19951121	G	3442	MI585136	PEDESTAL 		P40 															RADAR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										RADAR WILL NOT SCAN.																			 
1995120800297	19951208	00297		1995	12	8	HEEA956123 	4	19951122	G	2312	064100900	TRANSCEIVER 		KTR905 	BELL 	212 	212 	1181420	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1079U					31122				TRANSMIT BREAKS UP.						1	G	7	1 	4U				H4SW 					 
1995120800298	19951208	00298		1995	12	8	HEEA956124 	4	19951122	G	2312	064100900	TRANSCEIVR 		KTR905 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546G					760076				WON'T TRANSMIT OR RECEIVE ON 128.95 OR 122.82.						1	G	7	2 	3U				H1NE 					 
1995120800299	19951208	00299	NE 	1995	12	8	HEEA956125 	1	19951122	G	6410	7610105101041	BLADE 			SKRSKY	S76 	S76A 	8143006	NE 										T/R	DEFECTIVE 	E			HEEA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	31217	10030				760229				PADDLE B OF THIS ASSEMBLY HAS SLUNG THE INNER BLOCK AND WEIGHTS FROM THE TIP CAUSING EXCESSIVE VIBRATION.						1	G	7	2 	3U				H1NE 					 
1995120800300	19951208	00300		1995	12	8	HEEA956126 	4	19951122	G	3416	066304401	INDICATOR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22342					760096				DH LIGHT WILL NOT OPERATE. REPLACED DH LIGHT/SWITCH ASSEMBLY. REPAIRED. BENCH CHECK GOOD.						1	G	7	2 	3U				H1NE 					 
1995120800301	19951208	00301		1995	12	8	HEEA956127 	4	19951122	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7171A					S838				REPAIR FACEPLATE. REPLACED DEFECTIVE V301 PHOTODETECTOR. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995120800302	19951208	00302		1995	12	8	HEEA956128 	4	19951122	G	3455	071121009	CONTROL 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT ADF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911NC					7026				SOME NUMBERS ARE NOT LIGHTING UP AS REPORTED BY PILOT. REPLACED DEFECTIVE IC205 INTEGRATED CIRCUIT. REPAIRED AND UNIT B	ENCH CHECK GOOD.					1	G	7	2 	3U				H13EU 					 
1995120800303	19951208	00303		1995	12	8	HEEA956129 	4	19951122	G	3453	5410038	LORAN 		7000CDU 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				MANY LORAN CDU LED READOUTS INOPERATIVE.						1	G	7	2 	4U				H4SW 					 
1995120800304	19951208	00304		1995	12	8	HEEA956130 	4	19951122	G	3444	066104800	ALTIMETER 		KRA405 	BELL 	412 	412 	1182202	SW 										COCKPIT RAD ALT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S					36002				ALTIMETER FLUCTUATES IN FLIGHT.						1	G	7	2 	4U				H4SW 					 
1995120800305	19951208	00305		1995	12	8	HEEA956131 	4	19951122	G	2310	064101700	TRANSCEIVER 		KAC952 	BELL 	214 	214ST 	1182106	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8045T					28101				HF INOPERATIVE. WILL NOT TUNE.						2	G	7	2 	4U				H10SW 					 
1995120800306	19951208	00306	EU 	1995	12	8	HEEA956132 	1	19951122	G	6310	4638202007	CLUTCH 		4638001004 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5418A	1088 			1037	S800				INNER CAGE WORN BEYOND LIMITS AT INSPECTION. REPLACED CLUTCH WITH SERVICEABLE PART.						1	G	7	2 	3U				H3EU 					 
1995120800307	19951208	00307		1995	12	8	HEEA956133 	4	19951122	G	2312	064100900	TRANSCEIVER 		KT905 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546G					760076				TRANSMIT GARBLED.						1	G	7	2 	3U				H1NE 					 
1995120800308	19951208	00308		1995	12	8	HEEA956134 	4	19951122	G	2312	064100900	TRANSCEIVER 		KTR905 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31217					760229				WILL NOT TRANSMIT OR RECEIVE; HEAVY CORROSION.						1	G	7	2 	3U				H1NE 					 
1995120800309	19951208	00309		1995	12	8	HEEA956135 	4	19951122	G	3451	066106602	TRANSCEIVER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT DME	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8045T					28101				INOPERATIVE; WON'T COME ON LINE.						2	G	7	2 	4U				H10SW 					 
1995120800310	19951208	00310		1995	12	8	HEEA956136 	4	19951122	G	3450	071121004	CONTROL BOX 																	COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										ON/OFF/BFO IS INTERMITTENT WHEN SWITCHING BACK AND FORTH.																			 
1995120800311	19951208	00311	GL 	1995	12	8	HEEA956137 	2	19951122	G	7510	1092T1002W	SERVOMOTOR 			BOLKMS	105 	BO105S 	5626006	EU 	ALLSN 	250C 	250C20B 	03013	GL 					ANTI ICE	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6607K					S841				STICKING ANTI-ICE ACTUATOR.						1	G	7	2 	3U	3	U		H3EU 	E4CE				 
1995120800312	19951208	00312	EU 	1995	12	8	HEEA956138 	1	19951122	G	5302	STA6616	FRAME 			BOLKMS	117 	BK117B2 	5626013	EU 										TAILBOOM	CRACKED 	E		A	HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	136AE	1157 				7234				CRACKS DEVELOPED IN THE FRAME ALONG THE BOTTOM WHERE IT ATTACHES TO THE TAIL CONE SKIN. THE CRACKS TYPICALLY ORIGINATE 	FROM THE RIVETS AND RUN ALONG THE RIVET LINE. SOME CRACKS RUN BETWEEN RIVETS BUT DID NOT INTERSECT. OTHER CRACKS WENT 	TO THE EDGE. ONE CLIP ON THE RIGHT HAND LOWER POSITION WAS CRACKED IN THE SAME MANNER. THE RIGHT HAND REINFORCING ANGL	E P/N 117-22122-001.02 ALSO HAD A CRACK IN THE BEND RADIUS. CRACKED ALSO DEVELOPED UNDER THE UPPER AFT ECU MOUNT. THE 	CRACKS WEREBETWEEN AND AROUND RIVETS THAT HOLD THE MOUNT TO THE TAIL CONE SKIN. THE CRACKS ARE IN THE SKIN. INSTALLED R	EINFORCING ANGLE ALONG THE BOTTOM OF THE FRAME ACCORDING TO SB BK117-20-101 AND ALSO REPLACED THE CLIP.	1	G	7	2 	3U			NC	H13EU 					 
1995120800313	19951208	00313	EU 	1995	12	8	HEEA956139 	1	19951122	G	5302	STA6616	FRAME 			BOLKMS	117 	BK117B2 	5626013	EU 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	134AE	1156 				7237				CRACKS WERE FOUND ON THE FRAME WHERE IT RIVETED TO THE TAIL CONE SKIN. CRACKS WERE ALSO FOUND UNDER THE UPPER AFT ECU M	OUNT. INSTALLED REPAIR KIT P/N 117-SB20-101-3.1 ACCORDING TO SB BK117-20-101. INSTALLED A REPAIR DOUBLER ON TAIL CONE. 	 SHIMMED ECU TO AVOID ANY PRELOADS ON MOUNTS.				1	G	7	2 	3U			NC	H13EU 					 
1995120800314	19951208	00314	EU 	1995	12	8	HEEA956140 	1	19951122	G	5302		SKIN 			BOLKMS	117 	BK117B1 	5626012	EU 										TAILBOOM	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911TL	2969 				7198				DURING INSPECTION FOUND TAILBOOM MOUNT CONE SKIN CRACKED AT TOP AFT ECU MOUNT. REPAIRED SKIN BY STOP DRILLING CRACKS, AD	DING FILLER PATCH AND ADDING DOUBLER TO TAILBOOM MOUNT CONE SKIN AT TOP AFT ECU MOUNT AND IN ACCORDANCE WITH 337 DATED 4	-28-95 FOLLOWING REPAIR PROCEDURE BK117 #H6057-BK117-0426951.				1	G	7	2 	3U				H13EU 					 
1995120800315	19951208	00315	SW 	1995	12	8	HEEA956144 	1	19951128	G	7722	206375007103	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										ENG TOT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5005F					45176				NEEDLE STICKS THROUGHOUT SCALE. TIME SINCE REPAIR 147:15.						1	G	7	1 	3U				H2SW 					 
1995120800316	19951208	00316	EU 	1995	12	8	HEEA956145 	1	19951128	G	6240	10594575	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	6607K					S841				MAST MOMENT INDICATOR WOULD NOT TEST CORRECTLY.						1	G	7	2 	3U				H3EU 					 
1995120800317	19951208	00317	EU 	1995	12	8	HEEA956146 	1	19951128	G	6240	10594566	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6607K					S841				MAST MOMENT INDICATOR WOULD NOT TEST CORRECTLY.						1	G	7	2 	3U				H3EU 					 
1995120800318	19951208	00318		1995	12	8	HEEA956147 	4	19951128	G	2312	064101902	TRANSCEIVER 		KY196 	BELL 	206 	206L1 	1182107	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2777D					45299				UNABLE TO SWAP "STANDBY" CHANNEL TO "USE" AND "USE" TO "STANDBY". SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	1 	3U				H2SW 					 
1995120800319	19951208	00319		1995	12	8	HEEA956148 	4	19951128	G	3455	066104701	RECEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT ADF	WEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2258F					33073				WEAK RECEPTION. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	4U				H4SW 					 
1995120800320	19951208	00320		1995	12	8	HEEA956149 	4	19951128	G	3450	071106603	SELECTOR 		KFS580B 	SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546K					760082				WILL NOT SELECT STATIONS. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H1NE 					 
1995120800321	19951208	00321		1995	12	8	HEEA956150 	4	19951128	G	3416	212070238007	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893P					33012				NEEDLES INDICATE 80,000 FEET LOW. TIME SINCE REPAIR 25:45.						1	G	7	2 	4U				H4SW 					 
1995120800322	19951208	00322		1995	12	8	HEEA956151 	4	19951128	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	911TL					7198				ATC REPORTING INOPERATIVE. FOUND WAFER SWITCHES (2 EACH) BROKEN. REPLACED SWITCH BOARD. REPAIRED PROBLEM. ALIGNED REC	EIVER AND ADJUSTED FREQUENCY. BENCH CHECK GOOD.					1	G	7	2 	3U				H13EU 					 
1995120800323	19951208	00323		1995	12	8	HEEA956152 	4	19951128	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	513EH					45421				NOT RECEIVED BY ATC AFTER 2 HOURS OF FLIGHT. REPLACED BROKEN FACEPLATE. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT	. REPAIRED. REPLACED BROKEN HOLD DOWN AND INSTALLED GROOVE PIN. ADJUSTED PULSE WIDTH. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995120800324	19951208	00324		1995	12	8	HEEA956153 	4	19951128	G	3457	0845000000	SKYNAV 5000 	MAGELLAN 		SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6097Z					2820				GPS WILL NOT CHANNEL.						1	G	7	1 	3U				H9EU 					 
1995120800325	19951208	00325		1995	12	8	HEEA956154 	4	19951128	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206L1 	1182107	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1077A					45382				BENCH CHECK NEEDED. INSPECTED AND TESTED. REPLACED CAVITY TUBE V101 DUE TO WEAK POWER OUT. REPAIRED. ADJUSTED PULSE W	IDTH. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995120800326	19951208	00326		1995	12	8	HEEA956155 	4	19951128	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT ATC	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2269A					3608				TWO YEAR INSPECTION REQUIRED. FOUND V101 CAVITY OSCILLATOR WEAK AND V301 PHOTODETECTOR INOPERATIVE. REPLACED BOTH ITEMS	. ADJUSTED POWER OUT AND FREQUENCY TO SPECS. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995120800327	19951208	00327	GL 	1995	12	8	HEEA956156 	2	19951129	G	7230	23056634	GEARSHAFT 		23051643 	SKRSKY	S76 	S76A 	8143006	NE 	ALLSN 	250C 	250C30S 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5128	644 			CAC90014	760181	CAE890014S			ENGINE REMOVED DUE TO CYCLED OUT WHEELS. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIM	ITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. NEW PART INSTALLED.					1	G	7	2 	3U	3	U		H1NE 	E1GL				 
1995120800328	19951208	00328	GL 	1995	12	8	HEEA956157 	2	19951129	G	7230	23056634	GEARSHAFT 		23033193 	BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					SPUR ADAPTER	STEPWEAR 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8592X	816 			CAC90959	51508	CAE890638			ENGINE REMOVED DUE TO TURBINE OVERHAUL AND COMPRESSOR 1750 HOUR INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED T	HE FOLLOWING: STEP WEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. NEW PART INSTALLED.					1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995120800329	19951208	00329	GL 	1995	12	8	HEEA956158 	2	19951129	G	7260	23053968	SEAL 		23053960 						ALLSN 	250C 	250C30G2 	03013	GL 					GEARBOX	OIL LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03		1204 			CAG98241		CAE898241			ENGINE REPAIRED DUE TO OIL LEAK AND 300 HOUR INSPECTION. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: 1) OIL 	LEAKING FROM PTO MAG SEAL 2) EXCESSIVE WEAR ON SPACER. SEE MMIR #6159 FOR SPACER INFORMATION.										3	U			E1GL				 
1995120800330	19951208	00330	GL 	1995	12	8	HEEA956159 	2	19951129	G	7260	23059575	SPACER 		23053960 						ALLSN 	250C 	250C30G2 	03013	GL 					GEARBOX	WORN 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03		1204 			CAG98241		CAE898241			ENGINE REPAIRED DUE TO OIL LEAK AND 300 HOUR INSPECTION. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: 1) OIL 	LEAKING FROM PTO MAG SEAL 2) EXCESSIVE WEAR ON SPACER.										3	U			E1GL				 
1995120800331	19951208	00331	GL 	1995	12	8	HEEA956160 	2	19951129	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					3RD STAGE	BLADE DAMAGE 	E		A	HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	21240	558 			CAT70404	45647	CAE860702			ENGINE REMOVED DUE TO LOUD GRINDING NOISE, HIGH PITCH SQUEAL ACCOMPANIED BY TORQUE FLUCTUATIONS. UPON INSPECTION OF TUR	BINE PARTS NOTED THE FOLLOWING: RIM BREAKOUT OF 1 1/2" AND 1/4" OF TWO EACH BLADES ON 3RD STAGE WHEEL. SUSPECT CAUSE O	F FAILURE TO BE A STRESS CRACK ORIGINATING ON THE LEADING EDGE SIDE OF BREAKOUT IN REFERENCE TO DIRECTION OF ROTATION, O	N THE TRAILING EDGE OF RIM SHROUD AND PROGRESSED APPROXIMATELY 1/2 OF CHORDAL LENGTH UNTIL OVERLOAD. SECONDARY DAMAGE -	 P.T.SECTION EXHIBITS EXCESSIVE KNIFE AND SEAL CONTACT AND BEARING AREA DAMAGE.		1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995120800332	19951208	00332	GL 	1995	12	8	HEEA956161 	2	19951129	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					3RD STAGE	DAMAGED 	E		A	HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27702	636 			CAT70741	45300	CAE860520			ENGINE REMOVED DUE TO LOUD ROAR AND WHINE FOLLOWED BY ENGINE CHIP LIGHT. UPON INSPECTION OF TURBINE PARTS NOTED THE FOL	LOWING: RIM BREAKOUT OF 1 3/4" AND 1/4" OF THREE EACH BLADES ON 3RD STAGE WHEEL. SUSPECT CAUSE OF FAILURE TO BE A STRE	SS CRACK ORIGINATING ON THE LEADING EDGE SIDE OF BREAKOUT IN REFERENCE TO DIRECTION OF ROTATION, ON THE TRAILING EDGE OF	 RIM SHROUD AND PROGRESSED APPROXIMATELY 1/2 OF CHORDAL LENGTH UNTIL OVERLOAD. SECONDARY DAMAGE - P.T. SECTION EXHIBITS	EXCESSIVE F.O.D., KNIFE AND SEAL CONTACT AND BEARING AREA DAMAGE.		1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995121500259	19951215	00259	SW 	1995	12	15	HEEA956164 	1	19951205	G	6220	206011149105	YOKE 		206011100159	BELL 	206 	206L3 	1182108	SW 										M/R HUB	JOURNAL FAIL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	31077	11261			A101893	51520				BEARING JOURNAL BREAKING DOWN. REPLACED WITH NEW YOKE.						1	G	7	1 	3U				H2SW 					 
1995121500260	19951215	00260	EU 	1995	12	15	HEEA956165 	1	19951205	G	6310	4638202007	CLUTCH 		4638001004 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	CAGE BROKEN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7161J	2140 			1071	S834				DURING 600 HOUR CLUTCH INSPECTION; FOUND INNER CAGE BROKEN ON CLUTCH. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U				H3EU 					 
1995121500261	19951215	00261		1995	12	15	HEEA956166 	4	19951205	G	3455	066104701	RECEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT ADF	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				ADF INOPERATIVE. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	4U				H4SW 					 
1995121500262	19951215	00262	EU 	1995	12	15	HEEA956167 	1	19951205	G	7712	10594575	TRANSMITTER 			BOLKMS	105 	BO105S 	5626006	EU 										ENG TORQUE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	624MB					S751				NEEDLE HAS AN INTERMITTENT INDICATION.						1	G	7	2 	3U				H3EU 					 
1995121500263	19951215	00263	EU 	1995	12	15	HEEA956168 	1	19951205	G	6240	10594564	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										MAST MOMENT	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	624MB					S751				NEEDLE HAS AN INTERMITTENT INDICATION.						1	G	7	2 	3U				H3EU 					 
1995121500264	19951215	00264		1995	12	15	HEEA956169 	4	19951205	G	3452	066107100	TRANSPONDER 			BELL 	412 	412 	1182202	SW 										COCKPIT ATC	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2149S					36002				TRANSPONDER NEEDS BENCH CHECK. UNIT INOPERATIVE. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	4U				H4SW 					 
1995121500265	19951215	00265		1995	12	15	HEEA956170 	4	19951205	G	3451	066107001	TRANCEIVER 			BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT DME	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	205UC					S668				DME LED READOUT IS INOPERATIVE. REPLACED BURNT F201 FUSE, BURNT INSULATOR AND BURNT INSULATING BUSHING ONE Q203 TRANSIST	OR. THIS REPAIRED SHORT TO GROUND. BENCH CHECK GOOD.					1	G	7	2 	3U				H3EU 					 
1995121500266	19951215	00266		1995	12	15	HEEA956171 	4	19951205	G	3452	066107100	TRANSPONDER 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3897N					28106				INOPERATIVE. TROUBLESHOT AND FOUND INSULATING BUSHING ON TRANSISTOR Q501 BURNT AND CAUSING A SHORT TO GROUND. REPLACED 	BUSHING. CLEANED CORROSION ON CHASIS. BENCH CHECK GOOD.					2	G	7	2 	4U				H10SW 					 
1995121500267	19951215	00267	EU 	1995	12	15	HEEA956172 	1	19951205	G	3411	PR60321	PITOT TUBE 			BOLKMS	105 	BO105S 	5626006	EU 										PITOT SYS	LEAKING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	7171A					S838				LEAKING BEYOND LIMITS. REMOVED AND REPLACED WITH SERVICEABLE PITOT TUBE.						1	G	7	2 	3U				H3EU 					 
1995121500268	19951215	00268		1995	12	15	HEEA956173 	4	19951205	G	3432	066401018	RNAV 			BELL 	214 	214ST 	1182106	SW 										COCKPIT GS	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8045T					28101				GLIDESLOPE INOPERATIVE. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						2	G	7	2 	4U				H10SW 					 
1995121500269	19951215	00269		1995	12	15	HEEA956174 	4	19951205	G	2312	064101902	TRANSCEIVER 		KY196 	BELL 	206 	206L3 	1182108	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3207Q					50540				LOSES MEMORY; VHF RADIO DISPLAY FLICKERS. FREQUENCIES ARE NOT ALL ACCESSIBLE AND WILL NOT RECEIVE.						1	G	7	1 	3U				H2SW 					 
1995121500270	19951215	00270		1995	12	15	HEEA956175 	4	19951205	G	3455	066107700	RECEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT ADF	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				FRONT CONNECTOR CORRODED.						1	G	7	2 	4U				H4SW 					 
1995121500271	19951215	00271		1995	12	15	HEEA956176 	4	19951205	G	3416	066104802	RADAR ALTIMETER 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	3893P					33012				INTERMITTENTLY WON'T TEST CORRECTLY; JUST CAUSES INDICATOR NEEDLE TO SPIN AROUND.						1	G	7	2 	4U				H4SW 					 
1996011900253	19960119	00253		1996	1	19	HEEA956177 	4	19951205	G	3452	066011410101	TRANSPONDER 		KT76 	DOUG 	MD900 	MD900 	3027375	NM 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	9214U					90000014				INTERMITTENT DISPLAY AND LOCKS UP.						1	G	7	2 	3U			NC	H19NM 					 
1995121500272	19951215	00272	EU 	1995	12	15	HEEA956178 	1	19951205	G	6310	4638202007	CLUTCH 		4638001001 	BOLKMS	105 	BO105S 	5626006	EU 										FREEWHEEL	CAGE WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911FL	1888 			227	S717				COMPLIED WITH 600 HOUR INSPECTION. SCRAPPED CLUTCH DUE TO INNER CAGE WORN BEYOND LIMITS. REPLACED WITH SERVICEABLE CLUT	CH.					1	G	7	2 	3U				H3EU 					 
1995121500273	19951215	00273		1995	12	15	HEEA956179 	4	19951205	G	3452	066106200	TRANSCEIVER 		KT76 	BOLKMS	105 	BO105S 	5626006	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	4193R					S851				NO RECEIVING LIGHT. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. REPAIRED. ADJUSTED FREQUENCY. BENCH CHECK GOOD.						1	G	7	2 	3U				H3EU 					 
1995121500274	19951215	00274		1995	12	15	HEEA956180 	4	19951205	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B 	1181511	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3181J					3771				WEAK, OFF FREQUENCY. ALIGNED RECEIVER AND ADJUSTED FREQUENCY TO SPECS. REPAIRED. REPLACED CRACKED FACEPLATE. REPLACED	 PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. REPAIRED. ADJUSTED PULSE WIDTH. BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995121500275	19951215	00275		1995	12	15	HEEA956181 	4	19951205	G	3452	071119218	CONTROL DISPLAY 			BELL 	412 	412 	1182202	SW 										COCKPIT XPONDER	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21498					36003				DISPLAY DIM IN BRIGHT LIGHT. REPLACED PHOTOCELLV101. REPAIRED. REPLACED INTERMITTENT "IDT" SWITCH S103. BENCH CHECK G	OOD.					1	G	7	2 	4U				H4SW 					 
1995121500276	19951215	00276		1995	12	15	HEEA956182 	4	19951205	G	2312	064105430	TRANSCEIVER 			BELL 	206 	206B 	1181511	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	21431					3452				DISPLAY INOPERATIVE.						1	G	7	1 	3U				H2SW 					 
1995121500277	19951215	00277		1995	12	15	HEEA956183 	4	19951205	G	3452	066106200	TRANSCEIVER 		KT76 	BELL 	206 	206B3 	1181506	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2270G					3610				PILOT REPORTED INOPERATIVE. FOUND POWER OUT LOW AT ABOUT 125W AND FREQUENCY OUT OF SPECS. ADJUSTED CAVITY OSCILLATOR V1	01 TO GET CORRECT POWER OUT AND FREQUENCY. REPLACED BURNT R477 RESISTOR. INSPECTED AND BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW 					 
1995121500278	19951215	00278		1995	12	15	HEEA956184 	4	19951205	G	3442	MI585202	ANT PEDESTAL 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT RADAR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	706AE					760275				UNIT TRACKER INTERMITTENT IN 60 DEGREES SCAN.						1	G	7	2 	3U				H1NE 					 
1995121500279	19951215	00279		1995	12	15	HEEA956185 	4	19951205	G	3451	066106602	TRANSCEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT DME	WEAK 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				UNIT HAS WEAK POWER OUT. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	4U				H4SW 					 
1995121500280	19951215	00280		1995	12	15	HEEA956186 	4	19951205	G	3455	066104701	RECEIVER 			BELL 	412 	412 	1182202	SW 										COCKPIT ADF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22608					33075				BANDS IN HIGHER FREQUENCY INOPERATIVE. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	4U				H4SW 					 
1995121500281	19951215	00281		1995	12	15	HEEA956187 	4	19951205	G	2370	9806019001	CVR 			BELL 	412 	412 	1182202	SW 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	33008	2483 				36004				CVR DOESN'T TEST						1	G	7	2 	4U				H4SW 					 
1995121500282	19951215	00282		1995	12	15	HEEA956188 	4	19951206	G	2370	9806019001	CVR 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	WONT TEST 	E			HEEA	K				NONE 				L			NO TEST 			NR	NOT REPORTED 	1			SW	03	31217	1913 				760229				CVR WILL NOT TEST.						1	G	7	2 	3U				H1NE 					 
1995121500283	19951215	00283	EU 	1995	12	15	HEEA956189 	1	19951206	G	7722	50061036	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										EXH TEMP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7171A					S838				EXH TEMP INDICATOR HAS 40 DEGREES FRICTION.						1	G	7	2 	3U				H3EU 					 
1995121500284	19951215	00284		1995	12	15	HEEA956190 	4	19951206	G	3457	0845000000	SKYNAV 5000 			SNIAS 	350 	AS350B2 	8680813	EU 										COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6095S	162 				2777				INTERMITTENTLY LOSES ALL WAYPOINTS AND SATELLITE RECEPTION.						1	G	7	1 	3U				H9EU 					 
1995121500285	19951215	00285		1995	12	15	HEEA956191 	4	19951206	G	3450	071121004	CONTROL BOX 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5748M					28102				CONTROL BOX ONES AND HUNDREDS PLACE DOES NOT INCREMENT OR DECREMENT.						2	G	7	2 	4U				H10SW 					 
1995121500286	19951215	00286		1995	12	15	HEEA956192 	4	19951206	G	3444	066104800	ALTIMETER 		KRA405 	BELL 	412 	412 	1182202	SW 										COCKPIT RAD ALT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	3893P					33012				ALTIMETER DEFECTIVE. PEGS TO HIGH SIDE						1	G	7	2 	4U				H4SW 					 
1995121500287	19951215	00287		1995	12	15	HEEA956193 	4	19951206	G	3455	071121009	CONTROL 			BELL 	412 	412 	1182202	SW 										COCKPIT ADF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				CONTROL DOES NOT INDICATE SWITCHING FROM BFO, TO ADF, TO ANT.						1	G	7	2 	4U				H4SW 					 
1995121500288	19951215	00288		1995	12	15	HEEA956194 	4	19951206	G	3453	25410038	DISPLAY 		7000CDU 	BELL 	412 	412 	1182202	SW 										COCKPIT LORAN	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2261D					33076				SEVERAL SEGMENTS ON DISPLAY DO NOT ILLUMINATE. SENT TO NAVIGATION DATA SYSTEMS FOR INSPECTION AND REPAIR.						1	G	7	2 	4U				H4SW 					 
1995121500289	19951215	00289		1995	12	15	HEEA956195 	4	19951206	G	3442	MI5851345	INDICATOR 		P40 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2258F					33073				DISPLAY FLICKERS IN ALL GREEN SCREEN.						1	G	7	2 	4U				H4SW 					 
1995121500290	19951215	00290		1995	12	15	HEEA956196 	4	19951206	G	3442	MI5851352	TRANSCEIVER 		P40 	BELL 	412 	412 	1182202	SW 										COCKPIT RADAR	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22347					36005				R/T UNIT SHUTS DOWN AFTER TURNED ON.						1	G	7	2 	4U				H4SW 					 
1995121500291	19951215	00291		1995	12	15	HEEA956197 	4	19951207	G	2312	071121540	COMM CONTROL 			BELL 	214 	214ST 	1182106	SW 										SBY SWITCH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8045T					28101				"SBY" SWITCH HAS NO SPRING TENSION. REPLACED COMM CONTROL TRANSFER SWITCH S102. REPAIRED. REPLACED HEADER P201 AND APP	LIED HUMISEAL TO HEADER FOR CORROSION CONTROL. REPLACED LENS. BENCH CHECK GOOD.					2	G	7	2 	4U				H10SW 					 
1995121500292	19951215	00292		1995	12	15	HEEA956198 	4	19951207	G	2312	071121540	COMM CONTROL 			BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	33008					36004				DISPLAY DIM IN BRIGHT LIGHT. REPLACED PHOTOCELL V101. REPAIRED. APPLIED HUMISEAL TO HEADER FOR CORROSION CONTROL. REP	LACED LENS FOR PHOTOCELL. TOUCHED UP FACEPLATE. BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995121500293	19951215	00293		1995	12	15	HEEA956199 	4	19951207	G	3444	066304401	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT	LIGHT INOP 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	911NC					7026				BENCH CHECK NEEDED. REPLACED DH LIGHT SWITCH ASSY. DS101 DUE TO INOPERATIVE LIGHT. REPAIRED. PERFORMED COMPLETE ALIGN	MENT AND CALIBRATION. BENCH CHECK GOOD.					1	G	7	2 	3U				H13EU 					 
1995121500294	19951215	00294		1995	12	15	HEEA956200 	4	19951207	G	3451	066106901	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT DME	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2149S					36002				DME WON'T LOCK ON TO STATION. PREVENTS KDI573 FROM DISPLAYING ANY DIGITS OR SEGMENTS. TROUBLESHOT AND FOUND IC-803 INTE	GRATED CIRCUIT TO BE KILLING SIGNAL. REPLACED IC803. REPAIRED PROBLEM AND UNIT BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW 					 
1995121500295	19951215	00295		1995	12	15	HEEA956201 	4	19951207	G	2312	064105430	TRANSCEIVER 			BELL 	206 	206L3 	1182108	SW 										COCKPIT VHF	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8594X					51531				NUMBERS ON DISPLAY WON'T ALL LIGHT UP.						1	G	7	1 	3U				H2SW 					 
1995121500296	19951215	00296		1995	12	15	HEEA956202 	4	19951207	G	3442	MI5851345	INDICATOR 		P40 	BELL 	412 	412 	1182202	SW 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2258F					33073				INDICATOR WILL NOT SHUT OFF IN STANDBY.						1	G	7	2 	4U				H4SW 					 
1995121500297	19951215	00297		1995	12	15	HEEA956203 	4	19951207	G	3457	0845000000	SKYNAV 5000 																	COCKPIT GPS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03										FOREIGN CHARACTERS ARE DISPLAYED AT TURN ON AND DURING OPERATION.																			 
1995121500298	19951215	00298	SW 	1995	12	15	HEEA956204 	1	19951207	G	5610	P2056891	WINDOW 			BELL 	212 	212 	1181420	SW 										COCKPIT	MIS MFG 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5736D					31135				THICKNESS OF WINDOW MUST BE A MINIMUM OF .119". THIS WINDOW IS ONLY .105" TO .107".						1	G	7	1 	4U				H4SW 					 
1995121500299	19951215	00299	NE 	1995	12	15	HEEA956205 	2	19951207	G	7210	3024780	GEARBOX 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					COMB GR BOX	OIL LEAK 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22347	15026				36005				OIL TRANSFER FROM #1 ENGINE TO GEARBOX.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995121500300	19951215	00300	EU 	1995	12	15	HEEA956206 	1	19951207	G	2844	642792002	TRANSMITTER 			SNIAS 	350 	AS350B2 	8680813	EU 										FUEL FILTER	DEFECTIVE 	E			HEEA	K				NONE 				N			FALSE WARNING 			NR	NOT REPORTED 	1			SW	03	6097Z	1058 				2820				INTERMITTENT FUEL FILTER LIGHT.						1	G	7	1 	3U				H9EU 					 
1995121500301	19951215	00301	SW 	1995	12	15	HEEA956207 	1	19951207	G	7714	206075681117	INDICATOR 			BELL 	206 	206L3 	1182108	SW 										DUAL TACH	ERR0R 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	8588X					51486				DUAL TACH INDICATES 2% SPLIT.						1	G	7	1 	3U				H2SW 					 
1995121500302	19951215	00302	EU 	1995	12	15	HEEA956208 	1	19951207	G	6730	7004109901	ACTUATOR ASSY 			BOLKMS	117 	BK117A4 	5626017	EU 										AUTO FLIGHT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	YERAL					7092				CSAS PITCH LIGHT STAYS ON ALL THE TIME						1	G	7	2 	3U				H13EU 					 
1995121500303	19951215	00303	NE 	1995	12	15	HEEA956209 	2	19951207	G	7210	3024780	GEARBOX 			BELL 	412 	412 	1182202	SW 	PWA 	PT6T 	PT6T3B 	52045	NE 					COMB GR BOX	MAKING METAL 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	33008					36004				COMBINING GR BOX MAKING METAL.						1	G	7	2 	4U	4	U		H4SW 	E22EA				 
1995121500304	19951215	00304		1995	12	15	HEEA956210 	4	19951207	G	3416	10163511839	ALTIMETER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	LIGHT INOP 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	707AE					760276				ALTIMETER LIGHT INOPERATIVE.						1	G	7	2 	3U				H1NE 					 
1995121500305	19951215	00305	SW 	1995	12	15	HEEA956213 	1	19951207	G	6730	206076062003	CYLINDER 			BELL 	206 	206L1 	1182107	SW 										M/R SERVO	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	16938	3790 				45157				SERVO BEARINGS LOOSE AND PILOT VALVE LEAKING.						1	G	7	1 	3U				H2SW 					 
1995121500306	19951215	00306		1995	12	15	HEEA956214 	1	19951207	G	7714	65201008	INDICATOR 																	COCKPIT TACH	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03		360 								RATTLE INSIDE OF TRIPLE TACH INDICATOR.																			 
1995121500307	19951215	00307	SW 	1995	12	15	HEEA956215 	1	19951207	G	7921	206360501101	COOLER 			BELL 	206 	206L3 	1182108	SW 										ENG OIL	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	6160Y					51609				HIGH ENGINE OIL TEMP. DEFECTIVE OIL COOLER.						1	G	7	1 	3U				H2SW 					 
1995121500308	19951215	00308	SW 	1995	12	15	HEEA956216 	1	19951207	G	3040	204070907002	MOTOR 			BELL 	412 	412 	1182202	SW 										WIPER	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	22608					33075				WHEN MOUNTED IN AIRFRAME WIPER MOTOR VIBRATES. COMING LOOSE FROM CONVERTER.						1	G	7	2 	4U				H4SW 					 
1995121500309	19951215	00309	SW 	1995	12	15	HEEA956217 	1	19951208	G	7714	222375021113	INDICATOR 			BELL 	230 	230 	1182149	SW 										COCKPIT TACH	FLUCTUATES 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	770 				23009				TRIPLE TACH FLUCTUATES ON HIGH END. WILL NOT REACH 100%.						1	G	7	2 	3U			NC	H9SW 					 
1995122200367	19951222	00367	SW 	1995	12	22	HEEA956219 	1	19951211	G	6220	412010111103	FITTING 		412010100193	BELL 	412 	412 	1182202	SW 										M/R	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	2298Z				AAD50024	33077				BOLT HOLE EAR NOT CUT DOWN.						1	G	7	2 	4U				H4SW 					 
1995122200368	19951222	00368	GL 	1995	12	22	HEEA956220 	2	19951211	G	7320	222360703101	SOLENOID 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					IDLE STOP	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2654 				23009				INTERMITTENT IDLE STOP.						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995122200369	19951222	00369		1995	12	22	HEEA956221 	4	19951211	G	3423	022200041EQ	COMPASS 			AEROSP	SA365 	SA365N 	8680669	EU 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	9UW					6076				GLASS CRAZED CAUSING WATER EVAPORATION.						1	G	7	2 	3U				H10EU 					 
1995122200370	19951222	00370	EU 	1995	12	22	HEEA956222 	1	19951211	G	2822	1176415103	PUMP 			BOLKMS	117 	BK117B1 	5626012	EU 										FUEL BOOST	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	117BK					7229				BOOST PUMP INOPERATIVE.						1	G	7	2 	3U				H13EU 					 
1995122200371	19951222	00371	GL 	1995	12	22	HEEA956224 	2	19951212	G	7250	23030974	SPLINE ADAPTER 		23035128 	BELL 	206 	206L3 	1182108	SW 	ALLSN 	250C 	250C30P 	03013	GL 					TURBINE	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	206FS				CAT97894	51506	CAE890112			RECEIVING INSPECTION OF NEW, NEVER INSTALLED SPLINE ADAPTER INDICATED I.D. MANUFACTURED .0005" OVER MAX B.P. SPECS OF .6	565". ADAPTER MEASURES .657. INSTALLED NEW SPLINE ADAPTER. SHIPMENT OF PART AND SUBMITTAL FOR CREDIT ACCOMPLISHED ON A	FA# 24444A.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200372	19951222	00372	GL 	1995	12	22	HEEA956229 	2	19951212	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					3RD STAGE	BLADE CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	50182	393 			CAT70162	45242	CAE860164			ENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER	 C1245F-RMG-1195. ZYGLO INSPECTION REVEALED ONE EACH INDICATION 1/8" FROM SHROUD OF L/E BACK SIDE OF BLADE. INDICATION	DOES NOT GO THROUGH BLADE. INSTALLED SERVICEABLE 3RD STAGE WHEEL.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200373	19951222	00373	GL 	1995	12	22	HEEA956230 	2	19951212	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					3RD STAGE	BLADE CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5017G	552 			CAT28005	45228	CAE860290			ENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER	 C1245F-RMG-1195. ZYGLO INSPECTION REVEALED SIX EACH CRACKS ON L/E OF BLADES 1/8" FROM SHROUD 3/16" LONG. INSTALLED SER	VICEABLE 3RD STAGE WHEEL. RETURNED TO ALLISON ON RO#0635. APPLICATION FOR CREDIT ACCOMPLISHED ON AFA# 24437A.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200374	19951222	00374	GL 	1995	12	22	HEEA956231 	2	19951212	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					3RD STAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5007Y	453 			CAT70022	45192	CAE860583			ENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER	 C1245F-RMG-1195. ZYGLO INSPECTION REVEALED ONE EACH INDICATION ON L/E 15/16" FROM HUB. INSTALLED SERVICEABLE 3RD STAGE	 WHEEL.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200375	19951222	00375	GL 	1995	12	22	HEEA956232 	2	19951212	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					3RD STAGE	BLADE CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3905B	250 			CAT70502	45598	CAE860771			ENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER	 C1245F-RMG-1195. ZYGLO INSPECTION REVEALED ONE EACH BLADE CRACKED 3/32" FROM HUB L/E 3/16" LONG, AND ONE EACH BLADECRA	CKED 1/8" FROM SHROUD L/E 3/16" LONG. INSTALLED SERVICEABLE 3RD STAGE WHEEL.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200376	19951222	00376	GL 	1995	12	22	HEEA956233 	2	19951212	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					3RD STAGE	BLADE CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5745S	311 			CAT70467	45491	CAE860136			ENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER	 C1245F-RMG-1195. ZYGLO INSPECTION REVEALED FOUR EACH BLADES CRACKED 3/16" LONG, 1/16" FROM SHROUD ON L/E. INSTALLED	 SERVICEABLE 3RD STAGE WHEEL.				1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200377	19951222	00377	GL 	1995	12	22	HEEA956234 	2	19951212	G	7250	23001977	WHEEL 		23033185 	BELL 	206 	206L1 	1182107	SW 	ALLSN 	250C 	250C28B 	03013	GL 					3RD STAGE	CRACKED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	22425	350 			CAT70343	45743	CAE860046			ENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER	 C1245F-RMG-1195. ZYGLO INSPECTION REVEALED THREE EACH CRACKS 3/16" LONG, 1/16" FROM SHROUD ON L/E. CRACKSLOCATED 1	80 DEGREES AROUND WHEEL, ONE EACH INDICATION 1/8" LONG ON L/E 1/16" FROM HUB AREA. INSTALLED SERVICEABLE 3RD STAGE WHEEL	.			1	G	7	1 	3U	3	U		H2SW 	E1GL				 
1995122200378	19951222	00378	EU 	1995	12	22	HEEA956235 	1	19951213	G	5230	D355600041	STRUCTURE 		D350600043 	AEROSP	AS355 	AS355F1 	8680810	EU 										LT CARGO DOOR	MISINSTALLED 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	5796S					5164				FORWARD UPPER CORNER DOES NOT FIT PROPERLY. MODIFIED LT CARGO DOOR TO FIT AIRCRAFT.						1	G	7	2 	3U				H11EU 					 
1995122200379	19951222	00379	NE 	1995	12	22	HEEA956236 	1	19951213	G	3340	A490ATSDF1428	POWER SUPPLY 			SKRSKY	S76 	S76A 	8143006	NE 										STROBE	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1547D					760077				NO OUTPUT TO STROBE LIGHT, WILL NOT FLASH. TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H1NE 					 
1995122200380	19951222	00380		1995	12	22	HEEA956237 	4	19951213	G	2562	ELT910	ELT 	NARCO 		AEROSP	AS355 	AS355F1 	8680810	EU 										G SWITCH	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y					5141				ELT G SWITCH INOPERATIVE.						1	G	7	2 	3U				H11EU 					 
1995122200381	19951222	00381	NE 	1995	12	22	HEEA956238 	1	19951213	G	2435	200SGL1064	ARMATURE 			SKRSKY	S76 	S76A 	8143006	NE 										START/GEN	FAILED 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1546K					760082				STARTER GENERATOR CAUSING GRINDING NOISE AND NO VOLTAGE OUTPUT.						1	G	7	2 	3U				H1NE 					 
1995122200382	19951222	00382	EU 	1995	12	22	HEEA956241 	1	19951213	G	6240	KDW02	WARNING BOX 			BOLKMS	105 	BO105S 	5626006	EU 										ROTOR RPM	MALFUNCTION 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	967MB					S737				LOW ROTOR HAS CONTINUOUS HORN. . TIME SINCE REPAIR 11:15.						1	G	7	2 	3U				H3EU 					 
1995122200383	19951222	00383		1995	12	22	HEEA956243 	4	19951213	G	2210	7690001802106	ACTUATOR 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2743E	5152 				760155				AFCS ACTUATOR HAS BAD POTS AND EXCESSIVE SHAFT END PLAY.						1	G	7	2 	3U				H1NE 					 
1995122200384	19951222	00384	SW 	1995	12	22	HEEA956244 	1	19951213	G	2432	39563001	BATTERY 			BELL 	412 	412 	1182202	SW 										STANDBY PACK	FAIL TEST 	E			HEEA	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	2298Z	980 				33077				BATTERY PACK FAILED DISCHARGING TEST. ALSO ONE YEAR INSPECTION DUE.						1	G	7	2 	4U				H4SW 					 
1995122200385	19951222	00385	SW 	1995	12	22	HEEA956245 	1	19951213	G	6330	206033506101	RESTRAINT 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	DETERIORATING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	41791					51465				RESTRAINT RUBBER DETERIORATING IN MOUNT.						1	G	7	1 	3U				H2SW 					 
1995122200386	19951222	00386	SW 	1995	12	22	HEEA956246 	1	19951213	G	6330	206033506101	RESTRAINT 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	BEARING UNSTAKED	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3116L					51529				TRANSMISSION RESTRAINT BEARING UNSTAKED.						1	G	7	1 	3U				H2SW 					 
1995122200387	19951222	00387	SW 	1995	12	22	HEEA956247 	1	19951213	G	6330	206033516101	FLEXURE 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	COAT UNBONDED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8587X					51464				FLEXURE COATING COMING OFF AND BUBBLED.						1	G	7	1 	3U				H2SW 					 
1995122200388	19951222	00388	SW 	1995	12	22	HEEA956248 	1	19951213	G	6330	206033516101	FLEXURE 			BELL 	206 	206L3 	1182108	SW 										TRANSMISSION	DETERIORATING 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8589X					51487				ELASTOMERIC COVERING DETERIORATING.						1	G	7	1 	3U				H2SW 					 
1995122200389	19951222	00389	SW 	1995	12	22	HEEA956249 	1	19951213	G	6330	206033516101	FLEXURE 			BELL 	206 	206L1 	1182107	SW 										TRANSMISSION	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2251A					45755				FLEXURE WORN.						1	G	7	1 	3U				H2SW 					 
1995122200390	19951222	00390	EU 	1995	12	22	HEEA956250 	1	19951213	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117B1 	5626012	EU 										FUEL QTY	INTERMITTENT 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	217UC	1249 				7152				#1 INTERMITTENT DROPS TO ZERO. SENT TO MASCO FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H13EU 					 
1995122200391	19951222	00391		1995	12	22	HEEA956251 	4	19951213	G	3421	7660002113103	VERTICAL GYRO 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT VG	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31217					760229				ADI TUMBLES INTERMITTENTLY.						1	G	7	2 	3U				H1NE 					 
1995122200392	19951222	00392	EU 	1995	12	22	HEEA956252 	1	19951213	G	7722	56265550011	INDICATOR 			AEROSP	AS355 	AS355F1 	8680810	EU 										COCKPIT T4	READS LOW 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	5793Y					5141				INDICATOR READS LOW AT 800 DEGREES AND CRACKED SEAL.						1	G	7	2 	3U				H11EU 					 
1995122200393	19951222	00393		1995	12	22	HEEA956254 	4	19951213	G	2210	7690001802106	ACTUATOR 			SKRSKY	S76 	S76A 	8143006	NE 										AFCS	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	4253S	4452 				760035				AFCS ACTUATOR POT CHECK BAD						1	G	7	2 	3U				H1NE 					 
1995122200394	19951222	00394	SW 	1995	12	22	HEEA956255 	1	19951213	G	6710	214001347005	ACTUATOR Y 			BELL 	412 	412 	1182202	SW 										ROTARY	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	7128R					36007				ROTARY ACTUATOR DEFECTIVE. FORCE TRIM WONT RELEASE.						1	G	7	2 	4U				H4SW 					 
1995122200395	19951222	00395	SW 	1995	12	22	HEEA956256 	1	19951213	G	6300	212040149001	GEAR ASSY 			BELL 	212 	212 	1181420	SW 										SEAL RIDE	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1079U					31122				WORN SEAL RIDE AREA.						1	G	7	1 	4U				H4SW 					 
1995122200396	19951222	00396		1995	12	22	HEEA956257 	4	19951213	G	3416	214175278101	INDICATOR 			BELL 	412 	412 	1182202	SW 										COCKPIT ENCODER	READS HIGH 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	2148K	5039 				36001				ENCODER READS 120 FEET HIGH AT 20K.						1	G	7	2 	4U				H4SW 					 
1995122200397	19951222	00397	SW 	1995	12	22	HEEA956258 	1	19951213	G	6730	206076062003	CYLINDER 			BELL 	206 	206L3 	1182108	SW 										M/R	LEAKING 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	6610Y	14260				51419				CYLINDER LEAKING.						1	G	7	1 	3U				H2SW 					 
1995122200398	19951222	00398	NE 	1995	12	22	HEEA956259 	1	19951213	G	2161	1296321	SENSOR 			SKRSKY	S76 	S76A 	8143006	NE 										CABIN TEMP	STICKING 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	31219					760230				SENSOR STICKING AND DOES NOT REGULATE TEMPERATURE.						1	G	7	2 	3U				H1NE 					 
1995122200399	19951222	00399	EU 	1995	12	22	HEEA956260 	1	19951213	G	7714	DL43638	INDICATOR 			BOLKMS	105 	BO105S 	5626006	EU 										TRIPLE TACH	ERROR 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	105WK					S812				INTERMITTENTLY DOES NOT INDICATE AND HAS EXCESSIVE FRICTION ERROR.						1	G	7	2 	3U				H3EU 					 
1995122200400	19951222	00400		1995	12	22	HEEA956261 	4	19951213	G	3444	7001840913	TRANSCEIVER 			SKRSKY	S76 	S76A 	8143006	NE 										COCKPIT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	1546G	389 				760076				WHEN UNIT WARMS UP, VALID LIGHT GOES OFF.						1	G	7	2 	3U				H1NE 					 
1995122200401	19951222	00401	SW 	1995	12	22	HEEA956262 	1	19951213	G	7722	206375006101	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										COCKPIT TOT	STICKS 	E			HEEA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	03	1077A	697 				45382				NEEDLE STICKS INTERMITTENTLY AT 600 DEGREES CELSUIS AND ABOVE.						1	G	7	1 	3U				H2SW 					 
1995122900243	19951229	00243	SW 	1995	12	29	HEEA956300 	1	19951220	G	7714	214175249103	INDICATOR 			BELL 	214 	214ST 	1182106	SW 										COCKPIT	INOPERATIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N	22 				28106				NEEDLE DOESN'T MOVE.						2	G	7	2 	4U				H10SW 					 
1995122900244	19951229	00244	EU 	1995	12	29	HEEA956301 	1	19951220	G	6220	1051418303	BUSHING 			BOLKMS	105 	BO105S 	5626006	EU 										M/R	MIS MFG 	E			HEEA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03										RADIUS NOT FINISHED. MIS-MANUFACTURED.						1	G	7	2 	3U				H3EU 					 
1995122900245	19951229	00245	EU 	1995	12	29	HEEA956304 	1	19951220	G	6420	350A33211905	BODY 			SNIAS 	350 	AS350B2 	8680813	EU 										T/R	BEARING WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	6100R	231 				2862				WORN LAMINATE BEARINGS.						1	G	7	1 	3U				H9EU 					 
1995122900246	19951229	00246	SW 	1995	12	29	HEEA956305 	1	19951220	G	5320	206031314091S	CHANNEL 			BELL 	206 	206L1 	1182107	SW 										AIRFRAME FWD	MIS FITTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										CHANNEL HAS EXCESSIVE BOW ALONG UPPER FLANGE RADIUS. WITH CHANNEL INSTALLED IN AIRFRAME AT FORWARD AND AFT ENDS, THE CE	NTER AREA OF CHANNEL IS APPROXIMATELY 1/8" TO 3/16" LOWER THAN ORIGINAL LONGERON. THIS DIFFERENCE WILL RESULT INLOWERIN	G OF THE R/H ENGINE MOUNT CLIP AND BRACKET.				1	G	7	1 	3U				H2SW 					 
1995122900247	19951229	00247	SW 	1995	12	29	HEEA956307 	1	19951220	G	6320	204040701101	BEVEL GEAR TOOTH		412040002113	BELL 	412 	412 	1182202	SW 										XMSN	FAILED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2148K				ANG00073	36001				RECEIVED TRANSMISSION WITH METAL IN OIL. DISASSEMBLED AND FOUND BEVEL GEAR LISTED ABOVE WITH A TOOTH BROKEN OFF. PART I	S SCRAPPED CONDITION.					1	G	7	2 	4U				H4SW 					 
1995122900248	19951229	00248	SW 	1995	12	29	HEEA956308 	1	19951220	G	3212	222325023101	SWITCH 			BELL 	230 	230 	1182149	SW 										FLOAT	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2682 				23009				ON FLOAT INSPECTION, SWITCH WORKS INTERMITTENTLY.						1	G	7	2 	3U			NC	H9SW 					 
1995122900249	19951229	00249	SW 	1995	12	29	HEEA956309 	1	19951220	G	6410	214011819101	BEARING 		214011801117	BELL 	214 	214ST 	1182106	SW 										T/R	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	3897N	518 			A407	28106				BEARING LINER SMASHED OUT. EXCESSIVE WEAR ON BLADE BEARINGS.						2	G	7	2 	4U				H10SW 					 
1995122900250	19951229	00250	SW 	1995	12	29	HEEA956310 	1	19951222	G	6210	206010200033	BLADE 			BELL 	206 	206B3 	1181506	SW 										M/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2285B	1452 				3642				EXCESSIVE AMOUNT OF EXFOLIATION OF UPPER LEADING EDGE AND LOWER LEADING EDGE NEAR THE TIP WITH PIECES MISSING.						1	G	7	1 	3U				H2SW 					 
1995122900251	19951229	00251	SW 	1995	12	29	HEEA956311 	1	19951222	G	6210	206010200033	BLADE 			BELL 	206 	206B3 	1181506	SW 										M/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	2285B	1452 				3642				EXCESSIVE AMOUNT OF EXFOLIATION OF THE LEADING EDGE.						1	G	7	1 	3U				H2SW 					 
1995122900252	19951229	00252	SW 	1995	12	29	HEEA956312 	1	19951222	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	CORRODED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	27766	3181 				45312				EXCESSIVE AMOUNT OF EXFOLIATION OF THE LEADING EDGE.						1	G	7	1 	3U				H2SW 					 
1996020200315	19960202	00315	SW 	1996	2	2	HEEA956313 	1	19951227	G	6410	212010750105	BLADE 		212010701143	BELL 	212 	212 	1181420	SW 										T/R	DENTED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	5010F	313 			AFS2471	30936				TR BLADE HAS DENT ON TRAILING EDGE.						1	G	7	1 	4U				H4SW 					 
1996020200316	19960202	00316	SW 	1996	2	2	HEEA956321 	1	19951227	G	5210	1021401	ROLLER ASSY 			BELL 	230 	230 	1182149	SW 										DOOR	SHEARED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	1243 				23009				ROLLER AXLE SHEARED.						1	G	7	2 	3U			NC	H9SW 					 
1996020200317	19960202	00317	SW 	1996	2	2	HEEA956322 	1	19951227	G	6210	206015001107	BLADE 			BELL 	206 	206L3 	1182108	SW 										M/R	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	363BH	644 				51345				BLADE HAS A REPAIR NEAR THE LAST FINGER ON THE UPPER SURFACE THAT WAS DONE BY BELL HELICOPTER TEXTRON. WHEN PRIMING THE	 AREA MOISTURE STARTED SEEPING OUT. BLADE RECEIVED INSTALLED ON AIRCRAFT 12-1-95.					1	G	7	1 	3U				H2SW 					 
1996020200318	19960202	00318	SW 	1996	2	2	HEEA956323 	1	19951227	G	6420	214011819101	BEARING 		214011801117	BELL 	214 	214ST 	1182106	SW 										T/R FEATHER	WORN 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8045T	431 			A733	28101				ONE EACH BEARING UNSTAKED IN HUB AND THREE EACH BEARINGS WORN. REPLACED BEARINGS.						2	G	7	2 	4U				H10SW 					 
1996020200319	19960202	00319	SW 	1996	2	2	HEEA956325 	1	19951227	G	6320	222040003119	TRANSMISSION 			BELL 	230 	230 	1182149	SW 										T/R QUILL	OIL LEAK 	E			HEEA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	230UN	151 				23009				TRANSMISSIONOIL LEAK,						1	G	7	2 	3U			NC	H9SW 					 
1996020200320	19960202	00320	SW 	1996	2	2	HEEA956326 	1	19951227	G	6310	222044002101	COUPLING 			BELL 	230 	230 	1182149	SW 										M/R DRIVE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2616 				23009				COUPLINGSLINGING GREASE.						1	G	7	2 	3U			NC	H9SW 					 
1996020200321	19960202	00321	SW 	1996	2	2	HEEA956327 	1	19951227	G	6310	222044002101	COUPLING 			BELL 	230 	230 	1182149	SW 										M/R DRIVE	DEFECTIVE 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	230UN	2623 				23009				COUPLING SLINGING GREASE.						1	G	7	2 	3U			NC	H9SW 					 
1996020200322	19960202	00322	SW 	1996	2	2	HEEA956328 	1	19951229	G	3212	214073929105	FLOAT VALVE 			BELL 	214 	214ST 	1182106	SW 										OUTLET PORT	CONTAMINATED 	E			HEEA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03										VALVE WAS RECEIVED FROM BELL. UPON INSPECTION BY THE ACCESSORY SHOP, CONTAMINATION WAS FOUND IN THE OUTLET PORT.						2	G	7	2 	4U				H10SW 					 
1995050500252	19950505	00252	SW 	1995	5	5	HEED9510 	1	19950420	G	6220	222310117103	SPRING 			BELL 	230 	230 	1182149	SW 										M/R FLAPPING	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	431 				23015				AIRCRAFT AOG, REMOVED SERIAL NOS. LK-0006, LK-0021 ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500253	19950505	00253	SW 	1995	5	5	HEED95103 	1	19950424	G	7933	MS280343	TEMP BULB 			BELL 	230 	230 	1182149	SW 										NR 1 ENG OIL	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	182 				23015				#1 ENGINE OIL TEMP WENT TO ZERO. INSTALLED NEW TEMP BULB FROM EXXON STOCK.						1	G	7	2 	3U			NC	H9SW 					 
1995050500254	19950505	00254	SW 	1995	5	5	HEED95106 	1	19950424	G	6320	222040243001	TAB LOC-NUT 			BELL 	230 	230 	1182149	SW 										NR 1 INPUT QUILL	DEFECTIVE 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	170 				23015				#1 INPUT QUILL SEAL CHANGE LEAKING. ORDER NEW SEAL						1	G	7	2 	3U			NC	H9SW 					 
1995050500255	19950505	00255	SW 	1995	5	5	HEED95107 	1	19950424	G	6320	M832481032	PACKING 			BELL 	230 	230 	1182149	SW 										NR 1 INPUT QUILL	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	170 				23015				#1 INPUT QUILL SEAL CHANGE LEAKING. ORDER NEW PACKING						1	G	7	2 	3U			NC	H9SW 					 
1995050500256	19950505	00256	SW 	1995	5	5	HEED95108 	1	19950424	G	6320	MS29561114	PACKING 			BELL 	230 	230 	1182149	SW 										NR 1 INPUT QUILL	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	170 				23015				#1 INPUT QUILL SEAL CHANGE LEAKING. ORDER NEW PACKING						1	G	7	2 	3U			NC	H9SW 					 
1995050500257	19950505	00257	SW 	1995	5	5	HEED95109 	1	19950424	G	6320	MS29561247	PACKING 			BELL 	230 	230 	1182149	SW 										NR 1 INPUT QUILL	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	170 				23015				#1 INPUT QUILL SEAL CHANGE LEAKING. ORDER NEW PACKING						1	G	7	2 	3U			NC	H9SW 					 
1995050500258	19950505	00258	SW 	1995	5	5	HEED9511 	1	19950420	G	6330	222331617101	ISOLATION MOUNT 			BELL 	230 	230 	1182149	SW 										M/R XMSN	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	460 				23015				OUTBOARD BEARING OF LATERAL ISOLATION MOUNT WORN .012 RADIAL AND .007 - .010 AXIAL. ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500259	19950505	00259	SW 	1995	5	5	HEED95110 	1	19950424	G	6320	M832481034	PACKING 			BELL 	230 	230 	1182149	SW 										NR 1 QUILL	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	170 				23015				#1 INPUT QUILL SEAL CHANGE LEAKING. ORDER NEW PACKING						1	G	7	2 	3U			NC	H9SW 					 
1995050500260	19950505	00260	SW 	1995	5	5	HEED95111 	1	19950424	G	7933	MS28034	TEMPERATURE BULB			BELL 	230 	230 	1182149	SW 										OIL TEMP	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	170 				23015				TEMP BULB INOPERATIVE REPLACED WITH ONE FROM EXXON STOCK						1	G	7	2 	3U			NC	H9SW 					 
1995050500261	19950505	00261	SW 	1995	5	5	HEED95112 	1	19950424	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										LIGHTING	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	170 				23015				LAMP INOPERATIVE. REPLACED WITH ONE FROM EXXON STOCK						1	G	7	2 	3U			NC	H9SW 					 
1995050500262	19950505	00262	SW 	1995	5	5	HEED95120 	1	19950424	G	6220	222310117103	SPRING 			BELL 	230 	230 	1182149	SW 										M/R FLAPPING	BEARING FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	39 				23015				BEARING SEPARATED BEYOND LIMITS. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500263	19950505	00263	SW 	1995	5	5	HEED95121 	1	19950425	G	6220	222310117103	SPRING 			BELL 	230 	230 	1182149	SW 										M/R FLAPPING	BEARING FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	39 				23015				BEARING SEPERATED BEYOND LIMITS. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500264	19950505	00264	SW 	1995	5	5	HEED95122 	1	19950425	G	3610	222325017101	VALVE ASSY 			BELL 	230 	230 	1182149	SW 										AIR VALVE	ADJ BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	39 				23015				VALVE ADJUSTMENT CONTROL BROKEN. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500265	19950505	00265	SW 	1995	5	5	HEED9513 	1	19950420	G	6310	222044006109	SHAFT ASSY 			BELL 	230 	230 	1182149	SW 										FWD COUPLING	GREASE LEAK 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	460 				23015				FORWARD COUPLING SLINGING GREASE REPLACED WITH NEW PART, ALSO COMPLIED WITH ASB 230-93-2, REV. 1. ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500266	19950505	00266	SW 	1995	5	5	HEED95132 	1	19950425	G	6320	222040243001	TAB LOCKNUT 			BELL 	230 	230 	1182149	SW 										M/R XMSN	SEAL LEAK 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	231 				23015				SEAL LEAKING. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500267	19950505	00267	SW 	1995	5	5	HEED95137 	1	19950425	G	6220	NAS6268	BOLT 		222012101105	BELL 	230 	230 	1182149	SW 										M/R TRUNNION	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	231 			A23	23015				MAIN ROTOR TRUNNION BOLTS WORN. FOUND ON 50 HOUR INSPECTION ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500268	19950505	00268		1995	5	5	HEED95138 	4	19950425	G	2312	07101215070	CONTROL HEAD 			BELL 	230 	230 	1182149	SW 										COCKPIT VHF	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	253 				23015				LOSES MEMORY WHEN RADIO IS OFF. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500269	19950505	00269	SW 	1995	5	5	HEED9514 	1	19950420	G	6220	222010151105	WEIGHT 			BELL 	230 	230 	1182149	SW 										M/R HUB	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	431 				23015				BALANCE WEIGHT FOR M/R BLADE DEFECTIVE. ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500270	19950505	00270	SW 	1995	5	5	HEED9515 	1	19950420	G	6720	222312702101	LINK 			BELL 	230 	230 	1182149	SW 										T/R	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	92 				23015				PARTS WORN BEYOND EXXON LIMITS. ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500271	19950505	00271	SW 	1995	5	5	HEED95154 	1	19950425	G	6730	230360701103	ACTUATOR 			BELL 	230 	230 	1182149	SW 										SERVO SYS	SEIZED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	326 				23015				ACTUATOR WOULD NOT MOVE. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500272	19950505	00272	SW 	1995	5	5	HEED95156 	1	19950425	G	3220	MS9386314	PACKING 			BELL 	230 	230 	1182149	SW 										SKID STINGER	LOOSE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	326 				23015				TAIL SKID STINGER LOOSE, REPLACE 2 EACH O'RING SEAL IN STINGER SUPPORT ASSEMBLY. REMOVED FROM CONSIGNMENT KIT,						1	G	7	2 	3U			NC	H9SW 					 
1995050500273	19950505	00273	GL 	1995	5	5	HEED95157 	1	19950425	G	6710	206062721105	ACTUATOR 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					ENG	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	326 				23015				ACTUATOR FAILED TO RESPOND TO SWITCH. ORDERED NEW						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995050500274	19950505	00274	SW 	1995	5	5	HEED95169 	1	19950425	G	6720	222042001007	GEARBOX 			BELL 	230 	230 	1182149	SW 										T/R	LINK FAILURE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	386 				23015				T/R PITCH LINK FAILURE. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500275	19950505	00275	SW 	1995	5	5	HEED95170 	1	19950425	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										LIGHTING	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	386 				23015				BULB BLOWN. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500276	19950505	00276	SW 	1995	5	5	HEED95172 	1	19950425	G	6720	222012737001	RETENTION NUT 			BELL 	230 	230 	1182149	SW 										T/R PITCH	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	386 				23015				REPLACE DUE TO T/R PITCH CHANGE LINK FAILURE. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500277	19950505	00277	SW 	1995	5	5	HEED95173 	1	19950425	G	6720	222312702101	LINK 			BELL 	230 	230 	1182149	SW 										T/R PITCH	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	385 				23015				PITCH LINK FAILED. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500278	19950505	00278	SW 	1995	5	5	HEED95191 	1	19950426	G	6730	222382001105	SERVO 			BELL 	230 	230 	1182149	SW 										SERVO SYS	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	812 				23015				WORN BEARINGS AND LEAKING. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500279	19950505	00279	SW 	1995	5	5	HEED95195 	1	19950426	G	6520	222342401103	SEAL 		222042001007	BELL 	230 	230 	1182149	SW 										T/R GR BOX	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	444 			A446	23015				T/R GEARBOX INPUT SEAL LEAKING. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500280	19950505	00280	SW 	1995	5	5	HEED95197 	1	19950426	G	6520	10007220	PLUG 		222042001007	BELL 	230 	230 	1182149	SW 										T/R GR BOX	SEAL LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	444 			A446	23015				T/R GEARBOX INPUT SEAL LEAKING. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500281	19950505	00281		1995	5	5	HEED9520 	4	19950420	G	3444	066104802	ALTIMETER 			BELL 	230 	230 	1182149	SW 										COCKPIT	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	491 				23015				NEEDLE PEGS ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500282	19950505	00282		1995	5	5	HEED95202 	4	19950426	G	3454	230077522115	CABLE ASSY 			SKRSKY	S76 	S76C 	8143008	NE 										VOR SYS	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	804 				760406				BOTH VOR NEEDLES HUNT. NEW CABLE MFG WITH NEW COAX AND CONVERTORS						1	G	7	2 	3U			NC	H1NE 					 
1995050500283	19950505	00283	SW 	1995	5	5	HEED95203 	1	19950426	G	3340	01077028521	STROBE LIGHT 			BELL 	230 	230 	1182149	SW 										POWER SUPPLY	MALFUNCTION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	843 				23015				POWER SUPPLY CAUSES CIRCUIT BREAKER TO POP. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500284	19950505	00284	SW 	1995	5	5	HEED95205 	1	19950426	G	6710	222031638101	SHIM FLEX REST 			BELL 	230 	230 	1182149	SW 										M/R	CHAFING 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	834 				23015				FOUND CAM ARMS CHAFING, RESHIMMED. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500285	19950505	00285	SW 	1995	5	5	HEED95206 	1	19950426	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										SEARCH LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	87 				23015				SEARCH LIGHT INOPERATIVE ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500286	19950505	00286	SW 	1995	5	5	HEED95207 	1	19950426	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	60 				23015				BULB BURNT OUT. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500287	19950505	00287	SW 	1995	5	5	HEED95208 	1	19950426	G	6321	5009209	LINING 			BELL 	230 	230 	1182149	SW 										ROTOR BRAKE	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	665 				23015				LININGS WORN. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500288	19950505	00288	SW 	1995	5	5	HEED95209 	1	19950426	G	3222	MS9386314	PACKING 			BELL 	230 	230 	1182149	SW 										STINGER	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	290 				23015				INNER SURFACE WORN FLAT CAUSING DELAY IN STINGER. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500289	19950505	00289	SW 	1995	5	5	HEED9521 	1	19950420	G	2435	206062200119	GENERATOR 			BELL 	230 	230 	1182149	SW 										START GEN	FAILED 	E			HEED	K				NONE 				H	B		ELECT. POWER LOSS-50 PC 	SMOKE/FUMES/ODORS/SPARKS 		IN	INSP/MAINT 	1			SW	03	236X	26 				23015				#2 GENERATOR WILL NOT COME ON LINE, SMOKES IN STARTER MODE. ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500290	19950505	00290		1995	5	5	HEED95217 	4	19950426	G	3422	2594484	TRANSMITTER 			SKRSKY	S76 	S76C 	8143008	NE 										FLUX VALVE	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	20 				760405				FLUX VALVE PRECESS 30 AND WILL NOT SLAVE RMI. ORDER NEW						1	G	7	2 	3U			NC	H1NE 					 
1995050500291	19950505	00291	NE 	1995	5	5	HEED95219 	1	19950426	G	6230	SB5200001	SLEEVE BEARING 		761040802004	SKRSKY	S76 	S76A 	8143006	NE 										SWASHPLATE	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	15458	516 			A18500596	760212				EXCESSIVE WEAR. REMOVED S/NOS 21701, 21390, 31823, 31912 INSTALLED S/NOS 33789, 33910, 33790, 34068 ORDER NEW S/NOS 34	834, 35664, 35637, 35765					1	G	7	2 	3U				H1NE 					 
1995050500292	19950505	00292	SW 	1995	5	5	HEED9522 	1	19950421	G	2430	A772XTA	RELAY 			BELL 	230 	230 	1182149	SW 										DC SYS	FAULTY 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	517 				23015				BATTERY RELAY AND BUSS INTERCONNECT LIGHTS ON AT SAME TIME, MUST BE RESET OFTEN. ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995080400023	19950804	00023	NE 	1995	8	4	HEED95227 	1	19950711	G	2913	7665009808101	PUMP 			SKRSKY	S76 	S76C 	8143008	NE 										HYD PUMP	SEAL LEAK 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	89H	2 				760406				PUMP SEAL LEAKING. REPLACE PUMP						1	G	7	2 	3U			NC	H1NE 					 
1995080400024	19950804	00024	NE 	1995	8	4	HEED95228 	1	19950711	G	6320	7635109600044	TRANSMISSION 			SKRSKY	S76 	S76C 	8143008	NE 										MAIN GR BOX	CORRODED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	2 				760406				REPAIR OF TRANSMISSION FOUND EXCESSIVE CORRISION ON UPPER HOUSING S/N (A001-00163) ON THE OIL COOLER BLOWER DRIVE QUIL	L MOUNTING SURFACE.					1	G	7	2 	3U			NC	H1NE 					 
1995050500293	19950505	00293	SW 	1995	5	5	HEED9523 	1	19950421	G	2436	222375060115	REGULATOR 			BELL 	230 	230 	1182149	SW 										DC REG	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	580 				23015				#2 ENGINE START DISENGAGE TRIPS BUSS INTERCONNECT, MUST RESET BATTERY SWITCH TO GET BUSS INTERCONNECT BACK ON LINE. ORDE	RED NEW PART.					1	G	7	2 	3U			NC	H9SW 					 
1995080400025	19950804	00025	SW 	1995	8	4	HEED95230 	1	19950711	G	2435	M832481113	SEAL 			BELL 	230 	230 	1182149	SW 										START/GEN	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	824 				23015				STARTER GEN GARLOCK SEAL CHANGE DUE TO LEAKING. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400026	19950804	00026	SW 	1995	8	4	HEED95231 	1	19950711	G	5610	222031291106	HINGE 			BELL 	230 	230 	1182149	SW 										PILOT VENT	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	979 				23015				HINGE BROKEN ON PILOT VENT WINDOW. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400027	19950804	00027	SW 	1995	8	4	HEED95237 	1	19950711	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										LANDING LIGHT	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	99 				23015				FOUND LANDING LIGHT INOPERATIVE ON DAILY INSPECTION. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400028	19950804	00028	SW 	1995	8	4	HEED95238 	1	19950711	G	3340	MS25237387	BULB 			BELL 	230 	230 	1182149	SW 										LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1029 				23015				LAMP BURNT OUT. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400029	19950804	00029	SW 	1995	8	4	HEED95239 	1	19950711	G	6220	222011111101	FLAPPING SPRING 			BELL 	230 	230 	1182149	SW 										M/R	SEPARATION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	537 				23015				FLAPPING SPRING SEPERATION. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400030	19950804	00030	SW 	1995	8	4	HEED95240 	1	19950711	G	6220	222310117103	SPRING 			BELL 	230 	230 	1182149	SW 										M/R	SEPARATION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	537 				23015				M/R FLAPPING SPRING SEPERATION. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400031	19950804	00031	SW 	1995	8	4	HEED95242 	1	19950711	G	2435	M832481012	PACKING 			BELL 	230 	230 	1182149	SW 										START/GEN	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	824 				23015				STARTER GEN GARLOCK SEAL CHANGE DUE TO LEAKING. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400032	19950804	00032	SW 	1995	8	4	HEED95245 	1	19950711	G	3150	222060096103	SWITCH 			BELL 	230 	230 	1182149	SW 										WARN PANEL	DEFECTIVE 	E			HEED	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			SW	03	236X	996 				23015				CAUTION PANEL LIGHT ILLUMINATED. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400033	19950804	00033	SW 	1995	8	4	HEED95246 	1	19950711	G	5320	222020578106	PANEL ASSY 			BELL 	230 	230 	1182149	SW 										FUSELAGE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1009 				23015				PANEL CRACKED. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995080400034	19950804	00034	SW 	1995	8	4	HEED95249 	1	19950711	G	7600	222360703101	SOLENOID 			BELL 	230 	230 	1182149	SW 										NR 1 ENG	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	678 				23015				SOLENOID INOPERATIVE ON #1 ENGINE FLIGHT IDLE. ORDERED NEW UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995050500294	19950505	00294	SW 	1995	5	5	HEED9525 	1	19950421	G	6410	222016001111	BLADE 			BELL 	230 	230 	1182149	SW 										T/R BLADE	LINK FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	385 				23015				PITCH LINK FAILED. SN A513 & A517						1	G	7	2 	3U			NC	H9SW 					 
1995080400035	19950804	00035		1995	8	4	HEED95253 	4	19950712	G	3420	1113034	INDICATOR 			SKRSKY	S76 	S76C 	8143008	NE 										GS NEEDLE	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	3 				760406				GS NEEDLE INDICATOR SHORTED OUT GOES TO TOP OF INDICATOR AND STAYS,. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995080400036	19950804	00036	NE 	1995	8	4	HEED95255 	2	19950712	G	7300	0164247110	VALVE ASSY 			SKRSKY	S76 	S76C 	8143008	NE 	TMECA 	ARRIEL	ARRIEL1S 	60030	NE 					BY PASS	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	67 				760405				ENGINE WILL NOT SHUTOFF WITH THROTTLE. NEW A/C PURCHASED FROM SIKORKSY						1	G	7	2 	3U	3	U	NC	H1NE 	E19EU				 
1995080400037	19950804	00037	SW 	1995	8	4	HEED95258 	1	19950712	G	5320	230020810101	TRIM PANEL 			BELL 	230 	230 	1182149	SW 										FUSELAGE	STAINED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	975 				23015				TRIM PANEL STAINED FROM LEAKS IN TRANSMISSION PAN. NEW A/C PURCHASED FROM SIKORKSY						1	G	7	2 	3U			NC	H9SW 					 
1995050500295	19950505	00295	SW 	1995	5	5	HEED9526 	1	19950421	G	6420	222012701119	HUB ASSY 			BELL 	230 	230 	1182149	SW 										T/R	LINK FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	385 				23015				PITCH CHANGE LINK FAILED						1	G	7	2 	3U			NC	H9SW 					 
1995080400038	19950804	00038	SW 	1995	8	4	HEED95260 	1	19950712	G	5320	222020573104	TRIM PANEL 			BELL 	230 	230 	1182149	SW 										FUSELAGE	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	979 				23015				PANEL UPPER HALF CORNER BROKEN OFF, CATCHES ON AIRFRAME. ORDER REPLACEMENT PART						1	G	7	2 	3U			NC	H9SW 					 
1995080400039	19950804	00039	SW 	1995	8	4	HEED95263 	1	19950712	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										SEARCH LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	132 				23015				SEARCH LIGHT INOPERATIVE ORDER REPLACEMENT PART						1	G	7	2 	3U			NC	H9SW 					 
1995080400040	19950804	00040	SW 	1995	8	4	HEED95267 	1	19950712	G	5320	MS21059L3	NUT PLATE 			BELL 	230 	230 	1182149	SW 										BELLY	STRIPPED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	861 				23015				NUT PLATE STRIPED OUT IN BELLY PANELS. ORDER REPLACEMENT PART						1	G	7	2 	3U			NC	H9SW 					 
1995050500296	19950505	00296	SW 	1995	5	5	HEED9527 	1	19950421	G	6720	222012774109	HORN ASSEMBLY 			BELL 	230 	230 	1182149	SW 										T/R PITCH	LINK FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	385 				23015				PART OF T/R ASSY PITCH CHANGE LINK FAILED.						1	G	7	2 	3U			NC	H9SW 					 
1995080400041	19950804	00041	NE 	1995	8	4	HEED95273 	1	19950712	G	2432	29490001	BATTERY 			SKRSKY	S76 	S76C 	8143008	NE 										DC SYS	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	88 				760406				BATTERY HAD TEMP HOT LIGHT INSPECTION AND CHECKED. BATTERY HAS SEVERAL WEAK CELLS AND WILL NOT GO THROUGH A MAINTENANCE	 INSPECTION CYCLE WITH A CHARGEER ANALIZER UNIT. ORDER REPLACEMENT PART					1	G	7	2 	3U			NC	H1NE 					 
1995080400042	19950804	00042	NE 	1995	8	4	HEED95275 	1	19950712	G	6210	7615009100053	BLADE 			SKRSKY	S76 	S76C 	8143008	NE 										M/R	SEPARATION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	7 				760406				SKIN SEPERATION ON M/R BLADE TOP ARE AT ALL SIKORSKY TOOLING HOLES STATION 72.06, 121.50, AND 186.50. ORDER REPLACEMENT 	PART					1	G	7	2 	3U			NC	H1NE 					 
1995080400043	19950804	00043		1995	8	4	HEED95276 	4	19950712	G	2210	7660000113103	GYRO 			SKRSKY	S76 	S76A 	8143006	NE 										AUTO PILOT	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	15460	5 				760223				AUTO PILOT KICKS IN PITCH AND ROLL CHANNELS ORDER REPLACEMENT PART						1	G	7	2 	3U				H1NE 					 
1995080400044	19950804	00044		1995	8	4	HEED95277 	4	19950712	G	2220	7040002200108	ACTUATOR 			SKRSKY	S76 	S76C 	8143008	NE 										PBA LINEAR	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	205 				760405				ACTUATOR INOPERATIVE ORDER REPLACEMENT PART						1	G	7	2 	3U			NC	H1NE 					 
1995080400045	19950804	00045	NE 	1995	8	4	HEED95278 	1	19950712	G	6220	7610608003042	PISTON ROD 			SKRSKY	S76 	S76A 	8143006	NE 										M/R	EXCESS WEAR 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	15460	124 				760223				EXCESSIVE WEAR IN THE CYLINDER HEAD SEAL RIDE AREA. NOTE: TT: UNK TTSI: 124.20 REPLACE PART WITH REWORKED , TSO:-0- PAR	T					1	G	7	2 	3U				H1NE 					 
1995080400046	19950804	00046	NE 	1995	8	4	HEED95279 	1	19950712	G	7714	54487129110	INDICATOR 			SKRSKY	S76 	S76C 	8143008	NE 										ENG N1	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	174 				760405				SECTIONS OF LED LITES INOPERATIVE DURING ALL SETTINGS REPLACE UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995080400047	19950804	00047	NE 	1995	8	4	HEED95281 	1	19950712	G	7160	7630207028059	SCREEN 			SKRSKY	S76 	S76A 	8143006	NE 										INTAKE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	15460					760223				CRACKED SCREEN REPLACE UNIT						1	G	7	2 	3U				H1NE 					 
1995080400048	19950804	00048		1995	8	4	HEED95283 	4	19950712	G	2312	064102300	TRANSCIEVER 			SKRSKY	S76 	S76C 	8143008	NE 										COCKPIT VHF	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H					760406				TRANSCEIVER HAS NO OUTPUT. WILL NOT TURN ON. REPLACE UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995080400049	19950804	00049	NE 	1995	8	4	HEED95284 	1	19950712	G	2910	951952	SHUTTLE VALVE 			SKRSKY	S76 	S76C 	8143008	NE 										HYD	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	276X	213 				760405				SHUTTLE VALVE LEAKING REPLACED WITH NEW STYLE P/N (98-71-2) AS PER CSL 76-A0-95-005						1	G	7	2 	3U			NC	H1NE 					 
1995080400050	19950804	00050	NE 	1995	8	4	HEED95285 	1	19950712	G	2910	951952	SHUTTLE VALVE 			SKRSKY	S76 	S76C 	8143008	NE 										HYD	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	89H	8 				760406				SHUTTLE VALVE LEAKING REPLACED WITH NEW STYLE P/N (98-71-2) AS PER CSL 76-A0-95-005						1	G	7	2 	3U			NC	H1NE 					 
1995080400051	19950804	00051	SW 	1995	8	4	HEED95287 	1	19950712	G	7810	230063301102	EXHAUST STACK 			BELL 	230 	230 	1182149	SW 										ENGINE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1133 				23015				EXH CRACKED AFT SIDE CENTER SEAM ABOVE MOUNTING FLANGE. REPLACE UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995050500297	19950505	00297	SW 	1995	5	5	HEED9529 	1	19950421	G	6710	206062721105	ACTUATOR 			BELL 	230 	230 	1182149	SW 										M/R	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	535 				23015				UNIT INOPERATIVE ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995080400052	19950804	00052	GL 	1995	8	4	HEED95299 	2	19950712	G	7321	22007762	VALVE 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30 	03013	GL 					FCU	STICKS 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1098 				23015				STICKS IN NORM POSITION CAN NOT SWITCH FCU TO ECONOMY MODE. REPLACE UNIT						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995050500298	19950505	00298	SW 	1995	5	5	HEED9530 	1	19950421	G	3340	68213002450	LENS 			BELL 	230 	230 	1182149	SW 										FLASH TUBE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	535 				23015				UNIT CRACKED . ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995080400053	19950804	00053	SW 	1995	8	4	HEED95300 	1	19950712	G	6710	206062721105	ACTUATOR 			BELL 	230 	230 	1182149	SW 										DROOP COMP	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	595 				23015				BEEP MOTOR WILL NOT EXTEND OR RETRACT. REPLACE UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995050500299	19950505	00299	SW 	1995	5	5	HEED9531 	1	19950421	G	7810	230063301102	STACK 			BELL 	230 	230 	1182149	SW 										EXHAUST	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	535 				23015				CRACKED STACK. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995050500300	19950505	00300	SW 	1995	5	5	HEED9532 	1	19950421	G	6200	222310504101	BEARING PAD 			BELL 	230 	230 	1182149	SW 										M/R	UNBONDED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	535 				23015				UNIT UNBONDING. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995050500301	19950505	00301	SW 	1995	5	5	HEED9533 	1	19950421	G	6200	222012711107	LINK ASSY 			BELL 	230 	230 	1182149	SW 										COUNTERWEIGHT	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	549 				23015				LINK ASSY WORN. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995092900455	19950929	00455	NE 	1995	9	29	HEED95336 	1	19950822	G	6230	78286SB5007101	UNIBALL BEARING 		761040850004	SKRSKY	S76 	S76C 	8143008	NE 										SWASHPLATE	CORRODED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	292 			A23800111	760405				UNIBALL BEARING CORROSION. REPLACE UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995092900456	19950929	00456		1995	9	29	HEED95337 	4	19950907	G	3442	MI5853013	INDICATOR 			BELL 	230 	230 	1182149	SW 										RADAR	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	942 				23015				RADAR INDICATOR FUZZY AND HARD TO READ.						1	G	7	2 	3U			NC	H9SW 					 
1995092900457	19950929	00457	NE 	1995	9	29	HEED95338 	1	19950907	G	6230	SB52001	BEARING 			SKRSKY	S76 	S76A 	8143006	NE 										SWASHPLATE	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	15460	811 				760223				BEARINGS EXCESSIVELY WORN S/NOS. 33441, 33463, 33465, 33533 REPACED WITH NEW BEARINGS S/NOS. 34834, 35664, 35637, 35765						1	G	7	2 	3U				H1NE 					 
1995092900458	19950929	00458	SW 	1995	9	29	HEED95339 	1	19950914	G	3340	MS25237387	BULB 			BELL 	230 	230 	1182149	SW 										LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1260 				23015				INOPERATIVE REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995092900459	19950929	00459		1995	9	29	HEED95340 	4	19950914	G	3434	MS33386839	LAMP 			BELL 	230 	230 	1182149	SW 										MARKER BEACON	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1260 				23015				MARKER BEACON SWITCH LIGHT INOPERATIVE REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995092900460	19950929	00460	SW 	1995	9	29	HEED95341 	1	19950914	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										SEARCH LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	115 				23015				SEARCH LIGHT INOPERATIVE REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995092900461	19950929	00461	SW 	1995	9	29	HEED95346 	1	19950914	G	2820	17451004	FILTER 			BELL 	230 	230 	1182149	SW 										FUEL SYS	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	182 				23015				FILTER BYPASS BUTTON EXTENDED. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995092900462	19950929	00462	SW 	1995	9	29	HEED95348 	1	19950914	G	3340	10648BH13	SWITCH 			BELL 	230 	230 	1182149	SW 										POSIT LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	891 				23015				INOPERATIVE REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995050500302	19950505	00302	SW 	1995	5	5	HEED9535 	1	19950421	G	6720	222001088109	TUBE ASSY 			BELL 	230 	230 	1182149	SW 										T/R CONTROL	CHAFED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	589 				23015				FOUND TUBE CHAFED AT AFT FRD ON 600 HOUR INSPECTION. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995092900463	19950929	00463	SW 	1995	9	29	HEED95350 	1	19950914	G	5610	222031293103	LATCH 			BELL 	230 	230 	1182149	SW 										CP WINDOW	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1231 				23015				LATCH ON CO-PILOT WINDOW BROKEN. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995092900464	19950929	00464	SW 	1995	9	29	HEED95351 	1	19950914	G	2435	M832481113	PACKING 			BELL 	230 	230 	1182149	SW 										START/GEN	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	1212 				23015				LEAKING STARTER GENERATOR. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995102700458	19951027	00458	NE 	1995	10	27	HEED95353 	1	19950922	G	7400	9550147560	START ELECTRODE 			SKRSKY	S76 	S76C 	8143008	NE 	TMECA 	ARRIEL	ARRIEL1S 	60030	NE 					ENGINE	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	167 				760406	15014			ENGINE WILL NOT START. REPLACE UNIT						1	G	7	2 	3U	3	U	NC	H1NE 	E19EU				 
1995102700459	19951027	00459	NE 	1995	10	27	HEED95354 	1	19950926	G	6210	7615009043050	TIP CAP 		761500910005	SKRSKY	S76 	S76C 	8143008	NE 										M/R BLADE	SEPARATION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	175 			A08602064	760406				SEPARATION ON OUTBOARD TRAILING EDGE. REPLACE UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995102700460	19951027	00460	NE 	1995	10	27	HEED95355 	1	19950926	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76C 	8143008	NE 										M/R BLADE	SEPARATION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	175 				760406				SEPARATION ON OUTBOARD TRAILING EDGE. REPLACE UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995102700461	19951027	00461	NE 	1995	10	27	HEED95356 	1	19950927	G	2612	7630607902103	DETECTOR 			SKRSKY	S76 	S76C 	8143008	NE 										ENGINE	DEFECTIVE 	E			HEED	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			SW	03	89H	176 				760406				DETECTOR FAULTY. CAUSES INTERMITTENT FIRE LIGHT. REPLACE UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995102700462	19951027	00462	NE 	1995	10	27	HEED95357 	2	19951002	G	7261	0292005250	SEAL 			SKRSKY	S76 	S76C 	8143008	NE 	TMECA 	ARRIEL	ARRIEL1S 	60030	NE 					LABYRINTH	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	89H	184 				760406				REAR LABYRINTH SEAL LEAKING HIGH OIL USEAGE. ENGINE SMOKING. REPLACE ENGINE ASSEMBLY						1	G	7	2 	3U	3	U	NC	H1NE 	E19EU				 
1995102700463	19951027	00463	NE 	1995	10	27	HEED95358 	2	19951003	G	7261	0292005250	SEAL 			SKRSKY	S76 	S76C 	8143008	NE 	TMECA 	ARRIEL	ARRIEL1S 	60030	NE 					MODULE 5	LEAK 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	89H	2999 				760406				ENGINE HAD BAD OIL LEAK AT MODULE 5 AFTER SEAL REPLACEMENT ON VIBRATION CHECK AT REAR BEARING HAD HIGH VIBRATION OF 35 	MM AND GOT ENGINE CHIPLITES, FOUND METAL ON MODULE 5 PLUG AND ON OTHER CHIP PLUGS AND IN FILTER. NONE					1	G	7	2 	3U	3	U	NC	H1NE 	E19EU				 
1995102700464	19951027	00464	NE 	1995	10	27	HEED95359 	1	19951005	G	7921	7630807901106	COOLER 			SKRSKY	S76 	S76C 	8143008	NE 										ENG OIL	METAL CONTAM 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	198 				760406				OIL COOLER METAL CONTAIMINATION. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE 					 
1995102700465	19951027	00465	NE 	1995	10	27	HEED95360 	1	19951009	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76C 	8143008	NE 										M/R	SEOARATION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	383 				760405				TRAILING EDGE SEPERATION. REPLACE UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995102700466	19951027	00466		1995	10	27	HEED95361 	2	19951010	G	7261	0292105180	OIL PUMP 			SKRSKY	S76 	S76C 	8143008	NE 										ENG OIL	DEFECTIVE 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	276X	390 				760405				LOW OIL PRESSURE AT MODULE 5 TEST POINT, ALSO OIL LEAKS FROM OIL TANK TO ENGINE GEARBOX. REPLACE UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995102700467	19951027	00467	SW 	1995	10	27	HEED95362 	1	19951010	G	5210	222325017101	AIR VALVE ASSY 			BELL 	230 	230 	1182149	SW 										LT AFT DOOR	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1301 				23015				L/H AFT DOOR AIR VALVE BROKEN. REPLACE UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995102700468	19951027	00468	SW 	1995	10	27	HEED95365 	1	19951010	G	6230	222010400127	SWASHPLATE 			BELL 	230 	230 	1182149	SW 										SLIDER	BUSHING UNBONDED	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1315 				23015				SLIDER BUSHING UNBONDED. REPLACE UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995102700469	19951027	00469	SW 	1995	10	27	HEED95366 	1	19951010	G	6330	230030535103	ROD END 			BELL 	230 	230 	1182149	SW 										ISO MOUNT	BEARING WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1231 				23015				BEARING WORN ON ISOLATION MOUNT. REPLACE UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995102700470	19951027	00470	SW 	1995	10	27	HEED95367 	1	19951010	G	6730	222382001105	ACTUATOR ASSY 			BELL 	230 	230 	1182149	SW 										M/R	BEARING WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1315 				23015				UPPER BEARING WORN. REPLACE UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995112400081	19951124	00081	NE 	1995	11	24	HEED95369 	1	19951012	G	6320	7635109002051	UPPER HOUSING 		763510960004	SKRSKY	S76 	S76C 	8143008	NE 										M/R GR BOX	CORRODED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	420 			A23100115	760405				WHILE CHANGING OIL COOLER DRIVE QUILL SEAL , FOUND CORROSION ON QUILL MOUNT PAD , TREATED AND APPLIED MASTING UNTIL PERM	ANENT REPAIR CAN BE MADE.					1	G	7	2 	3U			NC	H1NE 					 
1995050500303	19950505	00303	SW 	1995	5	5	HEED9537 	1	19950421	G	2121	222066605101	TUBE ASSY 			BELL 	230 	230 	1182149	SW 										VENT	DAMAGED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	589 				23015				TUBE SMASHED. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995112400082	19951124	00082		1995	11	24	HEED95370 	4	19951012	G	3424	7690001808103	RATE GYRO 			SKRSKY	S76 	S76C 	8143008	NE 										COCKPIT	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	394 				760405				RATE GYRO INOPERATIVE, REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE 					 
1995112400083	19951124	00083	NE 	1995	11	24	HEED95371 	1	19951012	G	2435	23081043	STARTER 			SKRSKY	S76 	S76C 	8143008	NE 										START/GEN	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	401 				760405				STARTER WON'T ENERGIZE, REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE 					 
1995112400084	19951124	00084	NE 	1995	11	24	HEED95373 	1	19951103	G	7160	7630207028059	INTAKE SCREEN 			SKRSKY	S76 	S76C 	8143008	NE 										ENG INTAKE	MESH BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	254 				760406				INTAKE SCREEN WIRE MESH BROKEN .REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900253	19951229	00253	NE 	1995	12	29	HEED95374 	1	19951103	G	2460	A1077W	RELAY 			SKRSKY	S76 	S76C 	8143008	NE 										BUS TIE	DEFECTIVE 	E			HEED	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			SW	03	89H	198 				760406				BUS TIE LIGHT STAYS ON AT ALL TIMES REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995050500304	19950505	00304	SW 	1995	5	5	HEED9538 	1	19950421	G	5270	1SX48T	SWITCH 			BELL 	230 	230 	1182149	SW 										DOOR	DEFECTIVE 	E			HEED	K				NONE 				P			NO WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	236X	589 				23015				DOOR LOCK LIGHT WILL NOT COME ON WHEN DOOR IS OPEN. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995112400085	19951124	00085	SW 	1995	11	24	HEED95382 	1	19951103	G	5610	222031291105	HINGE HALF 			BELL 	230 	230 	1182149	SW 										COPILOT WINDOW	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1315 				23015				CO-PILOT VENT WINDOW LATCH AND HINGE BROKEN REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995112400086	19951124	00086	SW 	1995	11	24	HEED95383 	1	19951103	G	5610	222031291107	HINGE HALF 			BELL 	230 	230 	1182149	SW 										COPILOT WINDOW	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1315 				23015				CO-PILOT VENT WINDOW LATCH AND HINGE BROKEN REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995112400087	19951124	00087	SW 	1995	11	24	HEED95384 	1	19951103	G	5610	222031293103	LATCH 			BELL 	230 	230 	1182149	SW 										COPILOT VENT	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1315 				23015				CO-PILOT VENT WINDOW LATCH AND HINGE BROKEN REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995112400088	19951124	00088	SW 	1995	11	24	HEED95385 	1	19951103	G	6320	222031591101	GASKET 			BELL 	230 	230 	1182149	SW 										XMSN DRAIN PAN	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	1315 				23015				TRANSMISSION DRAIN PAN LEAKING. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995112400089	19951124	00089	SW 	1995	11	24	HEED95387 	1	19951103	G	6720	222312702101	LINK 			BELL 	230 	230 	1182149	SW 										T/R PITCH	BEARING WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	126 				23015				BEARING WORN TO EXXON LIMITS .REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995112400090	19951124	00090	SW 	1995	11	24	HEED95389 	1	19951103	G	2931	222375016101	INDICATOR 			BELL 	230 	230 	1182149	SW 										HYD IND	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1333 				23015				HYD PRESSURE WENT TO ZERO, ON NEXT START HYD PRESSURE FLUCTUATE FROM 0-2000 PSI. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995050500305	19950505	00305	SW 	1995	5	5	HEED9539 	1	19950421	G	5210	222031293103	LATCH 			BELL 	230 	230 	1182149	SW 										DOOR	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	589 				23015				LATCH UNIT BROKEN. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995122900254	19951229	00254	SW 	1995	12	29	HEED95390 	1	19951103	G	5330	206033100285	PANEL ASSY 			BELL 	206 	206L3 	1182108	SW 										AFT TUB	SEPARATION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	8594X	3907 				51531				AIRCRAFT HAS SEPERATION ON A BELL APPROVED AIRFRAME AFT TUB AREA SEPARATION ON A ENGINEERING MOD OR MFG. REPAIR TO AFT 	CABIN TUB FLOOR. MADE REPAIR TO FORWARD LOWER SHELL PER BELL HELICOPTER STATEMENT OF COMPLIANCE FORM AE-100-1 S/N A2242 	DATED, OCTOBER 17, 1995.				1	G	7	1 	3U				H2SW 					 
1995122900255	19951229	00255	NE 	1995	12	29	HEED95391 	1	19951108	G	7160	7630207028059	INTAKE SCREEN 			SKRSKY	S76 	S76C 	8143008	NE 										ENG INTAKE	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	276 				760406				INTAKE SCREEN BROKEN. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900256	19951229	00256	NE 	1995	12	29	HEED95392 	1	19951114	G	2840	23356	SWITCH 			SKRSKY	S76 	S76C 	8143008	NE 										FUEL LOW PRESS	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476X	12 				760436				PRESSURE SWITCH CANNON PLUG SECTION BROKEN. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900257	19951229	00257	NE 	1995	12	29	HEED95393 	1	19951114	G	6322	950156790	BLOWER 			SKRSKY	S76 	S76C 	8143008	NE 										OIL COOLER	OIL LEAKS 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	276X	489 				760405				OIL LEAKS AT IMPELLER SHAFT. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900258	19951229	00258	NE 	1995	12	29	HEED95394 	1	19951117	G	7160	7630207028059	INTAKE SCREEN 			SKRSKY	S76 	S76C 	8143008	NE 										ENG INTAKE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	423 				760405				INTAKE SCREEN CRACKED. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900259	19951229	00259	NE 	1995	12	29	HEED95395 	1	19951117	G	6220	7610608000050	DAMPER 			SKRSKY	S76 	S76C 	8143008	NE 										M/R	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	89H	290 				760406				DAMPER LEAKING. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900260	19951229	00260	NE 	1995	12	29	HEED95396 	1	19951120	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76C 	8143008	NE 										M/R	SEPARATED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	502 				760405				TRAILING EDGE SEPERATED. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900261	19951229	00261	NE 	1995	12	29	HEED95397 	1	19951120	G	6210	7615009043050	TIP CAP 			SKRSKY	S76 	S76C 	8143008	NE 										M/R	SEPARATED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	502 				760405				TRAILING EDGE SEPERATED REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900262	19951229	00262	NE 	1995	12	29	HEED95398 	1	19951121	G	2612	7630607902103	DETECTOR 			SKRSKY	S76 	S76C 	8143008	NE 										ENG	DEFECTIVE 	E			HEED	K				NONE 				L			NO TEST 			IN	INSP/MAINT 	1			SW	03	276X	41 				760405				FLAME DETECTOR WOULD NOT TEST, THIS DETECTOR ORIGINALLY INSTALLED IN N476X. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1995122900263	19951229	00263	NE 	1995	12	29	HEED95399 	1	19951121	G	7400	9550147560	SOLENOID 			SKRSKY	S76 	S76C 	8143008	NE 	TMECA 	ARRIEL	ARRIEL1S1 	60030	NE 					ENG IGNITION	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	18 				760405	15094			ENGINE NOT STARTING. REPLACED UNIT						1	G	7	2 	3U	3	U	NC	H1NE 	E19EU				 
1995050500306	19950505	00306	SW 	1995	5	5	HEED9540 	1	19950421	G	5210	222325017101	AIR VALVE ASSY 			BELL 	230 	230 	1182149	SW 										DOOR	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	577 				23015				HALF OF AIR VALVE ASSY BROKE OFF. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995122900264	19951229	00264	NE 	1995	12	29	HEED95400 	1	19951121	G	7170	0174078010	DRAIN VALVE 			SKRSKY	S76 	S76C 	8143008	NE 	TMECA 	ARRIEL	ARRIEL1S1 	60030	NE 					ENG START	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	18 				760405	15094			ENGINE NOT STARTING. REPLACED START DRAIN VALVE UNIT.						1	G	7	2 	3U	3	U	NC	H1NE 	E19EU				 
1995122900265	19951229	00265	NE 	1995	12	29	HEED95401 	1	19951121	G	2840	23356	SWITCH 			SKRSKY	S76 	S76C 	8143008	NE 										FUEL LOW PRESS	STICKING 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	504 				760405				SWITCH STICKING. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500291	19960105	00291		1996	1	5	HEED95402 	4	19951121	G	3421	1113034	INDICATOR 			SKRSKY	S76 	S76C 	8143008	NE 										COCKPIT ATTITUDE	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476X					760436				PITCH INDICATION WILL NOT WORK .REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500292	19960105	00292		1996	1	5	HEED95403 	4	19951121	G	2312	06200140200	TRANSCEIVER 		KFM985 	SKRSKY	S76 	S76C 	8143008	NE 										COCKPIT	WEAK 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476X	22 				760436				TRANSCEIVER WEAK. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500293	19960105	00293		1996	1	5	HEED95404 	4	19951127	G	3425	1113025	INDICATOR 			SKRSKY	S76 	S76C 	8143008	NE 										COCKPIT HSI	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476X					760436				INDICATOR WON'T TURN. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500294	19960105	00294	NE 	1996	1	5	HEED95405 	1	19951127	G	7160	7630207028059	INTAKE SCREEN 			SKRSKY	S76 	S76C 	8143008	NE 										ENG INLET	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	24 				760405				FOUND INLET SCREEN CRACKED IN CENTER AREA WHICH CONTRIBUTED TO ENGINE FOD ON ENGINE S/N: 15094. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500295	19960105	00295	NE 	1996	1	5	HEED95406 	2	19951127	G	7230	0292015310	ENGINE ASSY 			SKRSKY	S76 	S76C 	8143008	NE 	TMECA 	ARRIEL	ARRIEL1S 	60030	NE 					COMPRESSOR	FOD 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	3020 				760405				COMPRESSOR FOD. REPLACED UNIT						1	G	7	2 	3U	3	U	NC	H1NE 	E19EU				 
1996010500296	19960105	00296	SW 	1996	1	5	HEED95407 	1	19951128	G	7810	230061803101	EJECTOR 			BELL 	230 	230 	1182149	SW 										EXHAUST	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1435 				23015				EXHAUST EJECTOR HAS CRACK ABOUT 1" LONG. SENT TO LOCAL PHI BASE TO HAVE COWLING WELDED UP IN CRACK AREA.						1	G	7	2 	3U			NC	H9SW 					 
1996010500297	19960105	00297	NE 	1996	1	5	HEED95408 	1	19951130	G	6230	SB52001	BEARING 			SKRSKY	S76 	S76C 	8143008	NE 										SCISSORS	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	327 				760405				WORN BEARINGS S/NOS: 4483, 4754, 4749, 4686 REPLACED UNIT WITH S/NOS: 37674, 37540, 37624, 37581						1	G	7	2 	3U			NC	H1NE 					 
1996010500298	19960105	00298	NE 	1996	1	5	HEED95410 	1	19951201	G	7160	7630207028059	SCREEN 			SKRSKY	S76 	S76C 	8143008	NE 										INTAKE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	278X	14 				760440				FOUND ON NEW AIRCRASFT AT ARRIVAL A 7 1/2" CRACK INSCREEN WITH 2 SMALL PIECES OF WIRE ABOUT 1/2" MISSING FROM SCREEN 	IN 2 PLACES (NOTE) SCREEN MFG FEBURARY 3, 1995. REPLACED UNIT					1	G	7	2 	3U			NC	H1NE 					 
1996010500299	19960105	00299	NE 	1996	1	5	HEED95411 	1	19951201	G	7160	7630207028059	SCREEN 			SKRSKY	S76 	S76C 	8143008	NE 										INTAKE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476X	39 				760436				CRACKED SCREEN . REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500300	19960105	00300	NE 	1996	1	5	HEED95412 	1	19951204	G	7160	7630207028060	SCREEN 			SKRSKY	S76 	S76A 	8143006	NE 										INTAKE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	15460					760223				CRACKED SCREEN . REPLACED UNIT						1	G	7	2 	3U				H1NE 					 
1996010500301	19960105	00301	NE 	1996	1	5	HEED95413 	1	19951208	G	7160	7630207028060	SCREEN 			SKRSKY	S76 	S76C 	8143008	NE 										INTAKE	BROKEN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	476X	56 				760436				BROKEN WIRES . REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500302	19960105	00302	NE 	1996	1	5	HEED95414 	1	19951208	G	3610	7650007903102	VALVE 			SKRSKY	S76 	S76C 	8143008	NE 										BLEED SOV	STICKS 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X					760405				VALVE STICKS OPEN . REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500303	19960105	00303		1996	1	5	HEED95415 	4	19951208	G	2350	M1050RDAT	AUDIO AMP 			SKRSKY	S76 	S76C 	8143008	NE 										COCKPIT	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H					760406				AUDIO AMP INTERMITTANT. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500304	19960105	00304	GL 	1996	1	5	HEED95417 	2	19951213	G	7210	0292108170	SEAL RING 			SKRSKY	S76 	S76C 	8143008	NE 	ALLSN 	250C 	250C30S 	03013	GL 					NR 1 ENG	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	476X	14 				760436	15529			FRONT SEAL ON POWER SHAFT LEAKING ON #1 ENGINE . REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE 	E1GL				 
1996010500305	19960105	00305	NE 	1996	1	5	HEED95418 	1	19951213	G	5320	7630307013044	CATCH ASSEMBLY 			SKRSKY	S76 	S76C 	8143008	NE 										AFT COWL	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	473 				760405				AFT COWL CATCH CRACKED . REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE 					 
1996010500306	19960105	00306	NE 	1996	1	5	HEED95420 	1	19951213	G	3244	504T412	TIRE 			SKRSKY	S76 	S76C 	8143008	NE 										NOSE GEAR	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	307 				760406				TIRE HAD A KNOT IN MARKED AREA THAT ROSE ABOUT 1/2" ABOVE THE NORMAL SURFACE OF TIRE. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE 					 
1996010500307	19960105	00307	NE 	1996	1	5	HEED95421 	1	19951213	G	3244	504T412	TIRE 			SKRSKY	S76 	S76C 	8143008	NE 										NLG	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	89H	330 				760406				VERY SMALL PIN HOLE IN SIDE WALL NEAR BEAD. TIRE ALSO OUT OF ROUND REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE 					 
1996010500308	19960105	00308	NE 	1996	1	5	HEED95422 	1	19951213	G	6322	TBL25	BLOWER 			SKRSKY	S76 	S76C 	8143008	NE 										FAN SYS	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	383 				760405				BLOWER INOPERATIVE . REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE 					 
1996010500309	19960105	00309	NE 	1996	1	5	HEED95423 	1	19951213	G	3246	5007553	NOSE WHEEL 			SKRSKY	S76 	S76C 	8143008	NE 										HUB	CORROSION 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	473 				760405				CORROSION IN HUB CENTER AREA. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE 					 
1996010500310	19960105	00310	NE 	1996	1	5	HEED95424 	1	19951213	G	6320	7635109083103	FILTER 			SKRSKY	S76 	S76C 	8143008	NE 										XMSN	CHIP LIGHT 	E			HEED	K				NONE 				J			WARNING INDICATION 			IN	INSP/MAINT 	1			SW	03	278X	14 				760440				TRANSMISSION HAD TWO CHIP LIGHTS ON FLIGHT FROM SIKORSKY, FILTER REMOVED AND INSPECTED FOR METAL ALSO USED O'RING P/N M8	3248/1-238 AND 12 QTS OF DEXTRON II OIL. REPLACED FILTER O'RING AND OIL AS INSTRUCTED BY SIKORSKY					1	G	7	2 	3U			NC	H1NE 					 
1996010500311	19960105	00311	NE 	1996	1	5	HEED95425 	1	19951213	G	6320	7635109082105	CHIP DETECTOR 			SKRSKY	S76 	S76C 	8143008	NE 										XMSN	DEFECTIVE 	E			HEED	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			SW	03	278X	14 				760440				TRANSMISSION CHIP LIGHT CAME ON TWICE FOUND DETECTOR BAD HAD ONE OF TEFLON RINGS CRACKED (NOTE) ALSO USED ONE NEW O'RING	 P/N M83248/1-131. REPLACED CHIP DETECTOR AND INSTALLED NEW O'RING					1	G	7	2 	3U			NC	H1NE 					 
1996010500312	19960105	00312	NE 	1996	1	5	HEED95426 	1	19951213	G	7910	5F204000	OIL CAP 			SKRSKY	S76 	S76C 	8143008	NE 										ENG	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	531 				760405				R & R CAP. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500313	19960105	00313	NE 	1996	1	5	HEED95427 	1	19951213	G	7110	7630307013043	CATCH ASSEMBLY 			SKRSKY	S76 	S76C 	8143008	NE 										ENG COWL	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	150 				760405				ENGINE COWL CATCH CRACKED. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500314	19960105	00314	NE 	1996	1	5	HEED95429 	1	19951213	G	3610	7650007903102	VALVE 			SKRSKY	S76 	S76C 	8143008	NE 										BLEED SOV	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	276X	560 				760405				BLEED SOV LEAKING. REPLACED UNIT						1	G	7	2 	3U			NC	H1NE 					 
1996010500315	19960105	00315	SW 	1996	1	5	HEED95430 	1	19951213	G	6520	222340063101	SEAL 			BELL 	230 	230 	1182149	SW 										T/R XMSN	LEAKING 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1437 				23015				T/R OUTPUT SEAL ON TRANSMISSION LEAKING. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500316	19960105	00316	SW 	1996	1	5	HEED95431 	1	19951213	G	6520	222040239001	TABLOC-NUT 			BELL 	230 	230 	1182149	SW 										T/R TRANSMISSION	SEAL LEAK 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	1437 				23015				T/R OUTPUT SEAL ON TRANSMISSION LEAKING. REPLACED TAB LOC UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500317	19960105	00317	SW 	1996	1	5	HEED95432 	1	19951213	G	6520	M832481249	PACKING 			BELL 	230 	230 	1182149	SW 										T/R XMSN	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	1437 				23015				T/R OUTPUT SEAL ON TRANSMISSION LEAKING. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500318	19960105	00318	SW 	1996	1	5	HEED95433 	1	19951213	G	6520	MS29561112	PACKING 			BELL 	230 	230 	1182149	SW 										T/R XMSN	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	1437 				23015				T/R OUTPUT SEAL ON TRANSMISSION LEAKING. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500319	19960105	00319	SW 	1996	1	5	HEED95434 	1	19951213	G	6520	MS29561133	PACKING 			BELL 	230 	230 	1182149	SW 										T/R XMSN	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	1437 				23015				T/R OUTPUT SEAL ON TRANSMISSION LEAKING. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500320	19960105	00320	SW 	1996	1	5	HEED95435 	1	19951213	G	3340	900601	LIGHT 			BELL 	230 	230 	1182149	SW 										SEARCH	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1415 				23015				ON DAILY INSPECTION FOUND SEARCH LIGHT INOPERATIVE REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500321	19960105	00321	SW 	1996	1	5	HEED95436 	1	19951213	G	6210	222011118105	BUMPER 			BELL 	230 	230 	1182149	SW 										M/R GRIP	MISSING 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1412 				23015				BUMBER ON M/R GRIP MISSING REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500322	19960105	00322	SW 	1996	1	5	HEED95437 	1	19951213	G	2120	206072154103	PANEL 			BELL 	230 	230 	1182149	SW 										A/C VENT	MISSING 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1412 				23015				TRIM PANEL AROUND A/C VENT MISSING REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500323	19960105	00323	SW 	1996	1	5	HEED95441 	1	19951213	G	6321	5009209	BRAKE 			BELL 	230 	230 	1182149	SW 										ROTOR	PUCKS WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	747 				23015				ON ZONE INSP. FOUND ROTOR BRAKE PUCKS WORN. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500324	19960105	00324	SW 	1996	1	5	HEED95444 	1	19951213	G	6720	222312702101	LINK 			BELL 	230 	230 	1182149	SW 										T/R	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	62 				23015				T/R LINK DEFECTIVE. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500325	19960105	00325	SW 	1996	1	5	HEED95446 	1	19951213	G	6320	222040243001	TAB LOC-NUT 			BELL 	230 	230 	1182149	SW 										TRANSMISSION	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	983 				23015				#1 TRANSMISSION INPUT QUILL LEAKING REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500326	19960105	00326	SW 	1996	1	5	HEED95447 	1	19951213	G	6320	M832481032	PACKING 			BELL 	230 	230 	1182149	SW 										TRANSMISSION	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	983 				23015				#1 TRANSMISSION INPUT QUILL LEAKING REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500327	19960105	00327	SW 	1996	1	5	HEED95448 	1	19951213	G	6320	MS29561247	PACKING 			BELL 	230 	230 	1182149	SW 										TRANSMISSION	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	983 				23015				#1 TRANSMISSION INPUT QUILL LEAKING REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500328	19960105	00328	SW 	1996	1	5	HEED95449 	1	19951213	G	6320	7805315	MATING RING 			BELL 	230 	230 	1182149	SW 										TRANSMISSION	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	983 				23015				#1 TRANSMISSION INPUT QUILL LEAKING REPLACED MATING RING UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995050500307	19950505	00307	SW 	1995	5	5	HEED9545 	1	19950421	G	3320	MS25237387	BULB 			BELL 	230 	230 	1182149	SW 										CABIN	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	565 				23015				NO-SMOKING SIGN INOPERATIVE. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1996010500329	19960105	00329	SW 	1996	1	5	HEED95450 	1	19951213	G	6320	780531	SEAL 			BELL 	230 	230 	1182149	SW 										TRANSMISSION	LEAKING 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	983 				23015				#1 TRANSMISSION INPUT QUILL LEAKING REPLACED SEAL UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500330	19960105	00330	SW 	1996	1	5	HEED95452 	1	19951213	G	5610	222031291106	HINGE HALF 			BELL 	230 	230 	1182149	SW 										WINDOW	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1437 				23015				HINGE HALF CRACKED. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500331	19960105	00331	SW 	1996	1	5	HEED95453 	1	19951213	G	5330	222020563121	PANEL 			BELL 	230 	230 	1182149	SW 										FUSELAGE	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	632 				23015				CRACKED PANEL. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1996010500332	19960105	00332	SW 	1996	1	5	HEED95454 	1	19951213	G	3240	40004244	BRAKE ASSY 			BELL 	230 	230 	1182149	SW 										PISTONS	PUCKS LOOSE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	1437 				23015				PUCKS LOOSE ON PISTONS. REPLACED UNIT						1	G	7	2 	3U			NC	H9SW 					 
1995050500308	19950505	00308	SW 	1995	5	5	HEED955 	1	19950420	G	5302	212030100121	TAILBOOM 			BELL 	412 	412 	1182202	SW 										SPLICE JOINT	CORRODED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	107X	9031 				33113				LONGERON CORRISON AT SPLICE JOINT. CAUSE BY MANUFACTURER'S LEAVING PEEL-PLY MATERIAL ON SPLICE JOINT. HAD TAILBOOM REPA	IR LOCALLY.					1	G	7	2 	4U				H4SW 					 
1995050500309	19950505	00309	SW 	1995	5	5	HEED9552 	1	19950421	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	616 				23015				LAMP BURNT. ORDERED NEW PART						1	G	7	2 	3U			NC	H9SW 					 
1995050500310	19950505	00310		1995	5	5	HEED9553 	4	19950421	G	3442	MI5853001	RT UNIT 			BELL 	230 	230 	1182149	SW 										RADAR	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	452 				23015				NO POWER OUTPUT, SCOPE HAS A BLANK SCREEN.						1	G	7	2 	3U			NC	H9SW 					 
1995050500311	19950505	00311		1995	5	5	HEED9555 	4	19950421	G	2340	PM212302	SWITCH 			BELL 	230 	230 	1182149	SW 										PILOT ICS	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	651 				23015				DEFECTIVE PILOT TRIGGER SWITCH. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500312	19950505	00312	SW 	1995	5	5	HEED9556 	1	19950421	G	6720	222312702101	LINK 			BELL 	230 	230 	1182149	SW 										T/R	WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	143 				23015				T/R LINK WORN ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500313	19950505	00313	SW 	1995	5	5	HEED9557 	1	19950421	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	510 				23015				BULB BLOWN. ORDER NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500314	19950505	00314	GL 	1995	5	5	HEED9558 	2	19950421	G	7320	222360703101	SOLENOID 			BELL 	230 	230 	1182149	SW 	ALLSN 	250C 	250C30G2 	03013	GL 					NR 1 ENG	INOPERATIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	678 				23015				NR 1 ENGINE FLIGHT IDLE SOLENOID INOPERATIVE.						1	G	7	2 	3U	3	U	NC	H9SW 	E1GL				 
1995050500315	19950505	00315	SW 	1995	5	5	HEED956 	1	19950420	G	6210	222015600111	BLADE 			BELL 	230 	230 	1182149	SW 										M/R	DAMAGED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	431 				23015				DAMAGED BLADE. ORDERED NEW BLADE						1	G	7	2 	3U			NC	H9SW 					 
1995050500316	19950505	00316	SW 	1995	5	5	HEED9563 	1	19950421	G	3340	4580	LAMP 			BELL 	230 	230 	1182149	SW 										SEARCH LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	709 				23015				SEARCH LIGHT BURNT OUT. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500317	19950505	00317	SW 	1995	5	5	HEED9565 	1	19950421	G	3340	10648BH13	SWITCH 			BELL 	230 	230 	1182149	SW 										POSIT LIGHT	FAILED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	891 				23015				POSITION LIGHTS STAY ON WHEN SWITCH IS TURNED OFF. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500318	19950505	00318	SW 	1995	5	5	HEED9566 	1	19950424	G	5330	222020573103	PANEL ASSY 			BELL 	230 	230 	1182149	SW 										FUSELAGE	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	205 				23015				UPPER AFT CORNER CATCHS ON AIRFRAME AND BREAKS OFF. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500319	19950505	00319	SW 	1995	5	5	HEED9567 	1	19950424	G	6520	M832481033	PACKING 		222042001007	BELL 	230 	230 	1182149	SW 										T/R GR BOX	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	902 			A446	23015				T/R GEARBOX INPUT SEAL LEAKING. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500320	19950505	00320		1995	5	5	HEED9568 	4	19950424	G	3120	M8005BATT	CLOCK 			BELL 	230 	230 	1182149	SW 										COCKPIT	DEFECTIVE 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	891 				23015				ONE SECOND ON CLOCK = THREE SECOND OF TIME. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500321	19950505	00321	SW 	1995	5	5	HEED9569 	1	19950424	G	6230	204040244001	SEAL 		222040002115	BELL 	230 	230 	1182149	SW 										MAST	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	921 			A196	23015				MAST SEAL LEAKING. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500322	19950505	00322	SW 	1995	5	5	HEED957 	1	19950420	G	6200	222010150001	SUPPORT 			BELL 	230 	230 	1182149	SW 										M/R	MISSING 	E			HEED	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	03	236X	431 				23015				MISSING FROM AIRCRAFT. ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500323	19950505	00323	SW 	1995	5	5	HEED9570 	1	19950424	G	6230	M832481253	PACKING 		222040002115	BELL 	230 	230 	1182149	SW 										MAST	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	921 			A196	23015				MAST SEAL LEAKING. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500324	19950505	00324	SW 	1995	5	5	HEED9571 	1	19950424	G	5330	222020561103	PANEL ASSY 			BELL 	230 	230 	1182149	SW 										FUSELAGE	CRACKED 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	921 				23015				CRACKED AND STAINED FROM OIL LEAKS. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500325	19950505	00325	SW 	1995	5	5	HEED9573 	1	19950424	G	6322	230365001101	FAN 			BELL 	230 	230 	1182149	SW 										OIL COOLER	DEFECTIVE 	E			HEED	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	03	236X	916 				23015				FAN HAS HIGH FREQ. VIBRATION. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500326	19950505	00326	SW 	1995	5	5	HEED9574 	1	19950424	G	6520	MS29561239	PACKING 		222042001007	BELL 	230 	230 	1182149	SW 										T/R GR BOX	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	902 			A446	23015				T/R GEARBOX INPUT SEAL LEAKING. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500327	19950505	00327	SW 	1995	5	5	HEED9575 	1	19950424	G	6520	222342401103	SEAL 		222042001007	BELL 	230 	230 	1182149	SW 										T/R GR BOX	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	902 			A446	23015				T/R GEARBOX INPUT SEAL LEAKING. ORDER NEW.						1	G	7	2 	3U			NC	H9SW 					 
1995050500328	19950505	00328	SW 	1995	5	5	HEED9579 	1	19950424	G	6700	222001736005	BELLCRANK ASSY 			BELL 	230 	230 	1182149	SW 										CONTROL	BEARING WORN 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	737 				23015				WORN BEARING. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500329	19950505	00329	SW 	1995	5	5	HEED958 	1	19950420	G	6220	222011111101	SHIM 			BELL 	230 	230 	1182149	SW 										FLAPPING	DAMAGED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	431 				23015				DAMAGED. ORDERED NEW PART.						1	G	7	2 	3U			NC	H9SW 					 
1995050500330	19950505	00330	SW 	1995	5	5	HEED9580 	1	19950424	G	5330	222020573103	PANEL ASSY 			BELL 	230 	230 	1182149	SW 										FUSELAGE	DAMAGED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	716 				23015				UPPER AFT CORNER BROKEN OFF. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500331	19950505	00331	SW 	1995	5	5	HEED9581 	1	19950424	G	7910	222065505136	TANK ASSY 			BELL 	230 	230 	1182149	SW 										ENG OIL	CRACKED 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	716 				23015				ENGINE OIL TANK CRACKED AND LEAKING. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500332	19950505	00332	SW 	1995	5	5	HEED9582 	1	19950424	G	7910	11014410A	SEAL 			BELL 	230 	230 	1182149	SW 										OIL TANK	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	747 				23015				ENGINE OIL TANK CRACKED AND LEAKING. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500333	19950505	00333	SW 	1995	5	5	HEED9583 	1	19950424	G	7910	11014412A	SEAL 			BELL 	230 	230 	1182149	SW 										OIL TANK	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	747 				23015				ENGINE OIL TANK CRACKED AND LEAKING. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500334	19950505	00334	SW 	1995	5	5	HEED9584 	1	19950424	G	7910	15804	GASKET 			BELL 	230 	230 	1182149	SW 										OIL TANK	LEAKING 	E			HEED	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	03	236X	747 				23015				ENGINE OIL TANK CRACKED AND LEAKING. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995050500335	19950505	00335	SW 	1995	5	5	HEED9592 	1	19950424	G	5610	222031125276	WINDOW 			BELL 	230 	230 	1182149	SW 										COCKPIT	CRACKED 	E			HEED	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	03	236X	798 				23015				WINDOW CRACKED. ORDERED NEW						1	G	7	2 	3U			NC	H9SW 					 
1995052600668	19950526	00668	EU 	1995	5	26	JGVR052201 	1	19950522	G	2910		LINE 			AMD 	FALC50	FALCON50MYST	2730106	EU 										NR 1 HYD SYST	DAMAGED 	B				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CE	09	350WB					102				THE NAS221-8 SCREWS WHICH ATTACH THE TOTAL TEMPERTURE PROBE COVER SUPPORT, INSTALLED BY SERVICE BULLETIN F50-0034, (P/N 	F50B910001200A2) TO COVER ASSEMBLY (P/N F50B252020611A1) GOUGED NR 1 HYDRAULIC SYSTEM RETURN LINE (P/N F50B751552). THE	 LINE WAS REPLACED WITH A NEW LINE AND THE SCREWS CHANGED TO A SHORTER LENGTH. ALSO, ANTI-CHAF WRAP WAS INSTALLED OVER 	THE NEW HYDRAULIC LINE.			2	L	7	3 	4F				A46EU 					 
1995052600669	19950526	00669	EU 	1995	5	26	JGVR052202 	1	19950522	G	2910		LINE 			AMD 	FALC50	FALCON50MYST	2730106	EU 										NR 1 HYD SYST	DAMAGED 	B				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			CE	09	50TG					117				THE NAS221-8 SCREWS WHICH ATTACH THE TOTAL TEMPERTURE PROBE COVER SUPPORT, INSTALLED BY SERVICE BULLETIN F50-0034, (P/N 	F50B910001200A2) TO COVER ASSEMBLY (P/N F50B252020611A1) GOUGED NR 1 HYDRAULIC SYSTEM RETURN LINE (P/N F50B751552). THE	 LINE WAS REPLACED WITH A NEW LINE AND THE SCREWS CHANGED TO A SHORTER LENGTH. ALSO, ANTI-CHAF WRAP WAS INSTALLED OVER 	THE NEW HYDRAULIC LINE.			2	L	7	3 	4F				A46EU 					 
1995060200213	19950602	00213	EU 	1995	6	2	JGVR052601 	1	19950526	G	5210	59047	CABLE 			AMD 	FALC10	FALCON10 	2730101	EU 										PAX DOOR	CHAFED 	B				K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	100CK		2730 			222				DURING A DETAILED INSPECTION OF THE COCKPIT AREA, FOUND THE FORWARD UPPER CABIN DOOR CABLE (P/N 59047) CHAFING ON THE WI	RE BUNDLE. THE BUNDLE RUNS TO THE CIRCUIT BREAKER PANEL WHICH IS LOCATED BEHIND THE PILOTS SEAT. THE WIRE BUNDLE CLAMP	S WERE REPOSITIONED AND THE TEFLON PROTECTIVE SLEEVES WERE RECLAMPED TO PROVIDE SUFFICIENT CLEARANCE.				2	L	7	2 	4F			 	A33EU 					 
1995061600265	19950616	00265	CE 	1995	6	16	JGVR061301 	1	19950613	G	5320		THRESHOLD 			CESSNA	500 	500CESSNA 	2076602	CE 										CABIN DOOR	CHAFED 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	501LH					0342				CABIN DOOR THRESHOLD CHAFED IN TWO LOCATIONS, APPROXIMATLY .009 AND .015 DEEP. CHAFING CAUSED BY CABIN DOOR SKIN WHICH 	WAS BENT SLIGHTLY INWARD AND THE DOOR BEING OUT OF ADJUSTMENT.					1	L	7	2 	4F				A22CE 					 
1995061600266	19950616	00266	CE 	1995	6	16	JGVR061302 	1	19950613	G	5210		SKIN 			CESSNA	500 	500CESSNA 	2076602	CE 										CABIN DOOR	BENT 	B			JGVR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			CE	09	501LH					0342				UPPER CABIN DOOR LINTEL CHAFED AT FORWARD CORNER APPROXEMNTALY .010 DEEP. CHAFING CAUSED BY BENT DOOR SKIN AND MISALINE	D DOOR.					1	L	7	2 	4F				A22CE 					 
1996011900171	19960119	00171	NE 	1996	1	19	JYER951214 	1	19951214	G	3211	S61806316114	FITTING 			SKRSKY	S61 	S61A 	814210C	NE 										RT AFT MLG	CRACKED 	B			JYER	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			NM	09	1048Y	12987				61161				RIGHT REAR FUSELAGE LANDING GEAR FITTING CRACKED AT AFT EAR OUT OF BOLT HOLE. INSIDE OF EAR HAD SOME FRETTING. SUBMITT	ER RECOMMENDS PERIODIC RETORQUE OF LANDING GEAR. (X)					2	G	7	2 	4U				H2EA 					 
1996011900172	19960119	00172	NE 	1996	1	19	JYER951221 	1	19951221	G	6320	S6135220173	RING GEAR TOOTH 			SKRSKY	S61 	S61A 	814210C	NE 										MAIN GEARBOX	BROKE 	B			JYER	A				UNSCHED LANDING 				J			WARNING INDICATION 			NR	NOT REPORTED 	1			NM	09	1048Y		785 		A14A2464580	61161				PILOTS OBSERVED CHIP LIGHT. LANDED IMMEDIATELY. CHIPS BEYOND LIMITS FOUND ON CHIP PLUG. LOWER HALF OF RING GEAR TOOTH	 BROKE OFF. CRACK APPEARS TO HAVE INITIATED AT HARD LINE ON TOOTH. MISSING 1.4 INCHES OF TOOTH WAS BROKEN IN ABOUT 20 	PIECES. COMPONENT NR S6135-20600-039. (X)				2	G	7	2 	4U				H2EA 					 
1995081100430	19950811	00430	NM 	1995	8	11	JZBR10654 	1	19950701	G	2820	025W652002501	JET PUMP 			ISRAEL	1125 	1125 		NM 										FUEL TANK	INLET BLOCKED 	B		A	JZBR	O				OTHER 				J			WARNING INDICATION 			CR	CRUISE 	1			EA	25	45MS					41				IN-FLIGHT, LEFT FUEL PRESSURE LIGHT CAME ON. UPON ACTUATING BOOST PUMP, LIGHT WENT OUT. IN TROUBLESHOOTING THE SYSTEM,	 FOUND THERE WAS NO MOTIVE FLOW TO THE LEFT ENGINE. REMOVED JET PUMP AND FOUND A PIECE OF PLASTIC, THE SAME SIZE AS THE	 MOTIVE FLOW INLET LINE, BLOCKING THE INLET OF THE JET PUMP. REMOVED PLASTIC, RESINSTALLED JET PUMP. SYSTEM FUNCTIONED	 NORMALLY. HAVE NO IDEA HOW PLASTIC PIECE GOT IN THERE AS THIS LINE FROM THE JET PUMP GOES DIRECT TO THE ENGINE DRIVEN 	FUEL PUMP. (X)		2	L	7	2 	4F			RT	A16NM 					 
1995091500709	19950915	00709	EU 	1995	9	15	JZBR10689 	1	19950901	G	2750		FLAP CONTROL 			BRAERO	DH125 	BAE125800A 	1500285	EU 										KEEL FRAME 18	INTERFERENCE 	B	L	A	JZBR	O				OTHER 				F			FLT CONT AFFECTED 			NR	NOT REPORTED 	1			EA	25	161MM					258061				INVESTIGATION FOR FLAPS STUCK AT 26 DEGREES, FOUND A BOLT INSTALLED IMPROPERLY. BOLT (P/N A102-1/2G) INSTALLATION IS CO	NDUCTED PER HS125800 SB 53-82-3566G, ITEM NR 18. IF BOLT IS INSTALLED WITH THREADS OUT, FLAP CONTROL INTERFERENCE CAN O	CCUR. PROPER INSTALLATION IS FOR BOLT HEAD TO THE OUTSIDE AND THREADS INSIDE. RECOMMENDATION - RAYTHEON SHOULD REISSUE	 THE SB TO HIGHLIGHT DETAIL 'L' FOR PROPER BOLT INSTALLATION. AN INSPECTION FOR PROPER CLEARANCE FROM SURROUNDING FLAP 	CONTROL LINKAGE AND A FULL FLAP OPERATIONAL CHECK SHOULD BE ADDED TO THE PROCEDURES FOR THIS ITEM.		2	L	7	2 	4F			RT	A3EU 					 
1995082500623	19950825	00623	EU 	1995	8	25	JZBR10758 	1	19950808	G	2822	2070C1T3	PUMP 			ISRAEL	1124 	1124 	4500102	EU 										FUEL BOOST	FAILED 	B			JZBR	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			EA	25	40MP				T1210	334				CREW REPORTED NR 2 MAIN BOOST PUMP (FUEL) SWITCHES TO ALTERNATE AFTER TAKEOFF. INSPECTED AND FOUND NR 2 BOOST PUMP BAD.	 ORDERED AND RECEIVED AN OVERHAULED BOOST PUMP. INSTALLED AND ACCOMPLISHED OPERATIONAL CHECK. UNIT OPERATION FOR 3 OR	 4 MINUTES AND FAILED. ORDERED ANOTHER PUMP AND INSTALLED. OPERATIONAL AND LEAK CHECKS ACCOMPLISHED WITH NO FURTHER DI	SCREPANCIES. ALL WORK ACCOMPLISHED IAW THE MANUFACTURER'S MM. AIRCRAFT RETURNED TO SERVICE. (X)			2	M	7	2 	4F				A2SW 					 
1995082500624	19950825	00624	SO 	1995	8	25	JZBR10764 	1	19950808	G	2820	1159H40200143	HOSE 			GULSTM	G1159 	G1159A 	3970109	SO 										BOOST PUMP	MISMFG 	B			JZBR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25	82A					342				WHILE ACCOMPLISHING A HOSE CHANGE REQUIRED BY GULFSTREAM'S MM, CHAPTER 5, AT 5 YEARS, FOUND A NEW HOSE WITH ONE END NOT 	SWAGED. THE HOSE WAS ORDERED NEW AND RECEIVED IN GOOD CONDITION. ALL APPEARED GOOD UNTIL A LEAK CHECK REVEALED THE SWA	GE WAS NOT APPLIED TO ONE END. GULFSTREAM SPARES WERE ADVISED AS WELL AS QUALITY CONTROL. RECEIVED A REPLACEMENT HOSE 	AND INSTALLED. ALL LEAK CHECKS WERE GOOD. ALL WORK ACCOMPLISHED IAW THE GULFSTREAM MM AND CMP. AIRCRAFT RETURNED TO S	ERVICE. (X)		2	L	7	2 	4F				A12EA 					 
1995082500625	19950825	00625	EU 	1995	8	25	JZBR10767 	1	19950808	G	3010	EL12600	LOGIC BOX 			AMD 	FALC50	FALCON900 	2700160	EU 										ANTI-ICE	MISREPAIRED 	B			JZBR	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			EA	25	59CF				137	098				DURING A POST-FLIGHT INSPECTION, A TEST OF THE ANTI-ICING LOGIC BOX WAS ACCOMPLISHED. A DISCREPANCY WAS DISCOVERED (ENG	INE 1 LO LCD INOP). ORDERED AND RECEIVED A SERVICEABLE LOGIC BOX FROM AN FAA APPROVED REPAIR FACILITY. DURING INSTALLA	TION ON THE AIRCRAFT, THE APPROPRIATE CANNON PLUGS WOULD NOT REACH THE RECEPTACLES ON THE LOGIC BOX. FURTHER, INSPECTIO	N REVEALED THE CANNON PLUG FACEPLATE WAS IMPROPERLY INSTALLED AT REPAIR. ORDERED ANOTHER REPLACEMENT BOX, INSTALLED AND	 TESTED. NO FURTHER DISCREPANCIES. ALL WORK ACCOMPLISHED IAW THE FALCON 900 MM. AIRCRAFT RETURNED TO SERVICE. (X)		2	L	7	3 	4F			RT	A46EU 					 
1995082500626	19950825	00626	WP 	1995	8	25	JZBR10817 	2	19950809	G	7250		ENGINE 			BRAERO	DH125 	HS125700A 	4230170	EU 	GARRTT	TFE731	TFE7313R 	01518	WP 					AFT TURBINE	FAILED 	B			JZBR	C	D			ABORTED TAKEOFF 	RETURN TO BLOCK 			J			WARNING INDICATION 			TO	TAKEOFF 	1			EA	25	746BC	6883 				NA0218	P80115C			WHILE SITTING AT THE END OF RUNWAY, AIRCRAFT WAS CLEAR FOR TAKEOFF. CREW ADVANCED THROTTLES. WHILE SPOOLING UP TO N1 F	OR TAKEOFF, THE LEFT ENGINE RELEASED A LOUD EXPLOSION. THROTTLES WERE RETARDED, TRIP WAS CANCELLED. THE AIRCRAFT TAXIE	D TO A MAINTENANCE FACILITY. INITIAL INSPECTION IDENTIFIED THE AFT TURBINE WHEEL MISSING SEVERAL SECTIONS OF BLADES. T	HE SHROUD WAS DAMAGED AND HAD SOME HOLES IN IT. A BORESCOPE OF THE COMBUSTION CHAMBER REVEALED METAL SPRAY. THE ENGINE	 IS BEING REMOVED FOR FURTHER INVESTIGATION AND REPAIR. 4,522 CSN. (X)		2	L	7	2 	4F	4	F		A3EU 	E6WE				 
1996020900032	19960209	00032	CE 	1996	2	9	JZBR11598 	1	19951209	G	3250	80017104	SERVO 			LEAR 	35 	35A 	5170602	CE 										NLG STEERING	SHAFT SHEARED 	B		A	JZBR	O				OTHER 				O			OTHER 			LD	LANDING 	1			EA	25	8LA				0549	124				UPON LANDING, PILOT COMPLAINED OF NOSE WHEEL SHIMMY AND LOSS OF NOSE WHEEL STEERING. AIRCRAFT HAD TO BE TOWED. TROUBLE	SHOOTING SHOWED THE SERVO RUNNING WITHOUT ACTUATION OF STEERING, THE AIRCRAFT WAS JACKED AND THE SERVO REMOVED. FURTHER	 INVESTIGATING SHOWED THE SHAFT WAS SHEARED IN THE SERVO. REPLACED SERVO, RESHIMMED NOSE GEAR AND REPACKED WHEEL BEARIN	GS. OPERATIONAL CHECK OF NOSE WHEEL STEERING WAS ACCOMPLISHED WITH NO DISCREPANCIES NOTED. ALL WORK PERFORMED PER THE 	LEARJET MM. AIRCRAFT RETURNED TO SERVICE. (X)		2	L	7	2 	4F				A10CE 					 
1995080400558	19950804	00558	EU 	1995	8	4	JZBR9510606 	1	19950605	G	2430	1PP2C	WIRE 			AMD 	FALC50	FALCON900 	2700160	EU 										NR 1 BAT BUS	SHORTED 	B		A	JZBR	K				NONE 				B	W		SMOKE/FUMES/ODORS/SPARKS 	INADEQUATE Q C 		IN	INSP/MAINT 	1			EA	25	74FS	1380 				085				UPON SHUT DOWN OF ENGINES, CREW EXPERIENCED SMOKE IN CLOSET AFT OF PILOT'S SEAT. SMOKE STOPPED AFTER BATTERIES WERE SHU	T OFF. UPON INSPECTION, FOUND THE COMPOSITE BULKHEAD, JUST FORWARD OF M.E.D., WAS BURNED AT ATTACH BRACKET FOR CURTAIN 	TRACK. AFTER LOWERING HEADLINERS, FOUND ONE OF THE SCREWS SEVERING CURTAIN TRACK CHAFED THROUGH FEEDER CABLE. CURRENT 	TRAVELED THROUGH THE SCREW, THROUGH CURTAIN TRACK, THROUGH ATTACH BRACKET, AND SHORTED IN THE BULKHEAD. CURTAIN TRACK A	TTACH SCREWS WERE TOO LONG. (X)		2	L	7	3 	4F			RT	A46EU 					 
1995092900398	19950929	00398	NM 	1995	9	29	KT3R643L 	1	19950823	G	5320	65198618	T-CHORD 			BOEING	727 	72722 	1384002	NM 										FS 335 RT	CORRODED 	B			KT3R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			WP	07	32719	70646				20388				SEVERE EXFOLIATING CORROSION FOUND ON SEC 41, LOWER RT T-CHORD AT BS 335 AND BS 350, RBL 18; CORROSION FOUND AFTER SKIN 	WAS OPENED UP TO INVESTIGATE CAUSE OF SKIN PILLOWING BETWEEN FASTENERS AND DISHED HEADS ON RIVETS. CORROSION LIMITED TO	 T-CHORD ONLY. INSPECTED ON CARD NR C53-100-01. DAMAGE REPAIRED ON W.O. ALL-02-000279 BY REPLACING PART. T.A.T., 70,6	45.41 HOURS. T.A.C., 52,119. (X)			2	L	7	3 	4F				A3WE 					 
1996041800186	19960418	00186	EA 	1996	4	18	LCFR950821 	2	19950821	G	7230	3024901	BLADE 		3018111 	BELL 	212 	212 	1181420	SW 	PWA 	PT6T 	PT6T3 	52045	EA 					COMP 1ST STAGE	ERODED 	B			LCFR	E				ENGINE SHUTDOWN 				R			PARTIAL RPM/PWR LOSS 			NR	NOT REPORTED 	1			NM	09	81FC	7224 	4109 		5974	30753	CPPS60382			THREE LOUD REPORTS WERE HEARD AND THEN NR 2 ENGINE WENT TO FLIGHT IDLE. PILOT SHIFTED TO MANUAL FUEL CONTROL AND ITT WE	NT TO 1,000 DEGREES CELSIUS. ENGINE WAS SHUT DOWN AND AIRCRAFT LANDED SAFELY. SUSPSECT COMPRESSOR STALLS DUE TO ERODED	 AND DIRTY COMPRESSOR BLADES. (X)				1	G	7	1 	4U	4	U		H4SW 	E22EA				 
1995081100515	19950811	00515	WP 	1995	8	11	LJER950516 	1	19950516	G	6520	A1111	GEARBOX 		A0211 	ROBSIN	R22 	R22ALPHA 	7640104	WP 										T/R	UNDER TORQUE 	B			LJER	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			NM	09	511TT		888 		1301	0439				TAIL ROTOR GEARBOX OUTPUT SHAFT RETAINING NUT, PN MS1414526, WAS FOUND SLIPPING AND UNDERTORQUED. DURING 100-HOUR INSPE	CTION, TAIL ROTOR BLADE ROTATION NOTED MOVING MORE THAN NORMAL GEAR BACKLASH. TEAR DOWN OF THE T/R GEARBOX REVEALED NUT	 TORQUED TO 75 INCHES/POUNDS VS 250 AND WASHER AND KEY WERE WORN. THIS GEARBOX WAS NOT SUBJECT TO AD 94-17-07. THE MAN	UFACTURER DOES NOT PUBLISH INSPECTION CRITERIA IN THIS AREA. A/C TT 6229.3 (X)			1	G	7	1 	3O				H10WE 					 
1996010500424	19960105	00424	SO 	1996	1	5	MCA12BMV 	2	19951027	G	7310	64103211A8	VALVE 			PIPER 	PA28 	PA28RT201T 	7102817	SO 	CONT 	O360 	TSIO360FB 	17025	SO 					FUEL MANIFOLD	LEAKING 	D				K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			GL	23	8412B	98 			11239506CR	28R8131164	299536R			FUEL MANIFOLD VALVE FOUND LEAKING AROUND VALVE DIAPHRAGM. REASON FOR LEAK UNKNOWN. ENGINE AND COMPONENTS REBUILT BY TC	M 5-12-95. (X)					1	L	7	1 	3O	3	O		2A13 	E9CE				 
1995070700356	19950707	00356	EU 	1995	7	7	RMXA9520526 	1	19950326	G	6240	117945641	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										MAST MOMENT	FAILED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117LS	214 				7113				INDICATOR CAUSED CIRCUIT BREAKER TO STAY POPPED. NOTHING WRONG WITH M.M. TRANSMITTER, MATCHED SET.						1	G	7	2 	3U				H13EU 					 
1995070700357	19950707	00357	EU 	1995	7	7	RMXA9520527 	1	19950326	G	7714	1179405303	INDICATOR 			BOLKMS	117 	BK117A1 	5626010	EU 										TRIPLE TACH	ERRATIC 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117LF	128 				7013				NUMBER 2 NEEDLE OCCASSIONALLY ERRATIC. ROTOR NEEDLE IS STILL ERRATIC.						1	G	7	2 	3U				H13EU 					 
1995070700358	19950707	00358	EU 	1995	7	7	RMXA9520529 	1	19950326	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL QTY	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	1140H	1 				7078				#1 & #2 SUPPLY DROPPED TO ZERO SLOWLY ONLY DURING FLIGHT. AFTER COLD SOAKED FOR 12 HOURS SAME PROBLEM AS BEFORE.						1	G	7	2 	3U				H13EU 					 
1995070700359	19950707	00359	SW 	1995	7	7	RMXA9520530 	1	19950326	G	2432	SP170A	BATTERY 			BELL 	206 	206L 	1181522	SW 										DC SYS	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	224LF					45199				BATTERY HAS THREE CELLS MARKED IN RED.						1	G	7	1 	3U				H2SW 					 
1995070700360	19950707	00360		1995	7	7	RMXA9520531 	4	19950326	G	2350	18282G	HEADSET 		H1066 	BOLKMS	117 	BK117A3 	5626015	EU 										COCKPIT	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	117LS					7113				SOMETIMES WILL NOT TRANSMIT OR RECEIVE. RETURN FOR CREDIT.						1	G	7	2 	3U				H13EU 					 
1995070700361	19950707	00361	NE 	1995	7	7	RMXA9520533 	2	19950326	G	7313	411101007	NOZZLE ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 	LYC 	LTS101	LTS101750B1 	41560	NE 					GAS PRODUCER	CRACKED 	E			RMXA	K				NONE 				R			PARTIAL RPM/PWR LOSS 			IN	INSP/MAINT 	1			SW	05	117VU	578 				7211	LE45528E			UPON INSPECTION OF ENGINE ASSEMBLY FOR CAUSE OF LOW POWER (-86%) THE G.P. NOZZLE WAS FOUND TO HAVE A LARGE CIRCUMFERENTI	AL CRACK ON THE INNER SHROUD TO VANE ASSY. WELD (81/2" CRACK) CIRCUMFERENCE OF INNER SHROUD IS APPROXIMATELY 19". REPLAC	ED NOZZLE.				1	G	7	2 	3U	3	U		H13EU 	E5NE10				 
1995070700362	19950707	00362	SW 	1995	7	7	RMXA9520535 	1	19950326	G	3340	A469B	LAMP 			BELL 	206 	206L1 	1182107	SW 										ANTI COLL	FAILED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2070Z	15 				45730				FLASH BURNED OUT/INOPERABLE AFTER ONLY 14.9 HOURS. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995070700363	19950707	00363	SW 	1995	7	7	RMXA9520539 	1	19950326	G	6310	222044672101	COUPLING 			BELL 	222 	222U 	1182140	SW 										ENG/XMSN	CORRODED 	E			RMXA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05										CORROSION ON THE GEARS WHEN RECEIVED.						1	G	7	2 	3U				H9SW 					 
1995070700364	19950707	00364	EU 	1995	7	7	RMXA9520542 	1	19950326	G	7714	DL40438	INDICATOR 			BOLKMS	105 	BO105A 		EU 										TRIPLE TACH	FLUCTUATES 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105NG	16 				632				N2 NEEDLE FLUCUATES 3% AT 100% - ONLY 16.1 HOURS SINCE REPAIR.						1	G	7	2 	3U				H3EU 					 
1995070700365	19950707	00365	EU 	1995	7	7	RMXA9520543 	1	19950326	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL QTY	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	1140H	7 				7078				MAIN DROPPED OFF SLOWLY TO 250KG. THEN CAME BACK UP DURING FLIGHT. INSTALLED ONLY .6 HOURS SINCE LAST REPAIR 3/15/94. T	HE FIFTH UNIT WORKED.					1	G	7	2 	3U				H13EU 					 
1995070700366	19950707	00366	EU 	1995	7	7	RMXA9520544 	1	19950326	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL QTY	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	05	1140H	1 				7078				MAIN FUEL QTY INDICATION DROPPED TO ZERO WHILE FLYING. SAME PROBLEM AS BEFORE.						1	G	7	2 	3U				H13EU 					 
1995070700367	19950707	00367	EU 	1995	7	7	RMXA9520545 	1	19950326	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL QTY	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			NR	NOT REPORTED 	1			SW	05	1140H	1 				7078				#1 SUPPLY GUAGE DROPPED TO 0 "ZERO", AFTER 25 MINUTES OF FLIGHT. AIRCRAFT COLD SOAKED OVERNIGHT.						1	G	7	2 	3U				H13EU 					 
1995070700368	19950707	00368	EU 	1995	7	7	RMXA9520547 	1	19950326	G	7714	32005008	TACH GENERATOR 			BOLKMS	105 	BO105S 	5626006	EU 										ENGINE	INOPERATIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105NG	4 				S632				INOPERABLE - TOTALLY, ONLY 3.8 HOURS SINCE OVERHAUL.						1	G	7	2 	3U				H3EU 					 
1995070700369	19950707	00369	CE 	1995	7	7	RMXA9520549 	1	19950326	G	3244	265F864	TIRE 			BEECH 	200 	200BEECH 	1152920	CE 										MLG	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	75LV	95 				BB1075				KNOT ON TIRE (CORD SEPARATION) REMOVED AND REPLACED.						1	L	7	2 	4T				A24CE 					 
1995070700370	19950707	00370	CE 	1995	7	7	RMXA9520550 	1	19950326	G	3244	265F864	TIRE 			BEECH 	200 	200BEECH 	1152920	CE 										MLG	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	75LV	76 				BB1075				HAS BUMP ON TIRE DUE TO CORD SEPARATION. THIS IS THE SECOND TIRE TO DO THIS. REMOVED AND REPAIRED.						1	L	7	2 	4T				A24CE 					 
1995070700371	19950707	00371		1995	7	7	RMXA9520551 	4	19950326	G	2562	ELT10	BATTERY 	NARCO 																ELT	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										UNABLE TO INSTALL ON A/C DUE TO ELT BATTERY ELECTRIC STUD NUT PLATE DEBONDED. RETURN FOR REPLACEMENT PART.																			 
1995070700372	19950707	00372	GL 	1995	7	7	RMXA9520553 	2	19950326	G	7250	6895021	1ST NOZZLE 								ALLSN 	250C 	250C20B 	03013	GL 					ENGINE	DEFECTIVE 	E			RMXA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05										DIAPHRAM IMPROPERLY INSTALLED, BOLT HOLES WOULD NOT LINE UP.											3	U			E4CE				 
1995070700373	19950707	00373	SW 	1995	7	7	RMXA9520557 	1	19950326	G	6310	222044607003	COUPLING 			BELL 	222 	222U 	1182140	SW 										ENG/XMSN	CORRODED 	E		A	RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	64 				47520				INNER COUPLING HAS EXCESSIVE CORROSION PITTING AFTER 63.7 HOURS, IMPROPER HEAT TREATMENT COULD HAVE BEEN A FACTOR. NEW 	DRIVE SHAFT IN A/C, COUPLING CAME WITH IT AND ONLY HAS 63.7 HOURS. REMOVED AND REPLACED.					1	G	7	2 	3U				H9SW 					 
1995070700374	19950707	00374	SW 	1995	7	7	RMXA9520558 	1	19950326	G	6310	222044672101	COUPLING 			BELL 	222 	222U 	1182140	SW 										ENG/TRANS	CORRODED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	64 				47520				1 EACH OUTER COUPLING HAS EXCESSIVE CORROSION PITTING AFTER 63.7 HOURS IMPROPER HEAT TREATMENT COULD HAVE BEEN A FACTOR 	IN THE MALFUNCTION. REMOVED AND REPLACED.					1	G	7	2 	3U				H9SW 					 
1995070700375	19950707	00375	SW 	1995	7	7	RMXA9520562 	1	19950326	G	6310	222044607003	COUPLING 			BELL 	222 	222U 	1182140	SW 										ENG/TRANS	CORRODED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911LW	60 				47520				INNER COUPLING HAS CORROSION PITTING ON GEAR TEETH CONTACT AREA, COUPLING ONLY HAS 59.6 HOURS SINCE NEW. REMOVED AND REP	LACED.					1	G	7	2 	3U				H9SW 					 
1995070700376	19950707	00376	EU 	1995	7	7	RMXA9520567 	1	19950326	G	6210	10513103505	BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										BLADE PIN	SCORED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	212AE					7222				BLADE PIN BOLT SCORED. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700377	19950707	00377	EU 	1995	7	7	RMXA9520568 	1	19950326	G	7110	1172321801	STAY ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										LT COWL	WORN 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	212AE	598 				7222				COWL LT STAY ASSY WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700378	19950707	00378	EU 	1995	7	7	RMXA9520569 	1	19950326	G	7110	1172321802	STAY ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										RT COWL	WORN 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	212AE	598 				7222				COWL RT STAY ASSY WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700379	19950707	00379	EU 	1995	7	7	RMXA9520570 	1	19950326	G	3150	6607A2114	WARNING LIGHT 			BOLKMS	105 	BO105LSA3 	5626020	EU 										OIL PRESS	MALFUNCTION 	E			RMXA	K				NONE 				N			FALSE WARNING 			IN	INSP/MAINT 	1			SW	05	911SV	165 				2033				ANNUNCIATOR LIGHT ON WITH A/C RUNNING. REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU 					 
1995070700380	19950707	00380	EU 	1995	7	7	RMXA9520572 	1	19950326	G	6420	1053170018	FITTED BOLT 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R	WORN 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	212AE	276 				7222				FITTED BOLT WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700381	19950707	00381	EU 	1995	7	7	RMXA9520575 	1	19950326	G	2822	1176415103	PUMP 			BOLKMS	117 	BK117C1 		EU 										FUEL SYS	LEAKING 	E			RMXA	K				NONE 				K			FLUID LOSS 			IN	INSP/MAINT 	1			SW	05	317MC	333 				7505				BOOST PUMP LEAKING FROM SEAL DRAIN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700382	19950707	00382	EU 	1995	7	7	RMXA9520576 	1	19950326	G	5350	365A24113300	FITTING FWD 			AEROSP	SA365 	SA365N1 	8680668	EU 										MCB COWLING	CRACKED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	365SC	484 				6298				CRACKED FITTING. REMOVED AND REPLACED.						1	G	7	2 	3U				H10EU 					 
1995070700383	19950707	00383	EU 	1995	7	7	RMXA9520577 	1	19950326	G	5530	11730650	ENDPLATE 			BOLKMS	117 	BK117A3 	5626015	EU 										VERT FIN	CRACKED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4493X	142 				S7038				VERT FIN ENDPLATE CRACKED AT KNOCKOUT PLUG.						1	G	7	2 	3U				H13EU 					 
1995070700384	19950707	00384	EU 	1995	7	7	RMXA9520579 	1	19950326	G	7712	117902131	VARTOMS 			BOLKMS	117 	BK117C1 		EU 										RPM CONTROL	MALFUNCTION 	E			RMXA	O				OTHER 				O			OTHER 			TO	TAKEOFF 	1			SW	05	317MC	351 				7505				EXCESSIVE TORQUE SPLITS ON TAKE OFF. REMOVED AND REPLACED RPM CONTROL.						1	G	7	2 	3U				H13EU 					 
1995070700385	19950707	00385	EU 	1995	7	7	RMXA9520588 	1	19950326	G	7120	10560387	BUSHING 			BOLKMS	105 	BO105LSA3 	5626020	EU 										ISOLATION MOUNT	SEPARATION 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911SV	466 				2033	280033			BUSHING SEPARATION. REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU 					 
1995070700386	19950707	00386	EU 	1995	7	7	RMXA9520589 	1	19950326	G	6420	1053170018	FITTED BOLT 			BOLKMS	117 	BK117C1 		EU 										T/R	WORN 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	911SV	215 				2033				FITTED BOLT DRY FILM WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700387	19950707	00387	EU 	1995	7	7	RMXA9520591 	1	19950326	G	6720	11788659	BELLCRANK ASSY 			BOLKMS	117 	BK117A3 	5626015	EU 										T/R CONTROL	BEARING WORN 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	527MB	70 				7103				TEFLON BEARING IS WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700388	19950707	00388	EU 	1995	7	7	RMXA9520592 	1	19950326	G	6720	11788659	BELLCRANK ASSY 			BOLKMS	117 	BK117B1 	5626012	EU 										T/R CONTROL	WORN 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	213AE	308 				7219				BELLCRANK ASSY WORN. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700389	19950707	00389	EU 	1995	7	7	RMXA9520727 	1	19950426	G	5610	1172258101	WINDOW ASSY 			BOLKMS	117 	BK117C1 		EU 										SIDE ASSY	CRACKED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	362 				7505				SIDE WINDOW ASSY CRACKED.						1	G	7	2 	3U				H13EU 					 
1995070700390	19950707	00390	EU 	1995	7	7	RMXA9520728 	1	19950426	G	5210	1172428111	CATCHER 			BOLKMS	117 	BK117C1 		EU 										LT DOOR	WORN 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	397 				7505				LT CATCHER WORN OUT. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700391	19950707	00391	EU 	1995	7	7	RMXA9520729 	1	19950426	G	5210	1172428211	CATCHER 			BOLKMS	117 	BK117C1 		EU 										LT DOOR	WORN 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	397 				7505				CATCHER WORN OUT. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700392	19950707	00392	EU 	1995	7	7	RMXA9520730 	1	19950426	G	5530	11730650	ENDPLATE 			BOLKMS	117 	BK117A3 	5626015	EU 										VERT STAB	HOLED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	4493X	10 				7038				LARGE HOLE ON OUTSIDE OF FACE OF END PLATE. WAS REPAIRED 1/5/95 FOR CRACKS IN SAME AREA.						1	G	7	2 	3U				H13EU 					 
1995070700393	19950707	00393	EU 	1995	7	7	RMXA9520731 	1	19950426	G	5530	11730650	ENDPLATE 			BOLKMS	117 	BK117C1 		EU 										VERT STAB	BREAKOUT 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	351 				7505				BREAKOUT INSERT OF BONDING. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700394	19950707	00394	EU 	1995	7	7	RMXA9520735 	1	19950426	G	6730	7012409901	ACTUATOR 			BOLKMS	117 	BK117C1 		EU 										DUPLEX PITCH	FAILURE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	12 				7505				ZE27 ERROR CODE ON PRE-FLIGHT TEST APZ WILL NOT ENGAGE. PITCH SERVO FAILURE. REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU 					 
1995070700395	19950707	00395	SW 	1995	7	7	RMXA9520736 	1	19950426	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	DEFECTIVE 	E			RMXA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	05	2070Z	27 				45730				BLADE DEFECTIVE. HUB VABRATION.						1	G	7	1 	3U				H2SW 					 
1995070700396	19950707	00396	SW 	1995	7	7	RMXA9520737 	1	19950426	G	6210	206015001107	BLADE 			BELL 	206 	206L1 	1182107	SW 										M/R	DEFECTIVE 	E			RMXA	K				NONE 				E			VIBRATION/BUFFET 			IN	INSP/MAINT 	1			SW	05	2070Z	27 				45730				BLADE DEFECTIVE. HUB VABRATION.						1	G	7	1 	3U				H2SW 					 
1995070700397	19950707	00397	SW 	1995	7	7	RMXA9520738 	1	19950426	G	6220	206011150105	FITTING 			BELL 	206 	206L1 	1182107	SW 										STATIC STOP	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2070Z					45730				STATIC STOP SURFACE NOT FLAT/DEFECTIVE. REPLACED.						1	G	7	1 	3U				H2SW 					 
1995070700398	19950707	00398	SW 	1995	7	7	RMXA9520739 	1	19950426	G	6220	206011150105	FITTING 			BELL 	206 	206L1 	1182107	SW 										STATIC STOP	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2070Z	166 				45730				FITTING MOVES IN YOKE, STATIC STOP SURFACE NOT FLAT. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995070700399	19950707	00399	SW 	1995	7	7	RMXA9520740 	1	19950426	G	6310	222044685101	SHAFT ASSY 			BELL 	222 	222 	1182122	SW 										M/R	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										SHAFT ASSY PRIMER COMING OFF OF I.D.						1	G	7	2 	3U				H9SW 					 
1995070700400	19950707	00400	SW 	1995	7	7	RMXA9520741 	1	19950426	G	6310	222044685101	SHAFT ASSY 			BELL 	222 	222 	1182122	SW 										M/R DRIVE	DEFECTIVE 	E			RMXA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05										EPOXY ZINC COMING OFF AT I.D. NEW PART RECEIVED DEFECTIVE.						1	G	7	2 	3U				H9SW 					 
1995070700401	19950707	00401	SW 	1995	7	7	RMXA9520742 	1	19950426	G	6310	222044685101	SHAFT ASSY 			BELL 	222 	222 	1182122	SW 										M/R DRIVE	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										BLACK OXIDE COATING MISSING ON SPLINES AND CORROSION (SLIGHT) HAS STARTED.						1	G	7	2 	3U				H9SW 					 
1995070700402	19950707	00402	SW 	1995	7	7	RMXA9520743 	1	19950426	G	6310	222044685101	SHAFT ASSY 			BELL 	222 	222 	1182122	SW 										M/R DRIVE	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										PRIMER FLAKING OFF OF I.D. OF SHAFT.						1	G	7	2 	3U				H9SW 					 
1995070700403	19950707	00403	SW 	1995	7	7	RMXA9520744 	1	19950426	G	6310	222044685101	SHAFT ASSY 			BELL 	222 	222 	1182122	SW 										M/R DRIVE	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										DEFECT IN COATING ON INSIDE DIAMETER OF SHAFT TUBE AND ALSO DEFECT IN BLACK OXIDE COATING ON SPLINGS ON WND OF SHAFT TUB	E (AREA AFFECTED JUST INSIDE AND MARKED PAST SHOULDER - CHECKED WITH BORESCOPE).					1	G	7	2 	3U				H9SW 					 
1995070700404	19950707	00404	SW 	1995	7	7	RMXA9520745 	1	19950426	G	6310	222044685101	SHAFT ASSY 			BELL 	222 	222 	1182122	SW 										M/R DRIVE	DEFECTIVE 	E			RMXA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05										EPOXY ZINC COATING IS COMING OFF OF I.D. SHAFT IS NEW FROM BELL.						1	G	7	2 	3U				H9SW 					 
1995070700405	19950707	00405	SW 	1995	7	7	RMXA9520746 	1	19950426	G	6310	222044685101	SHAFT ASSY 			BELL 	222 	222 	1182122	SW 										M/R DRIVE	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										EPOXY ZINC COATING IS COMING OFF OF I.D. SHAFT IS NEW FROM BELL.						1	G	7	2 	3U				H9SW 					 
1995070700406	19950707	00406	EU 	1995	7	7	RMXA9520747 	1	19950426	G	3340	1159851	LAMP 			BOLKMS	105 	BO105S 	5626006	EU 										LOCATOR II	FAILED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	105NG	151 				S632				INOPERABLE, ONLY 150.8 HOURS ON PART, REQUEST REPLACEMENT PART. REMOVED AND REPLACED.						1	G	7	2 	3U				H3EU 					 
1995070700407	19950707	00407		1995	7	7	RMXA9520748 	4	19950426	G	3422	2594484	FLUX VALVE 			BOLKMS	117 	BK117C1 		EU 										COMPASS SYS	FAULTY 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	317MC	268 				7505				FLUX VALVE WILL NOT COMPENSATE FOR 25 DEGREE ERROR.						1	G	7	2 	3U				H13EU 					 
1995070700408	19950707	00408	SW 	1995	7	7	RMXA9520749 	1	19950426	G	3340	A469B	LAMP 			BELL 	206 	206L1 	1182107	SW 										STROBE	FAILED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2070Z	11 				45730				BROKEN BASE, INOPERABLE. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995070700409	19950707	00409	SW 	1995	7	7	RMXA9520750 	1	19950426	G	3310	1179203103	CONTROL UNIT 			BELL 	222 	222 	1182122	SW 										LIGHTING	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05										POPPING CIRCUIT BREAKER WHEN RHEOSTAT IS TURNED ON. NEVER INSTALLED IN AIRCRAFT.						1	G	7	2 	3U				H9SW 					 
1995070700410	19950707	00410	SW 	1995	7	7	RMXA9520761 	1	19950427	G	7722	12444420	INDICATOR 			BELL 	206 	206L1 	1182107	SW 										ENG TOT	STICKING 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	5741Y	681 				45467				STICKING AROUND 500'C AND AS PER ASB 206L-94-94 REMOVED AND REPLACED						1	G	7	1 	3U				H2SW 					 
1995070700411	19950707	00411	SW 	1995	7	7	RMXA9520762 	1	19950427	G	6310	222044672101	COUPLING 			BELL 	222 	222U 	1182140	SW 										M/R DRIVE	CORRODED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	222DE	5 				47520				CORROSION IS FOUND REPEATEDLY IN THIS AREA ON MANY BHT1 222NT MAIN DRIVE SHAFTS. SUSPECT FAULTY GREASE P/N 204-040-755-0	05 OR OTHER DEFECTS. REMOVED AND REPLACED					1	G	7	2 	3U				H9SW 					 
1995070700412	19950707	00412	SW 	1995	7	7	RMXA9520763 	1	19950428	G	2432	31908001	BATTERY 			BELL 	230 	230 	1182149	SW 										DC SYS	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	230EM	72 				23011				LOW POWER, LONG CHARGE TIME. REMOVED						1	G	7	2 	3U			NC	H9SW 					 
1995070700413	19950707	00413	SW 	1995	7	7	RMXA9520764 	1	19950428	G	3340	GE4580	LAMP 			BELL 	206 	206L1 	1182107	SW 										SEARCH LIGHT	FAILED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	5741Y	3 				45467				LAMP WAS INSTALLED NEW WITH SEARCH LIGHT ASSEMBLY. ONLY LASTED 3.0 HOURS. (REMOVED & REPLACED)						1	G	7	1 	3U				H2SW 					 
1995070700414	19950707	00414	EU 	1995	7	7	RMXA9520765 	1	19950428	G	2841	1179405403	INDICATOR 			BOLKMS	117 	BK117A3 	5626015	EU 										FUEL QTY	STICKS 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	1140H	1 				7078				#1 SUPPLY GAUGE STICKS ABOUT 8 GALLONS, SAME PROBLEM AS BEFORE.						1	G	7	2 	3U				H13EU 					 
1995070700415	19950707	00415		1995	7	7	RMXA9520766 	4	19950428	G	2562	ELT1104	ELT 	NARCO 	ELT1104 	BOLKMS	117 	BK117B1 	5626012	EU 										COCKPIT	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	215AE	25 				7216				WILL NOT SHUT OFF. WAS ON A/C ONLY 27 DAY AFTER REPAIRED AND ONLY 24.7 HOURS.						1	G	7	2 	3U				H13EU 					 
1995070700416	19950707	00416	SW 	1995	7	7	RMXA9520767 	1	19950428	G	6730	6225194001	SERVO MOTOR 			BELL 	206 	206L1 	1182107	SW 										CONTROL SYS	DEFECTIVE 	E			RMXA	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	05	2070Z					45730				SERVO WAS REPAIRED 6-8-94. RETURNED & PUT ON SHELF FOR 7 MONTHS. SERVO WAS PULLED OFF SHELF 1-20-95 AND INSTALLED ON AIR	CRAFT. SERVO DID NOT WORK--SAME PROBLEMS AS BEFORE THE REPAIR AND NOW MAKES FUNNY NOISE WHILE RENGAGING. F.A. LIGHT INTE	RMITTENT, ENGAGES AND DROPS OFF LINES INTERMITTENTLY.				1	G	7	1 	3U				H2SW 					 
1995070700417	19950707	00417	SW 	1995	7	7	RMXA9520768 	1	19950428	G	3340	A469B	LAMP 			BELL 	206 	206L1 	1182107	SW 										STROBE	FAILED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2070Z	49 				45730				LAMP INOPERATIVE. WILL NOT FLASH REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995070700418	19950707	00418	SW 	1995	7	7	RMXA9520769 	1	19950428	G	3340	A469B	LAMP 			BELL 	206 	206L1 	1182107	SW 										STROBE	FAILED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2070Z	18 				45730				LAMP BROKEN. WILL NOT FLASH. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995070700419	19950707	00419	SW 	1995	7	7	RMXA9520770 	1	19950428	G	3340	A469B	LAMP 			BELL 	206 	206L1 	1182107	SW 										STROBE	CRACKED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2070Z					45730				STROBE HAS CRACKED BULB. REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW 					 
1995070700420	19950707	00420	SW 	1995	7	7	RMXA9520771 	1	19950428	G	3340	A469B	LAMP 			BELL 	206 	206L1 	1182107	SW 										STROBE	CRACKED 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	2070Z	5 				45730				STROBE HAS CRACKED TUBE. REMOVED AND REPLACED						1	G	7	1 	3U				H2SW 					 
1995070700421	19950707	00421	SW 	1995	7	7	RMXA9520871 	1	19950505	G	2435	23081018	STARTER 			BELL 	206 	206L1 	1182107	SW 										START/GEN	DEFECTIVE 	E			RMXA	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	05	5741Y	87 				45467				STARTER WILL NOT REACH 14% N1 ENGINE SPEED. ONLY 86.7 HOURS SINCE OVERHAUL.						1	G	7	1 	3U				H2SW 					 
1995112400069	19951124	00069	EU 	1995	11	24	RU3A95007 	1	19950914	G	3310	M4001265	RELAY 			BRAERO	DH125 	BAE125800A 	1500285	EU 										SUBPANEL 'B'	STUCK CLOSED 	A			RU3A	A	G	H		UNSCHED LANDING 	O2 MASK DEPLOYED 	DEACTIVATE SYST/CIRCUITS		B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			SW	21	95					258131				DURING A NORMAL MISSION, THE PILOT AND COPILOT EXPERIENCED A VARIETY OF ANNUNCIATOR LIGHTS THAT WENT FULL BRIGHT FOR NO 	APPARENT REASON. DURING THIS EVENT THERE WAS ALSO AN ODOR OF SOMETHING ELECTRICAL HEATING UP. UPON INVESTIGATION BY MA	INTENANCE PERSONNEL, FOUND THAT RELAY 'DA' ON SUBPANEL 'B' HAD STUCK CLOSED CAUSING A REVERSE BIAS TO BE APPLIED TO TWO 	POWER TRANSISTORS 'YC' AND 'YD' WHICH CAUSED THE COCKPIT LIGHTS TO STAY FULL BRIGHT AND THE TRANSISTORS TO HEAT UP AND P	UT OUT A BURNING SMELL IN THE COCKPIT. (X)		2	L	7	2 	4F			RT	A3EU 					 
1995120100687	19951201	00687	EU 	1995	12	1	RU3A950071 	1	19950914	G	3310	M4001265	RELAY 'DA' 			BRAERO	DH125 	BAE125800A 	1500285	EU 										SUBPANEL 'B'	STUCK 	A	L		RU3A	A	G	H		UNSCHED LANDING 	O2 MASK DEPLOYED 	DEACTIVATE SYST/CIRCUITS		B			SMOKE/FUMES/ODORS/SPARKS 			NR	NOT REPORTED 	1			SW	21	95					258131				DURING A NORMAL MISSION, THE PILOT AND CO-PILOT EXPERIENCED A VARIETY OF ANNUNCIATOR LIGHTS THAT WENT FULL BRIGHT FOR NO	 APPARENT REASON. DURING THIS EVENT THERE WAS ALSO AN ODOR OF SOMETHING ELECTRICAL HEATING UP. UPON INVESTIGATION BY M	AINTENANCE PERSONNEL IT WAS FOUND THAT RELAY 'DA' ON SUBPANEL 'B' HAD STUCK CLOSED CAUSING A REVERSE BIAS TO BE APPLIED 	TO TWO POWER TRANSISTORS 'YC' AND 'YD' WHICH CAUSED THE COCKPIT LIGHTS TO STAY FULL BRIGHT AND THE TRANSISTORS TO HEAT U	P AND PUT OUT A BURNING SMELL IN THE COCKPIT. (M)		2	L	7	2 	4F			RT	A3EU 					 
1995072800348	19950728	00348	CE 	1995	7	28	TEIL952 	1	19950505	G	2910	124D0036SL0226	HOSE ASSY 			CESSNA	500 	560CESSNA 	2076750	CE 	PWA 	JT15 	JT15D5 	52112	NE 					RT HYD	FAILED 	H			TEIL	K				NONE 				K	J		FLUID LOSS 	WARNING INDICATION 		LD	LANDING 	1			SW	09	502T	2583 				5600153	108316			DURING APPROACH AND LANDING AT SAT, AS LANDING GEAR WAS EXTENDED, HYDRAULIC LOW FLOW (RH) AND HYDRAULIC LOW LEVEL LIGHTS	 ILLUMINATED. INSPECTION ON THE GROUND AT SAT BY LOCAL MAINTENANCE PERSONNEL DETERMINED THE RH HYDRAULIC PUMP PRESSURE L	INE HAD FAILED AND WAS LEAKING FLUID. REPLACEMENT LINE WAS ORDERED AND SHIPPED TO SAT MAINTENANCE PERSONNEL FROM CESSNA 	AIRCRAFT AT ICT. LINE WAS REPLACED, SYSTEMS SERVICED, AND GROUND RUNS ACCOMPLISHED. HYDRAULIC PRESSURE FILTERS WERE INSP	ECTED FOR METAL CONTAMINATION AND NONE FOUND. SYSTEM BLED AND AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A22CE 	E25EA				 
1995072800349	19950728	00349	GL 	1995	7	28	TEIL953 	2	19950508	G	7323	10560590	LEVER ASSY 			BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					GOV	DEFECTIVE 	H			TEIL	K				NONE 				W			INADEQUATE Q C 			IN	INSP/MAINT 	1			SW	09										GOVENOR ATTACH BEARING WILL NOT GO ON SLEEVE. MIC DIMENSION OF BEARING SHAFT 6.016 MM. NEW PART SECURED AND INSTALLED. N	EW PART SHAFT DIMENSION 5.9 MM.					1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995072800350	19950728	00350	GL 	1995	7	28	TEIL956 	2	19950609	G	7210	6875035	BEARING 		6894171 	BOLKMS	105 	BO105CBS 	5626008	EU 	ALLSN 	250C 	250C20B 	03013	GL 					ENG GR BOX	MAKING METAL 	H			TEIL	K				NONE 				J			WARNING INDICATION 			LD	LANDING 	1			SW	09	3539T	2327 			34866	S397				INNER RACE FAILED CAUSING METAL ON CHIP DETECTORS. GEARBOX OVERHAULED AND UPDATED TO LATEST MOD STANDARD. BEARINGS REPLA	CED.					1	G	7	2 	3U	3	U	NC	H3EU 	E4CE				 
1995072800351	19950728	00351	SO 	1995	7	28	TEIL958 	1	19950627	G	2433	1159SCAV373509	CONVERTER 			GULSTM	G1159 	G1159A 	3970109	SO 										AC/DC SYS	BURNED 	H			TEIL	K				NONE 				M			OVER TEMP 			IN	INSP/MAINT 	1			SW	09	506T	126 				484				DURING A POST FLIGHT INSPECTION, THE DC(+) OUTPUT LEAD INSULATION OF THE RH CONVERTER WAS OBSERVED TO BE BURNED. FURTHER	 INSPECTION REVEALED THE TERMINAL POST BURNED, AN IMPROPER STACKUP OF LOCWASHER, TERMINAL LUG, PLAIN WASHER AND LOCKNUT,	 AS WELL AS BEING LOOSE. WIRE AND TERMINAL LUG WERE INSPECTED FOR OVERHEAT DAMAGED AND DETERMINED TO BE SERVICABLE.				2	L	7	2 	4F				A12EA 					 
1995092900502	19950929	00502	SW 	1995	9	29	TEIL959 	1	19950918	G	6520	406340105101	SEAL 		206040400013	BELL 	206 	206B 	1181511	SW 										GEARBOX	DETERIORATION 	H			TEIL	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	09	3528T	6955 			ALO12031	3516				AFTER ONLY 30 HOURS OF OPERATION WITH NEW STYLE SEAL, SEAL BEGAN TO DETERIORATE AROUND OUTPUT SHAFT SEALING SURFACE INTO	 OIL CAUSING OIL COLOR TO CHANGE TO BLACK. ACCUMULATION OF RUBBER SEAL MATERIAL ON CHIP PLUG DETECTOR FACE CAUSED CHIP P	LUG DETECTOR TO BECOME INOPERATIVE. REPLACED SEAL				1	G	7	1 	3U				H2SW 					 
1995080400559	19950804	00559	EU 	1995	8	4	XC4R9542177 	1	19950503	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	EXCESS WORN 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		131 			1175					STARTER/GENERATOR'S BRUSHES WERE EXTREMELY WORN. THE BRUSHES WERE WORN 80 PERCENT - 90 PERCENT WITHIN 131.0 FLIGHT HOUR	S. RECOMMEND RE-DESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1995080400560	19950804	00560	EU 	1995	8	4	XC4R9552345 	1	19950513	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	EXCESS WORN 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		314 			72					STARTER/GENERATOR BRUSHES WORN EXCESSIVELY. BRUSHES WORN 70 PERCENT WITHIN 314.0 FLIGHT HOURS. SUBMITTER RECOMMENDS RE	-DESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1995080400561	19950804	00561	EU 	1995	8	4	XC4R9552405 	1	19950510	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	EXCESS WORN 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		149 			580					STARTER/GENERATOR UNIT'S BRUSHES WERE SEVERELY WORN. THE BRUSHES WERE WORN 70 PERCENT WITHIN 149.0 FLIGHT HOURS. SUBMI	TTER RECOMMENDS RE-DESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1995080400562	19950804	00562	EU 	1995	8	4	XC4R9552473 	1	19950520	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	EXCESS WORN 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		138 			210					STARTER/GENERATOR UNIT'S BRUSHES WERE WORN SEVERELY. THE BRUSHES WERE WORN 60 PERCENT WITHIN 138.0 FLIGHT HOURS. RECOM	MEND RE-DESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1995082500259	19950825	00259	EU 	1995	8	25	XC4R9552672 	1	19950524	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		290 			176					STARTER/GENRATOR UNIT'S BRUSHES WERE SEVERELY WORN. THE BRUSHES WERE WORN 80 PERCENT WITHIN 290.0 FLIGHT HOURS. SUBMIT	TER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1995081800605	19950818	00605	EU 	1995	8	18	XC4R9563056 	1	19950708	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		51 			72					STARTER/GENERATOR BRUSHES WORN EXCESSIVELY. BRUSHES WORN WITHIN 50 PERCENT WITHIN 51.0 FLIGHT HOURS. SUBMITTER RECOMME	NDS REDESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1995081800606	19950818	00606	EU 	1995	8	18	XC4R9563060 	1	19950708	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		341 			1012					STARTER/GENERATOR UNIT'S BRUSHES WERE EXCESSIVELY WORN. THE BRUSHES WERE WORN 80 PERCENT WITHIN 341.0 FLIGHT HOURS. SU	BMITTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1995081800607	19950818	00607	EU 	1995	8	18	XC4R9573434 	1	19950718	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										COMM END	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		100 			580					STARTER/GENERATOR UNIT'S BRUSHES WERE EXTREMELY WORN. THE BRUSHES WERE WORN 100 PERCENT WITHIN 100.0 FLIGHT HOURS. SUB	MITTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1996110700108	19961107	00108	EU 	1996	11	7	XC4R9573564 	1	19950728	G	2435	P0698703	BRUSHES 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	WORN 	B		A		K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SW	99		115 			1249					STARTER/GENERATOR BRUSHES WERE EXCESSIVELY WORN. THE BRUSHES WERE WORN 90 PERCENT WITHIN 115.0 FLIGHT HOURS. SUBMITTER	 RECOMMENDS RE-DESIGNING DEFECTIVE BRUSHES. THIS IS A CONTINUAL DISCREPANCY.					2	L	7	3 	4F			 	A46EU 					 
1996110700125	19961107	00125	EU 	1996	11	7	XC4R9573607 	1	19950728	G	2435	P0557427	ARMATURE 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										DRIVE END	CRACKED 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19	50HM		370 		791	153				THIS STARTER/GENERATOR WAS REMOVED FOR BRUSH AND BEARING REPLACEMENT. UPON INSPECTION OF ARMATURE, DRIVE END BAND WAS F	OUND CRACKED IN AREA OF SPOT WELD FOR OUTBOARD EDGE OF BAND TOWARDS INBOARD. LENGTH OF CRACK .155 INCH. (X)					2	L	7	3 	4F				A46EU 					 
1996032200034	19960322	00034	EU 	1996	3	22	XC4R9584051 	1	19950828	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	EXCESS WEAR 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		285 			909					STARTER GENERATOR'S BRUSHES ARE EXTREMELY WORN. THE BRUSHES WERE WORN 60 PERCENT WITHIN 285.0 FLIGHT HOURS. SUBMITTER 	RECOMMENDS RE-DESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU 					 
1995110600634	19951106	00634	EU 	1995	11	6	XC4R9594285 	1	19950914	G	2435	P0698703	BRUSH 	AUXILEC 	8060300 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	EXCESS WORN 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		210 			210					INSPECTION FOUND STARTER GENERATOR'S BRUSHES ARE EXTREMELY WORN. THE BRUSHES WERE WORN 80 PERCENT WITHIN 210.0 FLIGHT H	OURS. SUBMITTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES.					2	L	7	3 	4F				A46EU 					 
1995110600635	19951106	00635	EU 	1995	11	6	XC4R9594310 	1	19950914	G	2435	P0698703	BRUSH 	AUXILEC 	80603 	AMD 	FALC50	FALCON50MYST	2730106	EU 										START/GEN	EXCESS WORN 	B			XC4R	K				NONE 				O			OTHER 			IN	INSP/MAINT 	1			SO	19		185 			147					INSPECTION FOUND STARTER GENERATOR'S BRUSHES ARE EXTREMELY WORN. THE BRUSHES ARE WORN 70 PERCENT WITHIN 185.0 FLIGHT HO	URS. SUBMITTER RECOMMENDS REDESIGNING DEFECTIVE BRUSHES. (X)					2	L	7	3 	4F				A46EU